阅读说明：本技术 制动器特性
(Brake characteristics
) 是由 安德鲁·比尔 于 2020-04-29 设计创作，主要内容包括：公开了一种其上存储有指令的非暂态计算机可读存储介质,所述指令在由处理器执行时使该处理器执行以下操作：确定飞行器轮制动器是否能够执行未来的中断起飞事件。该确定包括根据中断起飞能量参数和制动器参数集确定制动器的预估质量是否足以执行未来的中断起飞事件。此外,公开了一种用于确定飞行器轮制动器是否能够执行未来的中断起飞事件的方法。(Disclosed is a non-transitory computer-readable storage medium having instructions stored thereon, which when executed by a processor, cause the processor to: it is determined whether the aircraft wheel brakes are capable of performing a future aborted takeoff event. The determining includes determining whether the estimated quality of the brake is sufficient to execute a future rejected takeoff event based on the rejected takeoff energy parameter and the set of brake parameters. Further, a method for determining whether an aircraft wheel brake is capable of performing a future aborted takeoff event is disclosed.)
1. A non-transitory computer-readable storage medium having instructions stored thereon, which when executed by a processor, cause the processor to:
determining whether the aircraft wheel brakes are capable of performing a future rejected takeoff event, comprising:
And determining whether the estimated quality of the brake is enough to execute the future aborted takeoff event according to the aborted takeoff energy parameter and the set of brake parameters.
2. The non-transitory computer readable storage medium of claim 1, wherein the instructions, when executed by a processor, cause the processor to:
determining a number of predicted future use cycles after which the predicted quality is expected to be insufficient to execute the future aborted takeoff event.
3. The non-transitory computer readable storage medium of claim 1 or 2, wherein the instructions, when executed by a processor, cause the processor to:
determining a mass limit defining a minimum mass required to execute the future aborted takeoff event.
4. The non-transitory computer readable storage medium of claim 3, wherein the instructions, when executed by a processor, cause the processor to:
determining whether the estimated mass is sufficient to perform the future aborted takeoff event by comparing the estimated mass to the mass limit.
5. The non-transitory computer readable storage medium of claim 3 or 4, wherein the instructions, when executed by a processor, cause the processor to:
determining the mass limit using an amount of energy that the brake will absorb when performing the future rejected takeoff event determined based on characteristics of the brake.
6. The non-transitory computer readable storage medium of any of claims 3 to 5, wherein the instructions, when executed by a processor, cause the processor to:
determining a number of predicted future cycles of use that reduces the predicted quality to the quality limit.
7. The non-transitory computer readable storage medium of any preceding claim, wherein the instructions, when executed by a processor, cause the processor to:
issuing a first notification if the projected quality is determined to be sufficient to execute the future aborted takeoff event.
8. The non-transitory computer readable storage medium of any preceding claim, wherein the instructions, when executed by a processor, cause the processor to:
If it is determined that the projected mass is insufficient to execute the future aborted takeoff events, the determination as to whether the brake is capable of executing the future aborted takeoff events is repeated.
9. The non-transitory computer-readable storage medium of claim 8, wherein:
repeating the determining using the updated aborted takeoff energy parameter determined based on the updated aircraft weight.
10. The non-transitory computer readable storage medium of claim 9, wherein the instructions, when executed by a processor, cause the processor to:
in response to the updated aircraft weight meeting an aircraft weight criterion, issuing a second notification indicating that the brakes need to be repaired or replaced, and ceasing repeating the determining.
11. The non-transitory computer readable storage medium of any preceding claim, wherein the instructions, when executed by a processor, cause the processor to:
determining the rejected takeoff energy parameter based on a set of user input parameters.
12. The non-transitory computer readable storage medium of any preceding claim, wherein:
the brake parameter set includes an upper temperature cutoff of the brake.
13. The non-transitory computer readable storage medium of any preceding claim, wherein the instructions, when executed by a processor, cause the processor to:
determining a temperature limit, the temperature limit being a maximum temperature expected to be reached by the brake upon the occurrence of the future aborted takeoff event.
14. The non-transitory computer readable storage medium of claim 13, wherein the instructions, when executed by a processor, cause the processor to:
determining whether the projected mass of the brake is sufficient to execute the future aborted takeoff event by comparing the temperature limit to an upper temperature cutoff of the brake.
15. A method, comprising:
determining whether the aircraft wheel brakes are capable of performing a future rejected takeoff event, comprising:
and determining whether the estimated quality of the brake is enough to execute the future aborted takeoff event according to the aborted takeoff energy parameter and the set of brake parameters.
16. The method of claim 15, comprising:
determining a number of predicted future use cycles after which the predicted quality is expected to be insufficient to execute the future aborted takeoff event.
17. An apparatus comprising a processor configured to:
determining whether the aircraft wheel brakes are capable of performing a future rejected takeoff event, comprising:
and determining whether the estimated quality of the brake is enough to execute the future aborted takeoff event according to the aborted takeoff energy parameter and the set of brake parameters.
Technical Field
The invention relates to determining whether aircraft wheel brakes are capable of performing future rejected take-off events.
Background
Aircraft wheel brakes can experience wear and oxidation. The amount of wear of the brake can be checked and the brake can be visually inspected to identify signs of oxidation. If the amount of wear and/or oxidation has reached a certain level, the brake may be considered to require repair or replacement. In this case, the aircraft in question may not be able to gain permission to fly.
Disclosure of Invention
A first aspect of the invention provides a non-transitory computer-readable storage medium having instructions stored thereon, which when executed by a processor, cause the processor to: determining whether the aircraft wheel brakes are capable of performing a future rejected takeoff event includes determining whether the estimated quality of the brakes is sufficient to perform the future rejected takeoff event based on the rejected takeoff energy parameter and the set of brake parameters.
Optionally, the instructions, when executed by the processor, cause the processor to: determining a number of predicted future use cycles after which the predicted quality is expected to be insufficient to perform a future aborted takeoff event.
Optionally, the instructions, when executed by the processor, cause the processor to: a mass limit is determined that defines a minimum mass required to perform a future aborted takeoff event.
Optionally, the instructions, when executed by the processor, cause the processor to: a determination is made as to whether the predicted mass is sufficient to execute a future aborted takeoff event by comparing the predicted mass to the mass limit.
Optionally, the instructions, when executed by the processor, cause the processor to: the mass limit is determined using an amount of energy absorbed by the brake when performing a future rejected takeoff event determined based on characteristics of the brake.
Optionally, the instructions, when executed by the processor, cause the processor to: a number of predicted future use cycles that reduce the predicted quality to a quality limit is determined.
Optionally, the instructions, when executed by the processor, cause the processor to: a first notification is issued if the projected quality is determined to be sufficient to execute a future aborted takeoff event.
Optionally, the instructions, when executed by the processor, cause the processor to: if it is determined that the predicted quality is insufficient to execute a future aborted takeoff event, the determination of whether the brake is capable of executing the future aborted takeoff event is repeated.
Optionally, the determination is repeated using an updated aborted takeoff energy parameter determined based on the updated aircraft weight.
Optionally, the instructions, when executed by the processor, cause the processor to: in response to the updated aircraft weight meeting the aircraft weight criteria, a second notification is issued indicating that the brakes need to be repaired or replaced, and the repetition of the determination is ceased.
Optionally, the instructions, when executed by the processor, cause the processor to: the aborted takeoff energy parameter is determined based on a set of user input parameters.
Optionally, the set of brake parameters comprises an upper temperature cut-off of the brake.
Optionally, the instructions, when executed by the processor, cause the processor to: a temperature limit is determined that is the maximum temperature that the brake is expected to reach at the occurrence of a future rejected takeoff event.
Optionally, the instructions, when executed by the processor, cause the processor to: it is determined whether the estimated mass of the brake is sufficient to execute a future aborted takeoff event by comparing the temperature limit to an upper temperature cutoff of the brake.
A second aspect of the invention provides a method comprising: determining whether the aircraft wheel brakes are capable of performing a future rejected takeoff event includes determining whether the estimated quality of the brakes is sufficient to perform the future rejected takeoff event based on the rejected takeoff energy parameter and the set of brake parameters.
Optionally, the method according to the second aspect comprises: a number of predicted future use cycles is determined, after which the predicted quality is expected to be insufficient to perform a future aborted takeoff event.
A third aspect of the invention provides an apparatus comprising a processor configured to: determining whether the aircraft wheel brakes are capable of performing a future rejected takeoff event includes determining whether the estimated quality of the brakes is sufficient to perform the future rejected takeoff event based on the rejected takeoff energy parameter and the set of brake parameters.
Drawings
Embodiments of the invention will now be described, by way of example only, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic illustration of an aircraft on which an example of the invention may be deployed;
FIG. 2 is a schematic illustration of wheels of an aircraft landing gear and aircraft wheel brakes, according to an example;
FIG. 3 is a first flowchart of a first exemplary method of determining whether an aircraft wheel brake is capable of performing a future rejected takeoff event;
FIG. 4a is a second flowchart of a portion of a second exemplary method of determining whether aircraft wheel brakes are capable of performing a future rejected takeoff event;
FIG. 4b is a third flowchart of a portion of a second exemplary method of determining whether aircraft wheel brakes are capable of performing a future rejected takeoff event;
FIG. 5 is a schematic diagram of an exemplary computing device for performing the methods of the present invention.
FIG. 6 is a diagram showing the condition of aircraft wheel brakes according to the number of cycles of brake use, according to an example;
FIG. 7 is a flow chart of an exemplary method of determining a thermal oxidation state of a brake of an aircraft landing gear;
FIG. 8 is a flow chart of an exemplary method of determining a thermal oxidation state of a brake of an aircraft landing gear;
FIG. 9 is an exemplary graph illustrating temperature of the brake with respect to time;
FIG. 10 is an exemplary graph showing a thermal oxidation state of a stopper at a specific temperature with respect to time;
FIG. 11 is an exemplary flow chart of a method of determining an amount of brake wear according to an example; and
FIG. 12 is an exemplary flow chart of a method of predicting a number of good future use cycles for an aircraft brake according to an example.
Detailed Description
FIG. 1 is a simplified schematic diagram of an aircraft 100. The aircraft 100 includes a plurality of landing gear assemblies 102. The landing gear assembly 102 may include a main landing gear and a nose landing gear that may be extended during takeoff and landing. Each landing gear assembly 102 includes a wheel, such as wheel 104. The aircraft 100 also includes a computing system 106, the computing system 106 including one or more processors and one or more computer-readable storage media. The aircraft 100 also includes a set of sensors 108, which may include sensors for measuring environmental characteristics as well as sensors associated with various components of the aircraft 100 and measuring values of various physical properties of the respective components. Although the sensor 108 is represented by a single box in the schematic diagram of fig. 1, it will be understood that the sensor 108 may be positioned at various different locations on the aircraft 100. The aircraft 100 may also include a set of indication devices 110 for providing various indications relating to the aircraft 100 and environmental conditions. The pointing device may include a screen displaying text and/or graphics, a dial, a light indicator, an audible indicator that emits a sound providing an indication, and the like. The pointing device may be internal or external to the aircraft 100.
FIG. 2 is a simplified schematic of an aircraft wheel brake 200 (hereinafter "brake" 200) associated with wheel 104 of aircraft 100. Each wheel of aircraft 100 may have a brake, such as brake 200, associated therewith. The brake actuator 200 applies a braking force to suppress rotation of the wheel 104. In this example, brake 200 includes a plurality of brake discs 202, and brake discs 202 include a pressure plate 204, a reaction plate 206, and a number of rotors and stators, such as rotor 208 and stator 210. In this example, the brake disc 202 includes a plurality of rotors and stators, and thus the brake assembly 200 is a multi-disc brake. In other examples, the brake assembly 200 may not be a multi-disc brake. It will be appreciated that the type of brakes used in aircraft landing gear depends on the characteristics of the aircraft in question, such as size, load-bearing capacity, etc.
As the aircraft 100 travels along the ground supported by the landing gear 102, the rotor rotates with the wheel 104, while the stator, the pressure plate 204, and the reaction plate 206 do not rotate with the wheel 104. When the brakes are applied, pressure plate 204 is urged toward reaction plate 206 such that brake discs 202 contact each other (as shown in block 212 of FIG. 2) and friction acts to dampen the rotational movement of the rotor, thereby generating a braking force to reduce the speed of aircraft 100. The brake 200 may be hydraulically actuated or electrically actuated.
Any one or more of the rotor, stator, platen 204, and reaction plate 206 may be constructed of a carbon-carbon (CC) composite. A brake comprising a brake disc composed of a CC composite may be referred to as a carbon brake. For example, the brake disc 202 may be constructed of a graphite matrix reinforced with carbon fibers.
The brake 200 may be provided with a brake wear sensor 216 (described in further detail below). The brake 200 may also be provided with a temperature sensor 218. The temperature sensor 218 may be disposed in thermal contact with one of the brake discs. In the example of fig. 2, temperature sensor 218 is disposed on stator 210. In this example, the stator 210 is a brake disc that may reach the highest temperature. Temperature sensor 218 may be any type of temperature sensor suitable for use in an aircraft brake assembly. For example, the temperature sensor 218 may operate properly within a range of temperatures that the brake disc 202 may reach. For example, the temperature sensor 218 may be a thermocouple, a Surface Acoustic Wave (SAW) sensor, an eddy current sensor, a resistive thermal sensor, a strain gauge, or the like. If a temperature sensor is provided on a portion of the brake 200 other than one of the brake discs 202, an indication of the relationship between the temperature measured by the temperature sensor and the temperature of the brake disc 202 may be used to determine the temperature of the brake disc 202. In some examples, the relationship indication may be determined experimentally. In some examples, the relationship indication may be determined using a thermal model of the brake.
During use, the brake disc 202 may experience oxidation. During the oxidation reaction, the oxygen reacts with the carbon of the brake disc 202, causing carbon atoms to be removed from the brake disc 202 with the generated carbon dioxide and/or carbon monoxide, causing a mass loss per unit volume of the disc brake 202. The oxidation state/level of the brake 200 may be expressed as an amount of mass lost due to oxidation.
The brake disc 202 may be oxidized via catalytic oxidation or thermal oxidation. Catalytic oxidation may occur when the oxidation reaction is assisted by the action of a catalyst. For example, alkali metals are known catalysts for the oxidation of CC complexes. Catalytic oxidation may be involved in areas of relatively high salinity with air. Catalytic oxidation may also be involved at airports where runway deicers including alkali metal salts are used. Thermal oxidation of the brake disc 202 may occur if the brake disc 202 reaches high temperatures due to friction during use. This is because when brakes 200 are applied to reduce the speed of aircraft 100, some of the kinetic energy of aircraft 100 is absorbed into brakes 200 as heat that raises their temperature. In this example, the components of the brake 200 (i.e., the brake disc 202) that are composed of the CC composite undergo oxidation. However, the present disclosure hereinafter refers to this as the oxidation state of the brake 200 only.
Furthermore, the brake disc 202 may experience wear due to friction during braking. For example, when a given brake disc is in contact with other brake discs, material of the surface of the given brake disc may be lost due to friction during braking. The wear may cause the length L (shown in fig. 2) of the brake disc 202 to decrease. The measured wear value may be used to determine the wear state of the brake 200. The measured wear value may be a measured length associated with the brake 200. For example, the measured wear value may be the length L of the brake disc 202 or a length from which the length L may be derived. The measured wear value provides an indication of the change in length L and hence the amount of brake wear. Thus, wear may be expressed as a reduction in the length of the brake disc 202. Wear and oxidation may cause a reduction in the mass of the brake 200. In this example, the brake disc 202 is subject to wear. However, the present disclosure will hereinafter be referred to simply as the wear state of the brake 200.
The condition of the brake disc 202 may decline over time due to use. A pre-flight check may be performed to check various aspects of the aircraft 100 to ensure safe flight. The check may be performed in a variety of different ways. For example, a pilot of the aircraft 100 may obtain various indications related to the aircraft (e.g., using a computer system) prior to flight. For example, ground crew may perform a pre-flight check prior to flight. The condition of brakes of aircraft 100, such as brake 200, may be checked. In prior art examples, the brake 200 may be visually inspected to identify oxidation signs, and an indication of the amount of brake wear may be obtained (e.g., by inspecting wear pins described below). Oxidation and brake wear will be discussed in further detail below.
If it is found that the condition of brake 200 has dropped beyond a certain level (e.g., indicating a given amount of brake wear, and or oxidation becoming visually apparent), brake 200 may be deemed to require repair, or replacement of the entire brake 200 or a portion thereof. Thus, the aircraft 100 may not be allowed to begin flying until maintenance or replacement is performed.
A brake wear threshold may be specified for brake 200. For example, the brake wear threshold may be specified by the manufacturer of the brake 200. The brake wear threshold may be related to a value of the length L of the brake disc 202. When the length L is reduced to the brake wear threshold, the brake 200 may be deemed to require repair or replacement. The brake wear threshold may be a conservative threshold based on operating conditions under worst case scenarios. However, even when the length L has reached the brake wear threshold, the brake disc 202 may not be fully worn. For example, the brake disc 202 may be of sufficient length and the brake 200 may be of sufficient mass for safe use, depending on operating conditions. For example, brake 200 may be able to safely be used for any potential brake application under prevailing operating conditions despite the brake wear threshold being reached. In such an example, it may not be necessary to perform the pre-flight service discussed with respect to brakes 200.
For example, the brake 200 may be capable of performing future aborted takeoff events for certain operating conditions. A break-off takeoff event requires severe braking to abort the takeoff and can be performed at high speeds. The brake 200 may be considered safe to use if it is capable of performing a rejected takeoff event. In the following example, a future aborted takeoff event involves aborting the takeoff at a speed referred to as the decision speed (V1). The rules require that the aircraft be able to perform a aborted takeoff at any time before reaching the speed V1 for that aircraft and stop before the end of the runway. Above the V1 speed, takeoff should no longer be aborted (e.g., even if the engine fails or another problem arises). This is because, for example, a aborted takeoff event performed in excess of V1 may cause aircraft 100 to overrun the runway and cause and/or suffer serious damage.
Brake wear and the amount of oxidation affects the quality of the brake disc 202 undergoing oxidation and wear. However, only the mass of the brake 200 is referred to hereinafter. The quality of the brake 200 may affect its performance. Although mass is lost by reaching a specified brake wear threshold, the brake 200 may be of sufficient mass to be safely used under given operating conditions. For example, the brake 200 may be of sufficient quality to perform a future aborted takeoff event.
Fig. 3 is a flow chart of a method 300. A non-transitory computer-readable storage medium (hereinafter storage medium) having stored thereon instructions, which when executed by a processor, cause the processor to perform the method 300, may be provided. Method 300 is used to determine whether brake 200 is capable of performing a future aborted takeoff event. At block 302, it is determined whether the projected mass of the brake 200 is sufficient to execute a future rejected takeoff event based on the rejected takeoff energy parameter and the set of brake parameters.
The aborted takeoff energy parameter may indicate an amount of kinetic energy that the aircraft 100 will need to lose to perform a future aborted takeoff event. As discussed, the future aborted takeoff event is an aborted takeoff when the aircraft 100 is moving at a speed V1. The V1 speed of aircraft 100 may depend on the performance characteristics of aircraft 100, environmental conditions, runway length, and weight of aircraft 100, which are examples of operating conditions. The performance characteristics of the aircraft 100 may include thrust settings, pull-up speed (which is defined as the speed at which the pilot can begin to apply control inputs to pitch the aircraft nose up and then off the ground), and so forth. The environmental conditions may include conditions such as altitude, temperature, wind power and direction, the particular characteristics of the runway in question, and precipitation levels.
The brake parameter set may include an upper temperature cutoff for the brake 200. The upper temperature cutoff may be a temperature at which the performance of brake 200 is degraded, a temperature at which fuses of respective wheels 104 melt to relieve stress, a temperature at which brake discs 202 undergo thermal oxidation, a temperature at which respective shafts are thermally damaged, and the like. It may be desirable for the temperature of brake 200 not to exceed the upper temperature cutoff. The brake parameter set may also include parameters indicative of physical properties of the brake 200. For example, the brake parameter set may include the specific heat capacity of the brake 200. The specific heat capacity of brake 200 may be a function of some variable such as temperature.
The estimated mass of brake 200 may be an estimated current mass of brake 200 or an estimated future mass of brake 200. In examples where the future aborted takeoff events are those that may potentially occur during the next flight, the estimated current mass of the brakes 200 may be used. In examples where the future aborted takeoff events are those that may potentially occur after multiple future flights have occurred, the projected future mass of the brakes 200 may be used. The predicted future mass of the brake may be determined based on the predicted current mass.
The estimated mass may be determined based on an estimated oxidation state of brake 200 and a wear state of brake 200. As discussed, oxidation and wear results in a loss of mass of the brake 200. The estimated oxidation state of brake 200 may be expressed as an amount of mass lost from brake 200 due to oxidation. As discussed, the wear state of the brake 200 may be represented as a reduction in the length L of the brake disc 202. Given the density (which may take into account the oxidation level) and surface area of the brake disc 202, the amount of mass lost due to brake wear may be determined from the reduction in length. The amount of mass lost due to oxidation and the amount of mass lost due to wear may be subtracted from the original mass of brake 200 (i.e., the mass of brake 200 when it is new and not in use) to estimate the mass of brake 200.
In examples where the estimated current mass of brake 200 is to be determined, the estimated current oxidation state and the current wear state may be used. In examples where the predicted future quality of the brake 200 is to be determined, a predicted future oxidation state and a predicted wear state, which is a predicted future wear state, may be used. The manner in which the estimated current oxidation state and the estimated future oxidation state of brake 200 may be determined is described in further detail below. Furthermore, the manner in which the wear state may be measured and future wear states may be predicted will be described in further detail below.
Further details of how to determine whether the estimated mass of the brakes is sufficient to perform a future aborted takeoff event will be described below. Fig. 4a and 4b are a flow diagram illustrating a method 400 of acts that may be performed as part of the method 300. The method 400 also includes actions other than determining whether the estimated mass of the brakes is sufficient to perform a future aborted takeoff event. The blocks of method 400 may be performed in a variety of different orders and/or certain blocks may be omitted, as long as it is determined whether brake 200 is capable of performing a rejected takeoff event, as may be practical. The non-transitory computer readable storage medium may store instructions that, when executed by a processor, cause the processor to perform all or part of the method 400.
At block 402 of the method 400, a decision velocity V1 is determined. As discussed, the V1 speed may depend on the performance characteristics of the aircraft 100, environmental conditions, runway length, and weight of the aircraft 100 as examples of operating conditions. For example, the storage medium may store instructions that, when executed by the processor, cause the processor to determine the V1 velocity using these factors. Information regarding these factors may be received by the processor from sensors 108 of the aircraft 100, retrieved from a computer-readable storage medium, and/or input by a user of the processor.
In some examples, the V1 speed may be determined using a maximum takeoff weight, which may be the maximum weight a given aircraft 100 has while flying. In some examples, the measured aircraft weight (i.e., the actual current weight of the aircraft 100) may be used. In some examples, an estimated aircraft weight may be used. For example, the aircraft weight may be estimated by summing known empty weight, fuel weight estimate, passenger and crew weight estimates, and baggage weight estimate for aircraft 100. In some examples, the aircraft weight may be estimated by adding a proportion of the weight capacity of the aircraft (based on the number of passengers on the flight, etc.) to the known empty weight. In the following discussion, simply referred to as aircraft weight. As will be described below, the method 400 may be repeated (in an iterative manner) using different operating conditions. In some examples, method 400 may be performed using a measured (or estimated) aircraft weight, and method 400 may be repeated using an updated aircraft weight value, which is an updated value input into method 400 for the purpose of repeating method 400.
At block 404, a aborted takeoff energy parameter may be determined based on the aircraft weight and the speed V1. In some examples, the abort takeoff energy parameter may be determined based on a set of user input parameters. For example, a user may input a set of parameters indicative of one or more operating conditions under which blocks 402 and 404 are performed. Thus, a user may perform the methods described herein for a variety of different operating conditions.
At 406 of the method 400, a mass limit is determined that defines a minimum mass required to perform a future aborted takeoff event (i.e., a minimum mass of the brake 200). The mass limit may be determined using the amount of energy that brake 200 will absorb when performing a future rejected takeoff event. It should be noted that all of the brakes of aircraft 100 applied during a future rejected takeoff event may absorb some of the kinetic energy of aircraft 100. The mass limit is determined using the amount of energy that the particular brake for which method 400 is performed will absorb. Thus, the amount of energy that brake 200 will absorb (i.e., the proportion of the total kinetic energy of aircraft 100 that must be lost during the rejected takeoff event) is determined and used to determine the mass limit.
In some examples, the amount of energy that brake 200 will absorb may be determined based on the gain characteristics of brake 200. The gain characteristic of the actuator 200 may be indicative of certain physical properties of the actuator 200. For example, the gain characteristic may indicate the amount of energy that the brake 200 is expected to absorb for a given applied force. Each brake of the aircraft 100 that may be applied during a future aborted takeoff event may have its own gain characteristic. The amount of energy that must be lost to bring the aircraft 100 to a stop during a future takeoff blackout event may be divided among the brakes to be applied in consideration of various gain characteristics.
In the context of a future aborted takeoff event, the maximum force used to apply the brakes may be used. For example, given a maximum brake effort, the amount of energy each brake expected to be applied will absorb may be considered for the amount of time required for aircraft 100 to stop. It is thus possible to determine the amount of total energy that must be lost by aircraft 100 that will be absorbed by brakes 200. The maximum force may depend on the force that can be provided by the hydraulic/electric actuation system of the brakes 200 when the pilot forcibly applies all the brakes to perform a future aborted takeoff event. In some simpler examples, the total energy that aircraft 100 must lose during a future takeoff interrupted event (as indicated by the takeoff interrupted energy parameter) may be divided by the number of brakes of aircraft 100 to be applied to estimate the amount of energy that will be absorbed by brakes 200 for which the method is performed. It should be noted, however, that this approach will not take into account the differences between the various brakes. In some examples, in determining the energy to be absorbed by brakes 200, it may be assumed that there is a lack of braking on one of the wheels of aircraft 100 (e.g., to account for worst case scenarios).
As discussed, the brake parameter set may include an upper temperature cutoff and a specific heat capacity of the brake 200. The mass limit of brake 200 may be determined using the amount of energy brake 200 will absorb and the specific heat capacity of brake 200 such that brake 200 does not exceed the upper temperature cutoff. The mass limit may also take into account the physical size and density of the brake disc 202 (e.g., using the estimated oxidation state of the brake 200), such that the mass limit is related to the minimum size and density that will allow safe operation of the brake 200.
A temperature limit may be determined that is the maximum temperature that brake 200 is expected to reach when a future rejected takeoff event occurs. In the example of method 400, a temperature limit is determined at block 408. For example, the temperature may be determined using the amount of energy that brake 200 will absorb, the estimated mass and specific heat capacity of brake 200.
At block 410, it is determined whether the estimated mass of the brake 200 is sufficient to perform a future aborted takeoff event.
In some examples, whether the predicted quality is sufficient may be determined by comparing the predicted quality to a quality limit. For example, if the predicted quality is less than the quality limit, it may be determined that the predicted quality is insufficient to execute a future aborted takeoff event. On the other hand, if the predicted mass is greater than the mass limit, it may be determined that the predicted mass is sufficient to perform a future aborted takeoff event.
In some examples, whether the estimated quality is sufficient may be determined by comparing a temperature limit to an upper temperature cutoff. For example, if the temperature limit is less than the upper temperature cutoff, it may be determined that the predicted mass is sufficient to perform a future aborted takeoff event (because the brake 200 is not expected to become too hot). On the other hand, if the temperature limit is greater than the upper temperature cutoff, it may be determined that the predicted quality is insufficient to execute a future aborted takeoff event.
In examples where the future aborted takeoff events are those that may potentially occur during the next flight, the estimated mass used may be an estimated current mass of the brake 200 determined based on an estimated current oxidation state of the brake 200 and a current wear state of the brake 200. In examples where the future aborted takeoff events are those that may potentially occur after a given number of flights, the estimated future quality may be determined based on an estimated future oxidation state after the given number of flights and an estimated future wear state after the given number of flights.
Regardless of the result of this determination, the method proceeds to block 412. Block 412 is an optional block that may be performed and is described in further detail below. At block 412 of the method 400, a number of predicted future use cycles of the brake 200 is determined after which it is expected that the predicted quality will be insufficient to execute a future aborted takeoff event. The number of predicted future use cycles after which the predicted quality is expected to be insufficient is referred to hereinafter as the predicted brake quality cycle. The life cycle of brake 200 may be the time from when aircraft 100 with brake 200 installed thereon is at a gate prior to flight to when aircraft 100 is at a gate after flight. For example, a period of use includes all uses of brakes 200 in connection with a respective flight undertaken by aircraft 100. Thus, as used herein, a period of use relates to a complete flight of the aircraft 100. The predicted future use period may be a use period of brake 200 that has not yet occurred.
The predicted brake mass period may be determined by comparing the value of the predicted future mass to a mass limit. It should be noted that in the example where the future aborted takeoff event is associated with the next flight and it is determined that the estimated current mass is insufficient, the estimated brake mass period is zero for the operating condition in question (e.g., aircraft weight). In an example, where a future aborted takeoff event is associated with the next flight and the estimated current mass is determined to be sufficient, the estimated brake mass period is at least one.
The values of the predicted future mass of the brake 200 for each predicted future use period may be compared in turn to the mass limit. For example, the estimated future quality for the first given estimated future use period may be compared to a quality limit. If the estimated future quality for the first given estimated future use period is greater than the quality limit, the estimated future quality for the second given estimated future use period may be compared to the quality limit. The second given predicted future use period may be the next period immediately following the first given predicted future use period. The comparisons may be continued in turn in this manner until the predicted future quality for a particular predicted future use period is less than the quality limit. The predicted brake mass period may be determined as a number of predicted future use periods that have not occurred that is one less than the particular predicted future use period when the predicted future mass falls below the mass limit. In this way, an indication of when brake 200 needs servicing or replacement may be provided. Advantageously, such a determination may allow planning of maintenance and replacement work while avoiding flight delays due to finding a problem with the brakes 200 prior to flight.
A first notification may be issued if the projected quality is determined to be sufficient to perform a future aborted takeoff event. Upon the determination of block 410 being made using prevailing operating conditions, such as measured aircraft weight, the first notification may indicate that the estimated mass is sufficient to perform a future aborted takeoff event for the prevailing operating conditions (e.g., measured aircraft weight). The content of the first notification may vary depending on the operating conditions for which the determination of block 410 is made, as will be described below. In method 400, if it is determined that the projected quality is sufficient, method 400 proceeds to block 414. At block 414, a first notification is issued. If it is determined that the predicted quality is insufficient to perform a future aborted takeoff event, the determination of whether the brake 200 is capable of performing the future aborted takeoff event may be repeated. For example, the determination may be repeated using the updated operating conditions. If it is determined at block 410 that the estimated quality is insufficient, the method 400 proceeds to block 416. At block 416, an updated value of the aircraft weight is input into the method for the purpose of repeating the determination of whether the brakes are capable of performing a future aborted takeoff event. It should be noted that the updated value for aircraft weight is independent of the actual prevailing weight of aircraft 100, and is simply the value that is input into method 400 to repeat the determination to check whether brake 200 is capable of performing a future aborted takeoff event for a different operating condition (e.g., a different aircraft weight). For example, the updated value may be lower than the measured (or estimated) aircraft weight. For example, the updated value may be a given amount below the measured (or estimated) aircraft weight. In some examples, the given amount may be an estimated weight of a passenger and their luggage. An example of a given amount is 100 kg. The updated value of the aircraft weight input for the purpose of repeating the determination may be a given amount lower than the previous value each time the determination is repeated. In this way, the determination may be iterated for various different values of aircraft weight.
In response to the updated value of the aircraft weight satisfying the aircraft weight criterion, a second notification may be issued indicating that brake 200 needs to be repaired or replaced, and repetition of the determination may be stopped. In the example of method 400, at block 418, it is determined whether the updated value of the aircraft weight meets the aircraft weight criteria. The aircraft weight criterion may simply be, for example, an aircraft weight lower limit below which it is undesirable and/or flight cannot be initiated.
If the aircraft weight criteria are met, method 400 proceeds to block 402. Thus, if a determination is made that the estimated mass is insufficient using a different operating condition (in this case, an updated value for the aircraft weight), the determination is repeated. In repeating block 402, a decision velocity V1 is determined based on the updated value of the aircraft weight. Similarly, in repeating block 404, an updated aborted takeoff energy parameter is determined based on the updated value of the aircraft weight. It should be noted that for lower aircraft weight values, the aborted takeoff energy parameter may indicate that the aircraft 100 will need to lose a lower amount of energy to perform a future aborted takeoff event. The method 400 may continue to block 410 as described above. If it is determined at block 410 that the predicted mass is sufficient to perform a future aborted takeoff event (an updated value for the aircraft weight), the method proceeds to block 414 (optional block 412 may also be performed). At block 414, a first notification is issued. In this case, the first notification indicates that, while the estimated mass for the measured aircraft weight will not be sufficient to perform a future aborted takeoff event, the estimated mass will be sufficient to perform the future aborted takeoff event for the updated value of the aircraft weight. In response to the first notification, the pilot and/or other flight crew associated with the aircraft 100 may elect to change the actual weight of the aircraft 100 (e.g., by unloading luggage, etc.) in order to continue flying in a safe manner.
Thus, in the example of method 400, by repeating this determination, an operating condition may be found in which brake 200 is capable of performing a rejected takeoff event, i.e., the weight of the aircraft in this example.
In the example of method 400, if it is determined at block 418 that the aircraft weight criteria are not met, method 400 proceeds to block 420 shown in FIG. 4 b. (note that the transition from the block in FIG. 4a to the block in FIG. 4b is indicated by block "A"). It should be noted that method 400 proceeds to block 420 when it has been determined that the estimated mass of brake 200 is insufficient to perform a future aborted takeoff event for any of the determined aircraft weight values used to perform method 400.
At block 420, a second notification is issued. At block 422, repetition of the determination as to whether the brakes are capable of performing future aborted takeoff events is stopped. This may occur in an example where the processor performing the method has means to communicate with the brake system of the aircraft 100.
The storage medium described may be used with a processor of a computing device. For example, all or part of the methods described herein may be performed by one or more processors of the computing system 106 of the aircraft 100. In some examples, one or more processors of a computing device at a maintenance control center associated with aircraft 100 may perform all or part of the described methods. In some examples, one or more processors of a computing device of an electronic flight bag used by a crew of aircraft 100 may perform all or part of the described methods. Fig. 5 is a simplified schematic diagram of an apparatus 500, which is a computing device for performing all or part of the methods described herein. The apparatus 500 includes a processor 502 and a storage medium 504. The storage medium 504 may be a storage medium as described, and thus may store instructions that, when executed by the processor 502, cause the processor 502 to perform all or part of the methods described herein.
Other methods that may be performed based on instructions stored in the storage medium 504 are described below.
The manner in which the wear state of brake 200 may be determined and the predicted wear state is described below. In the case where the brake 200 is electrically actuated and controlled by an electronic brake controller, the measured wear value may be the length L of the brake disc 202 measured by the electronic brake controller. The electronic brake controller may, for example, control the position of the platen 204 relative to the reaction plate 206 and thus be able to measure the length L.
In the case where the brake 200 is hydraulically actuated, a brake wear sensor 216 configured to measure a wear value may be provided. Brake wear sensor 216 may include a Linear Variable Differential Transformer (LVDT) sensor or a hall effect sensor configured to measure linear displacement of components of brake 200. For example, such a brake wear sensor 216 may measure the linear displacement of the pressure plate 204 when the brake 200 is fully applied, and may derive the length L from the measured linear displacement.
In some examples, the measured wear value may be a remaining length of a wear pin (not shown) associated with brake 200, for example. The wear pin may be a component that provides an indication of a change in the length L of the brake disc 202. For example, a decrease in the remaining length of the wear pin may correspond to a decrease in the length L of the brake disc 202. The remaining length of the wear pin may be the length of the wear pin extending from the components of the brake 200. For example, the remaining length of the wear pin may be a wear pin length extending from a surface of a piston housing of brake 200 or another surface of a housing of brake 200.
The wear pin may move with the brake disc 202 and relative to the surface used to measure its remaining length. The wear sensor 216 may be a sensor fixed relative to a surface used to measure the remaining length of the wear pin. Such a sensor may measure the position of the wear pin relative to the surface and may therefore measure the change in the remaining length of the wear pin.
The estimated wear state may be an estimated wear state that brake 200 will be in after a future use period of brake 200 has occurred. The wear state of the brake 200 may be represented by a measured wear value, such as the remaining length of the wear pin measured with the brake wear sensor 216. As described, as the brake 200 becomes more worn, the length L of the brake disc 202 decreases. Thus, the measured wear value as defined herein decreases as the period of use occurs. The estimated wear state may be represented by an estimated wear value, which may be an estimated length associated with brake 200, such as an estimated remaining length of a wear pin. In the examples described below, the actual and predicted wear states are represented by measured and predicted wear values that decrease as the brake 200 becomes more worn.
The estimated wear state may be determined based on the wear state of brake 200. For example, a wear relationship between the wear state of the brake 200 and the number of usage cycles may be determined. The estimated wear state may be determined based on the wear relationship as described below. The wear relationship may be determined based on one or more of the measured wear values. For example, the wear state may be measured for the number of usage cycles that occur and considered for the total number of usage cycles of brake 200 that have occurred. In the examples described below, the wear state is measured for each usage cycle that occurs.
Fig. 6 is a graph showing a wear state and an estimated wear state as a function of the number of usage cycles of the brake 200 according to an example. The vertical axis of the graph of fig. 6 represents wear values (measured or estimated), while the horizontal axis represents the number of usage cycles. In this example, one hundred cycles of use have occurred (i.e., aircraft 100 has made 100 flights with brakes 200 installed). Thus, for each usage cycle that has occurred, the value of the wear state measured by the brake wear sensor 216 is to the left of the line 602. Line 602 is a vertical line that intersects the horizontal axis at one hundred cycles of use. For convenience, the various values of the wear state are not shown. But rather shows a solid line 604a fitted to the values of the wear state.
The solid line 604a may be determined using any known data fitting method. For example, a simple linear regression analysis may be used to determine the solid line 604 a. Examples of other methods of fitting the data include least squares, least absolute residual, binary fitting, and the like. It should be appreciated that any suitable data fitting method may be used.
In this example, a linear function is used to fit the values of the wear state to produce a solid line 604a, which is a straight line. However, in some examples, different functions may be used. For example, a polynomial function, an exponential function, or another function that can describe the reduction of the wear state value according to the period that can be used may be used.
As described, a linear function is used in the example of fig. 6. The linear function can be expressed according to the following equation 1:
y＝mx+c (1)
in the above equation (1), y represents a value of a wear state, x represents the number of usage cycles, m represents a brake wear amount per usage cycle (i.e., a gradient of a linear fit to the value of the wear state), and c represents a wear state when no usage cycle occurs (i.e., a value of a wear value measured when no usage cycle occurs, which may be, for example, a starting length of a wear pin).
By fitting the values of the wear state, unknown parameter values in the fitting function used can be determined. In this example, the value of m may be determined by fitting the values of the wear state using equation (1). The function used to fit the wear state values and the parameters determined from the fit represent the wear relationship.
To determine the estimated wear state (i.e., the estimated wear value in this example) after a given number of cycles of use have occurred, the given number of cycles of use may be substituted in equation (1) as the value of parameter x. Then, using the values of the parameters known from the fitting on the right hand side of equation (1), the estimated wear state after a given number of usage cycles (i.e., the value of the parameter y when x equals the given number of usage cycles) can be calculated. In fig. 6, a broken line 604b represents the value of the estimated wear state according to the number of usage cycles. In other words, a line (i.e., the dashed line 604b resulting from the fitted function and the determined parameters) may be determined for a value of the number of usage cycles that is greater than the number of actually occurring usage cycles. In this example, the corresponding number of estimated wear states for a period of use is the value falling on dashed line 604 b.
Fig. 7 outlines a method 700 of determining the thermal oxidation state of a brake (e.g., brake assembly 200) of aircraft landing gear assembly 102, according to an embodiment of the invention. Method 700 involves using a thermal oxidation model to determine the thermal oxidation state of brake assembly 200 after a braking event based on an initial thermal oxidation state (which is also referred to as an initial thermal oxidation level) prior to the braking event and a temperature profile of the brake versus time. The determined thermal oxidation state of brake assembly 200 after the braking event may be referred to as a renewed thermal oxidation state. This is because the thermal oxidation state of brake assembly 200 after a braking event takes into account the change in the initial thermal oxidation state due to the braking event.
A braking event is an event related to the application of the brake assembly 200. For example, a braking event may include one or more applications of brake assembly 200 to slow or stop aircraft 100. In some examples, the braking event may be a portion of time during which brake assembly 200 is continuously applied. The temperature of brake assembly 200 may increase whenever brake assembly 200 is applied. This is because when brake assembly 200 is applied to reduce the speed of aircraft 100, some of the kinetic energy of aircraft 100 is absorbed into brake assembly 200 as heat causing its temperature to increase. Accordingly, whether brake assembly 200 has been applied may be determined based on a change in temperature of brake assembly 200.
At block 702 of method 700, a temperature profile and an initial thermal oxidation state of brake assembly 200 are input. As explained above, the temperature profile indicates the change in temperature over time. The input temperature profile may be related to, for example, the life cycle of the aircraft 100. For example, the temperature profile may be for the entire life cycle of the aircraft 100, such as the time from when the aircraft 100 is at a check-in port before flight to when the aircraft 100 is at an arrival port after flight. In particular, the temperature profile may indicate the change in temperature over time for all braking events occurring during a cycle. In other examples, the temperature profile may not be for the entire life cycle of the aircraft 100. For example, the temperature profile may be for a single braking event or a portion of a cycle having many braking events. In some examples, multiple temperature profiles pertaining to a particular use period may be used to determine the thermal oxidation state of brake assembly 200 after the use period.
The temperature profile may for example be related to the period of use that has taken place. In other words, the temperature profile may include actual data from temperature sensor 218 of aircraft 100 during a previous use period. In such an example, the temperature profile is correlated to the real data. In another aspect, in some examples, the temperature profile may be an estimated temperature profile of an estimated future use period of the aircraft 100. In this scenario, the braking event may be an estimated future braking event.
The temperature profile may be obtained (in an example where the temperature profile includes actual data) from a temperature sensor 218 (see fig. 2) associated with the brake 200. The temperature sensor 218 may be disposed in thermal contact with one of the brake discs. In the example of fig. 2, temperature sensor 218 is disposed on stator 210. In this example, the stator 210 is a brake disc that may reach the highest temperature. Temperature sensor 218 may be any type of temperature sensor suitable for use in an aircraft brake assembly. For example, the temperature sensor 218 may operate properly within a range of temperatures that the brake disc 202 may reach. For example, the temperature sensor 218 may be a thermocouple, a Surface Acoustic Wave (SAW) sensor, an eddy current sensor, a resistive thermal sensor, a strain gauge, or the like. If a temperature sensor is provided on a portion of the brake 200 other than one of the brake discs 202, an indication of the relationship between the temperature measured by the temperature sensor and the temperature of the brake disc 202 may be used to determine the temperature of the brake disc 202. In some examples, the relationship indication may be determined experimentally. In some examples, the relationship indication may be determined using a thermal model of the brake.
Temperature sensor 218 may measure the temperature of stator 210 at given measurement intervals during a period of time in which brake 200 is expected to be used. The length of a given measurement interval may be different. A given measurement interval may be regular, irregular, or both regular and irregular over a period of time. For example, temperature sensor 218 may measure temperature such that a temperature versus time curve of stator 210 is captured. In other words, temperature sensor 218 measures the temperature of stator 210 at given measurement intervals so that temperature information as a function of time is captured. For example, a processor of computing system 106 may control the operation of temperature sensor 218 based on instructions stored in a computer-readable storage medium of computing system 106. The temperature measurements captured by temperature sensor 218 may be stored, for example, in a storage medium of computing system 106 along with associated time data.
The initial thermal oxidation state of brake assembly 200 is the thermal oxidation state of brake assembly 200 prior to a braking event for which an updated thermal oxidation state is to be determined. For example, for a new brake assembly 200 installed in aircraft 100, the initial oxidation state may indicate no oxidation. In some examples, the initial oxidation state of newly installed brake assembly 200 may be set by aircraft maintenance personnel at installation, and may indicate no or some oxidation as assessed by the personnel performing the installation. In examples where brake assembly 200 is not a new brake assembly, the initial oxidation state may be the oxidation state calculated the last time the example of method 700 was performed. In some examples, no new brakes or brake components may be installed on the aircraft 100. If temperature profile information is available for all previous braking events involving the brake or brake component, the thermal oxidation state at installation can be determined using method 700 using the available temperature profile information or by other methods disclosed herein.
At block 704 of method 700, a thermal oxidation state (updated thermal oxidation state) following the braking event is determined using a thermal oxidation model. For example, a thermal oxidation model is applied based on the input temperature profile and the initial thermal oxidation state of brake assembly 200. The thermal oxidation model indicates, for example, how the thermal oxidation state is expected to change over time for various temperatures starting from the initial thermal oxidation state. The thermal oxidation model is an evolution model of the thermal oxidation of the brake. Which thermal oxidation state to use may depend, for example, on the initial thermal oxidation state. Details and selection of a suitable thermal oxidation model are further described below. In some examples, method 700 may be performed on-the-fly during a period of use of aircraft 100. Where method 700 is performed on-the-fly (i.e., in real-time or near real-time), the temperature profile used may be from temperature data that has been currently acquired by temperature sensor 218, for example. Accordingly, at block 704, it is determined how the oxidation state changes due to the temperature increase associated with the braking event in question, starting from the initial oxidation state.
After the renewed thermal oxidation state is determined, the initial thermal oxidation state may be set to the renewed thermal oxidation state. In this way, the initial thermal oxidation state is maintained in synchronism with all previous braking events. In examples where the temperature profile relates to more than one braking event, method 700 may be performed again to determine an updated thermal oxidation state after a subsequent braking event. Updating the initial thermal oxidation state in this manner may ensure that the initial thermal oxidation state for a subsequent braking event takes into account all previous braking events.
In the example of a temperature profile for an entire use period of the aircraft 100, the method 700 may be performed to determine a corresponding updated thermal oxidation state after each braking event during the use period. It should be appreciated that this process may be performed sequentially in relation to the temporal sequence of braking events. This is so that the determination of the updated thermal oxidation state for each braking event is made from a starting point (initial thermal oxidation state) that takes into account all previous braking events.
In method 700, for example, an updated thermal oxidation state following a braking event may be determined using an appropriate thermal oxidation model based on a high temperature interval, an initial thermal oxidation state, and a thermal oxidation rate parameter.
Fig. 8 is a flow diagram of a method 800 illustrating acts that may be performed as part of method 700. For example, method 800 relates to a more specific example of block 704 of method 700. Block 802 is the same as block 702 of method 700, in which a temperature profile of the brake versus time and an initial thermal oxidation state of brake assembly 200 are entered. At block 804, the temperature profile is compared to a set of temperature standards. The set of temperature criteria may include a set of temperature thresholds. For example, the set of temperature criteria may include a first temperature threshold of 400 ℃ and a second temperature threshold of 750 ℃. In other examples, different temperature thresholds may be used depending on the physical properties of the brake assembly 200. The comparison of the temperature profiles can be carried out, for example, in chronological order of the temperature data contained in the temperature profiles. For example, a temperature value may be compared to the set of temperature thresholds, and then a next temperature value in time may be compared to the set of temperature thresholds.
In block 806, it is determined whether one or more temperature criteria are met. For example, if any temperature threshold is not exceeded, the method 800 ends. It should be appreciated that thermal oxidation of the CC compound of the brake disc 202 is the most significant process at high temperatures. Comparison of the temperature profile to a set of temperature thresholds therefore identifies high temperature events corresponding to braking events that may lead to thermal oxidation. As mentioned above, the braking event is, for example, an application of the brake assembly 200. However, a high temperature event is an event in which the temperature of the brake assembly exceeds at least one of the temperature thresholds due to a braking event. For example, if during a braking event (i.e., brake application), the temperature of the brake assembly 200 remains below all temperature thresholds, then no high temperature event occurs during the braking event. On the other hand, if the temperature of the brake components exceeds the temperature threshold during a braking event, the portion of the braking event that exceeds the temperature threshold may be referred to as a high temperature event. If more than one temperature threshold is exceeded, the high temperature event may be the portion of the braking event that exceeds the maximum temperature threshold.
The temperature threshold may be set based on the following temperatures: it is expected that a significant amount of thermal oxidation will occur above this temperature. Thus, if any temperature threshold is not exceeded, method 800 ends. This is because in this example, no braking event occurs that causes a sufficiently high temperature with respect to thermal oxidation. In such an example, the updated thermal oxidation state after the braking event may simply be set to the initial thermal oxidation state prior to the braking event in question.
On the other hand, if at least one of the temperature thresholds is exceeded, then at block 808 of method 800, a high temperature event corresponding to the braking event in question is identified. The high temperature event corresponds to a portion of the temperature profile above the highest of the exceeded temperature thresholds. This is because the portion of the temperature curve above the highest of the exceeded thresholds corresponds to the portion of the braking event that exceeds the highest temperature threshold. The identification of high temperature events is described with reference to fig. 9. FIG. 9 is a graph illustrating a portion of an example temperature profile. In the graph of fig. 9, the vertical axis represents the temperature of the brake assembly 200, and the horizontal axis represents time. In this example, curve portion 902 indicates that the temperature of brake assembly 200 exceeds first temperature threshold 904 and second temperature threshold 906. In this example, a high temperature event is identified as the portion of the curve 902 above the second temperature threshold 906 because the second temperature threshold 906 is the highest temperature threshold that is exceeded.
For a given time interval, the amount of thermal oxidation above second temperature threshold 906 may be significantly greater compared to thermal oxidation above first temperature threshold 904 but below second temperature threshold 906. Thus, in this example, the portion of the temperature curve below the second temperature threshold 906 is not considered. In other examples, the portion of the temperature curve between two temperature thresholds may be considered, for example, when using method 800 for instantaneous oxidation state monitoring as described further below. It should be understood that the graph of fig. 9 is merely an example illustration for illustrative purposes.
At block 810, the time interval occupied by the high temperature event is determined as the high temperature interval. As mentioned above, the updated thermal oxidation state may be determined based on (among other factors) the high temperature interval. In the example of fig. 9, the high temperature interval is determined as time interval 908.
At block 812, a high temperature event value for the brake assembly 200 is determined for the high temperature interval. The high temperature event value is a temperature value attributed to the high temperature event. In some examples, the high temperature event value is an average temperature during a high temperature interval. An alternative to the high temperature event value being the average temperature is described below in the context of instant oxidation monitoring.
At block 814, an oxidation rate parameter is calculated based on the high temperature event value and the physical property information of the brake. For example, the oxidation rate parameter of the thermal oxidation reaction may be determined based on the arrhenius formula as shown in the following formula 2:
in formula 2, k (T) is the thermal oxidation rate, A is the pre-constant, EAIs the activation energy of the carbon atoms of the CC composite component of the brake assembly 200, R is the universal gas constant and T is the temperature. In this example, for a particular high temperature event, the temperature T in equation 2 is set to the high temperature event value for purposes of block 814. In this example, the thermal oxidation rate k (t) is the oxidation parameter determined at block 814. Activation energy E AAnd the value of pre-pointing constant a may depend on the physical properties of the CC composition component of brake assembly 200 (brake disc 202 in this example). For example, the values of these parameters may depend on the density, porosity, manufacturing process, contaminants present in the CC composite structure, surface finish of the component, and surface coating of the brake assembly 200. Activation energy EAAnd the value of the pre-finger constant a may also vary depending on the high temperature event value and the initial thermal oxidation state. Thus, to determine the oxidation parameter, the activation energy E may be selected based on the physical properties of the brake assembly 200, the high temperature event value, and the initial thermal oxidation state prior to the braking event in questionAAnd a suitable value for the pre-finger constant a.
For example, activation energy EAMay be inversely related to temperature. Activation energy EAMay become lower at the following temperatures: at this temperature, oxygen molecules are able to penetrate the surface of the brake disc 202 and oxidation of the deeper carbon in the brake disc 202 may occur. For example, activation energy E may be experimentally determined for different initial amounts of thermal oxidation, temperatures, and physical properties of the brake under consideration prior to implementing method 800AAnd the combination of pre-finger factor A An appropriate value.
FIG. 10 is a graph of an example of the evolution over time of the thermal oxidation state of the brake discs of brake assembly 200 for a particular temperature. The vertical axis of the graph in fig. 10 represents the measurement result of the thermal oxidation indicated by the thermal oxidation state Ox. For example, the thermal oxidation state Ox may be a proportion of the mass of the brake assembly 200 lost due to thermal oxidation of the brake disc 202. Evolution curve 1002 shows how the proportion of mass lost due to thermal oxidation at a particular temperature increases over time. It should be noted that different evolution curves will indicate the variation of the thermal oxidation rate Ox with time for different temperature values.
In this example, the thermal oxidation state Ox varies over time below the thermal oxidation state level 1004 in a different manner than it does above the thermal oxidation state level 1004. In this example, the thermal oxidation state Ox (i.e., the mass lost due to thermal oxidation) is shown to increase non-linearly over time below the oxidation state level 1004 and to increase substantially linearly over time above the oxidation state level 1004. In this example, the thermal oxidation state increases at an acceleration rate over time until the thermal oxidation state level 1004 is reached. After reaching the thermal oxidation state level 1004, the rate of change of the thermal oxidation state Ox with time remains generally constant. For example, a portion of the graph of fig. 10 that is below the thermal oxidation state level 1004 may be considered a first thermal oxidation region, i.e., region 1, and a portion of the graph of fig. 10 that is above the thermal oxidation state level 1004 may be considered a second thermal oxidation region, i.e., region 2.
In some examples, activation energy E may be used based on in which thermal oxidation region brake assembly 200 is located as indicated by the initial thermal oxidation stateAAnd different values for pre-constant a.
At block 816, a thermal oxidation model is selected based on an initial thermal oxidation state prior to the braking event. The thermal oxidation model describes the evolution of the thermal oxidation state Ox of the brake assembly 200 for different temperature values. In case the initial thermal oxidation state is in the region 1, a thermal oxidation model describing the evolution of the thermal oxidation state Ox in the region 1 may be selected. In case the initial thermal oxidation state is in the region 2, a thermal oxidation model describing the evolution of the thermal oxidation state Ox in the region 2 may be selected. For example, a first thermal oxidation model, model 1, may be selected for region 1 and a second thermal oxidation model, model 2, may be selected for region 2. A model 1 for the region 1 describing the nonlinear change in the thermal oxidation state Ox with time can be represented by equation 3. The model 2 for the region 2 describing the linear change in the thermal oxidation state Ox with time can be represented by the following formula 4.
Ox＝1-[1-{k(T)×teq(1-n)}1/1-n](3)
Ox＝k(T)×teq(4)
In the above formulas 3 and 4, k (t) is a thermal oxidation rate defined by formula 2. Parameter t eqIs the equivalent time that it will take to reach the thermal oxidation state Ox at the temperature T. The parameter n refers to the order of the formula and depends on the properties of the CC composition used in the brake assembly 200. The parameter n may be determined experimentally, for example, for a brake using a particular CC compound.
In some examples, a thermal oxidation model different from that described by equations 3 and 4 may be used. In some examples, a single thermal oxidation model describing the evolution of the thermal oxidation state Ox for all of the thermal oxidation states Ox associated with the brake assembly 200 may be used. In some examples, more than two thermal oxidation models may be used for each range of the thermal oxidation state Ox. The method 800 may be suitably modified to use such an alternative thermal oxidation model. For example, a different set of inputs than those described in this particular example of method 800 may be applied to the thermal oxidation model depending on the circumstances.
It will be appreciated that block 816 may be performed at any stage of method 800 where block 802 was performed, as block 816 requires an initial thermal oxidation state.
At block 818, an updated thermal oxidation state for the high temperature event is determined using the selected thermal oxidation model based on the high temperature interval, the initial thermal oxidation state, and the determined thermal oxidation rate parameter. For example, do Determining the time taken to reach the initial thermal oxidation state from zero at the high temperature value, and adding the high temperature interval to the time to determine t to be used in the selected thermal oxidation modeleqThe value of (c). T to be determined therebyeqIs input into a formula selected from formulas 3 and 4 above, resulting in an updated thermal oxidation state of brake assembly 200 after the high temperature event as an output.
The updated thermal oxidation state may be set to a new initial thermal oxidation state for subsequent use of the method 800 for subsequent high temperature events in the temperature profile.
In some examples, method 700 and/or method 800 may be performed instantaneously during a use period in which a braking event is occurring. In such an example, portions of method 800 may be modified to allow for instantaneous brake oxidation monitoring, for example, and the temperature profile may correspond to an instantaneous measured temperature value. For example, the temperature information provided by the temperature sensor 218 may be continuously compared to the set of temperature criteria per block 804 of method 800, and high temperature events may be identified substantially as they occur. It will be appreciated that while such oxidation state monitoring is described as being instantaneous, the extent to which it occurs in real time will depend on various hardware and software (e.g., processing speed) limitations. For example, there may be a time delay between the temperature values measured by temperature sensor 218 corresponding to the high temperature event and those values that ultimately result in an updated thermal oxidation state of brake assembly 200.
For example, a high temperature event may be identified as a smaller portion of the temperature profile than in the examples described above. Referring again to fig. 9, the portion of the curve portion 902 that occurs within a time interval denoted 910 may be considered a high temperature event and the interval 910 is a high temperature interval of the high temperature event. In this example, the high temperature event value may be taken, for example, as the temperature value measured at the beginning or end of the high temperature interval 910 or the average of the two temperature values. Unlike the example above, in the case of immediate monitoring, even in the case of a temperature exceeding the second temperature threshold 906, the portion of the temperature curve between the first temperature threshold and the second temperature threshold may be considered. In the case of instantaneous monitoring, any portion of the temperature profile that is above at least one temperature threshold (e.g., the portion represented by interval 910) may be identified as a high temperature event. It will be appreciated that such modifications may allow the thermal oxidation state of brake assembly 200 to be updated upon the occurrence of a high temperature event corresponding to a braking event. In some examples, high temperature events may be identified based on the time between subsequent temperature measurements made by temperature sensor 218. For example, interval 910 may be a time interval between subsequent temperature measurements made by temperature sensor 218.
Method 700 and method 800 may be used to determine the thermal oxidation state of brake assembly 200 in an immediate manner after or during an actual use period of aircraft 100. In such an example, this determination may be made based on one or more temperature profiles that contain braking events over the usage period. As mentioned above, in some examples, temperature profile information collected by temperature sensor 218 is used to determine the thermal oxidation state of brake assembly 200 with respect to periods of use that have actually occurred.
In another aspect, in some examples, method 700 or method 800 may be used to predict a future thermal oxidation state of brake assembly 200 after a first plurality of predicted future use cycles of aircraft 100. The first plurality of future use periods may be a number of periods after which a thermal oxidation threshold is reached. Each predicted future use period may include a corresponding plurality of braking events. These predictions may be based on the corresponding predicted temperature profile of brake assembly 200 and the current thermal oxidation state for each predicted future use cycle. The current thermal oxidation state is, for example, an oxidation state that takes into account all previous braking events experienced by brake assembly 200.
For example, an estimated temperature profile may be input into method 700 or method 800, e.g., in chronological order, to determine a future thermal oxidation state of brake assembly 200. An estimated temperature profile for an estimated future use period may be estimated based on previous temperature profiles for previous actual use periods of the aircraft 100. For example, the portion of the temperature profile for the future use period may be predicted using the portion of the previous temperature profile associated with the landing phase. The high temperature interval, high temperature event value, etc. may be stored in a computer readable storage medium when method 700 or method 800 is performed for an actual life cycle of aircraft 100 for purposes of predicting a future thermal oxidation state.
In some examples, data from a previous cycle may not be available, for example, because brake assembly 200 may be new. In some examples, sufficient data may not be available to reliably predict the temperature profile for the predicted future use period. In such an example, a predetermined temperature profile may be used. The predetermined temperature profile may be a profile that is generally expected for a future use period of the aircraft 100.
The estimated temperature profile may, for example, take into account a future flight schedule of the aircraft 100. For example, for some of the predicted future use periods of the aircraft, the aircraft 100 may be expected to land at an airport with a short runway, which requires high energy (i.e., high temperature) braking when landing. For those predicted future usage periods, the predicted temperature profile may indicate high energy braking at landing. It will be appreciated that various other factors may be considered in predicting the temperature profile, such as taxi times at various stages of the predicted future use period, wait times between taxi stages and prior landing stages, etc.
As mentioned above, the first plurality of predicted future usage periods may be a number of predicted future periods after which the predicted future thermal oxidation state will reach the thermal oxidation threshold. For example, the prediction of future thermal oxidation states may be stopped after a period of reaching a thermal oxidation threshold. In some examples, prediction of future thermal oxidation states is stopped as soon as a thermal oxidation threshold is reached. The thermal oxidation threshold may be the following oxidation state: where maintenance or replacement of brake assembly 200 or components of brake assembly 200 is required. For example, the brake assembly 200 may require servicing with a mass reduction of between 4% and 6.5% (e.g., a 5.7% reduction) of the brake assembly 200, wherein the selected percentage threshold may differ, for example, based on the originally manufactured disc density. In this example, the first plurality of predicted future cycles of use is the number of cycles performed such that the proportion of mass lost due to thermal oxidation reaches or exceeds, for example, 5.7% (i.e. in the range of 4% to 6.5%).
On the other hand, in some examples, the prediction of future thermal oxidation state may be stopped at the end of the following predicted future use periods: during this future use period, the future thermal oxidation state is close to the thermal oxidation threshold so that the future thermal oxidation state can be expected to reach the thermal oxidation threshold during the next projected future use period. In such an example, it may be considered that the thermal oxidation threshold is reached within a first plurality of predicted future cycles of use. This is because: in fact, an aircraft 100 having a brake assembly 200 that is expected to strictly meet the thermal oxidation threshold in the very next cycle will not be allowed to fly, and at this point maintenance or replacement associated with that brake assembly 200 may be performed.
Using the first plurality of predicted future life cycles, an indication may be given as to how many life cycles can be performed before brake assembly 200 or components of brake assembly 200 need to be repaired or replaced due to thermal oxidation. In examples where the thermal oxidation threshold is strictly reached or exceeded during the last of the first plurality of future cycles, the number of cycles before repair or replacement is required due to thermal oxidation may be estimated to be one less than the number of cycles of the first plurality. In an example in which the prediction of future thermal oxidation states is stopped when a thermal oxidation threshold is expected to be reached in the next cycle after the first plurality, the first plurality is taken as the number of cycles before maintenance and replacement is required due to thermal oxidation.
FIG. 11 is a flow chart of a method 1100 for determining an amount of brake wear caused by a braking event using a brake wear model based on an amount of energy absorbed by brake assembly 200 due to the braking event and a density parameter of brake assembly 200. The amount of brake wear may be determined for all braking events that input energy to the brake assembly 200 during a process involving friction that would cause wear of the surfaces of the brake discs. For example, wear of the brake disc due to friction may cause the length of the brake disc 202 (length L as shown in fig. 2) to decrease as brake disc material is lost due to friction.
For example, the amount of brake wear may be determined for braking events that do not involve any high temperature events. For the method 1100, a braking event may be identified as an event of an increase in temperature of the brake assembly 200, for example, based on a temperature profile. In some examples, the braking event may simply be identified based on an indication that brake assembly 200 has been applied. For example, computing system 106 of aircraft 100 may detect when brake assembly 200 is applied and when released.
At block 1102 of method 1100, energy input to brake assembly 200 during a braking event is determined. The energy input to brake assembly 200 may be determined, for example, during a braking event based on a characteristic of aircraft 100 (e.g., mass of aircraft 100, speed of aircraft 100 during the braking event, etc.). The energy absorbed by brake assembly 200 may be calculated by determining the kinetic energy of aircraft 100 based on such characteristics of aircraft 100. For example, brake assembly 200 may absorb a given proportion of the kinetic energy of aircraft 100 such that the kinetic energy of aircraft 100 is reduced. In some examples, the energy input to brake assembly 200 may be determined based on measurements taken by instruments 108 of aircraft 100. For example, instrument 108 may include a tachometer associated with wheel 104 associated with brake assembly 200. In such an example, a tachometer measures the rotational speed of the wheel 104, and the change in rotational speed with respect to time can be used to determine the energy absorbed by the brake assembly 200.
In other examples, if the mass of brake assembly 200 is known, the energy absorbed may be determined based on an increase in the temperature of brake assembly 200 taking into account the specific heat of brake assembly 200. In some examples, the quality of brake assembly 200 may be determined based on the thermal oxidation state of brake assembly 200 determined according to the above-described method, because as described above, the thermal oxidation state may be expressed as an amount of mass lost from brake assembly 200 due to thermal oxidation.
At block 1104 of method 1100, a density parameter of brake assembly 200 is determined. The density parameter is, for example, a parameter indicating a reduction in the density of the brake assembly 200 compared to the original density, taking into account the lost mass. The density of the brake assembly 200 may be reduced, for example, due to thermal oxidation. It will be appreciated that thermal oxidation results in a reduction in mass as carbon atoms react with oxygen to form carbon dioxide or carbon monoxide and are thus removed from the brake disc 202. However, thermal oxidation may not necessarily change the volume of the brake disc 202. This is because thermal oxidation may not work evenly on a particular surface of the brake disc, but may occur to a depth into the interior of the brake disc.
The density parameter may be represented as (1-Ox), wherein the thermal oxidation state Ox is represented as a number between 0 and 1. For example, the density of the brake assembly 200 is reduced by a factor of (1-Ox) compared to the initial density before any thermal oxidation occurs (i.e., when the brake assembly 200 is new). Thus, the density parameter may be determined based on the initial oxidation state prior to the braking event.
In some examples, the reduced density of brake assembly 200 may be determined based on measurements made by instruments included in instrument 108. For example, the mass of brake assembly 200 may be calculated based on the amount of energy absorbed by brake assembly 200 (e.g., based on measurements from a tachometer) and a subsequent temperature increase of brake assembly 200 (e.g., based on measurements from temperature sensor 218). The reduced density of brake assembly 200 may be determined based on the calculated mass of brake assembly 200. Aircraft 100 may include the wear pin described in association with brake assembly 200. Typically, the wear pin provides an indication of a reduction in the length L of the brake, and thus an indication of brake wear. For example, the ground crew may check the worn pin between cycles and obtain an updated volume value for the brake assembly 200. In some examples, there may be other ways to measure the change in the length L of the brake assembly 200. For example, a length sensor may be provided for brake assembly 200, and/or an electrically actuated brake may be used. An updated volume value may be determined based on the reduced length L and used to determine the reduced density from the mass. During a single cycle, the change in volume of the brake assembly 200 may be insignificant for purposes of calculating the density parameter, and updated volumes may be obtained after multiple cycles. From the reduced density, a density parameter may be determined.
At block 1106 of method 1100, an amount of brake wear caused by the braking event is determined based on the energy absorbed by brake assembly 200 and the density parameter from block 1104 using a brake wear model. For example, the brake wear model of equation 5 below is used to determine the mass lost to the brake assembly 200 due to wear during a wear event.
In the above formula 5, mwearIs mass lost due to wear during a braking event, EbrakeIs the energy absorbed by the brake assembly 200 and W, X, Y and Z are constants. Constants W, X, Y and Z may be predetermined by experimentation, for example, and may differ depending on the properties of brake assembly 200. The amount of brake wear for a braking event may be determined as a reduction in the length L of the brake assembly 200 based on the reduction in mass due to brake wear during the braking event.
As mentioned above, the initial thermal oxidation rate is used in some examples to determine the density parameter. In these examples, the initial thermal oxidation state may be used for the determination of block 1106 when a braking event occurs (a high temperature event also occurs during the braking event). This is because brake wear occurs on a much shorter time scale than thermal oxidation.
The brake wear amount determined for a braking event may be added to the brake wear amounts in all previous braking events of brake assembly 200 to determine a total amount of brake wear.
For example, method 1100 may be performed instantaneously during the time a braking event occurs, or method 1100 may be performed using relevant data from a usage period that has occurred for that usage period. Method 1100 may also be used to predict a future amount of brake wear of brake assembly 200 after a second plurality of predicted future use periods of aircraft 100. The second plurality of predicted future usage periods may be a number of periods after which the thermal oxidation threshold is reached. Each predicted future use period may include a corresponding plurality of braking events. For example, method 1100 may be performed for each braking event in a second plurality of predicted future use periods. The wear amounts from each of these braking events may be summed to estimate a future brake wear amount for a second plurality of estimated future use periods. For each of the predicted future periods of use, the predictions may be based on a predicted amount of energy absorbed by the brake during the corresponding braking event and a corresponding predicted density parameter of the brake for the corresponding braking event. For example, braking events may be identified based on the estimated temperature profile and the energy absorbed by brake assembly 200 for those braking events may be determined. In other examples, the estimated amount of energy absorbed may be based on data from previous cycles. If the brake assembly 200 is new, or sufficient prior data is not available, a pre-estimated amount of energy may be predetermined.
Method 1100 may be used in conjunction with methods 700 or 800 for the purpose of predicting future brake wear amounts. In these examples, the most recent initial thermal oxidation state immediately prior to each predicted braking event (e.g., predicted future braking event) is known. In this manner, the initial thermal oxidation prior to the future braking event in question may be used to determine the quality of brake assembly 200 and thus the density parameter.
As described above, the second plurality of predicted future use periods may be a number of predicted future periods after which the predicted future amount of brake wear reaches the brake wear threshold. For example, the prediction of the future amount of brake wear may be stopped after a period of reaching a brake wear threshold. In some examples, the prediction of the future amount of brake wear may be stopped once the total amount of brake wear reaches a brake wear threshold. The brake wear threshold may be a total amount of brake wear when the brake assembly 200 or components of the brake assembly 200 need to be serviced or replaced. For example, in the event that the length L of a brake assembly (e.g., brake assembly 200 of fig. 2) is reduced by, for example, 22% to 24%, depending on the type of disc and its initial manufacturing density, the brake assembly may require servicing. For an exemplary disc having an initial length L of about 221mm, a reduction in length of about 60mm to 64mm may result in repair or replacement. In this example, the second plurality of predicted future usage cycles is the number of cycles required for the total amount of brake wear to reach or exceed, for example, 60mm to 64mm (again, this is for an initial disc having a length L of about 221 mm).
In some examples, the predicted amount of brake wear may be based on a predicted amount of brake wear that is expected to occur during the predicted future use period, and the predicted amount of brake wear may be based on a predicted amount of brake wear that is expected to occur during the predicted future use period. In such an example, the brake wear threshold may be considered to be reached within a second plurality of predicted future periods of use. This is because, in fact, aircraft 100 having brake assembly 200 that is expected to strictly reach the brake wear threshold in the next cycle will not be allowed to fly and service or replacement associated with brake assembly 200 may be performed at this time.
By using the second plurality of predicted future life cycles, an indication can be given as to how many life cycles can be performed before brake assembly 200 or components of brake assembly 200 need to be serviced or replaced due to brake wear. In examples where the brake wear threshold is strictly met or exceeded during the last cycle in the second plurality of future cycles, the number of cycles before requiring repair or replacement due to brake wear may be estimated to be one less than the number of cycles in the second plurality of estimated future use cycles. In examples where the prediction of the amount of future brake wear is stopped when the brake wear threshold is expected to be reached in the next cycle after the second plurality of predicted future use cycles, the second plurality of predicted future use cycles is taken as the number of cycles before service or replacement is required due to brake wear.
FIG. 12 is a flow chart of a method 1200 for determining a number of good future use cycles until one of a thermal oxidation threshold and a brake wear threshold is reached. The number of good future use cycles is the number of remaining future use cycles before one of the thermal oxidation threshold or the brake wear threshold is reached. Method 1200 may be performed for a plurality of predicted future cycles of use until a first one of the thresholds is reached. Method 1200 involves estimating a future thermal oxidation state and a future amount of brake wear after the estimated future use period, and determining a number of good future use periods before either of a thermal oxidation threshold and a brake wear threshold is reached if one of the thresholds is reached. In case one of the thresholds is not reached, the prediction is performed for the next predicted future usage period. As in the above example, each predicted future use period includes a plurality of braking events. For each predicted future use period, the predictions are based on a corresponding predicted brake temperature profile, a current thermal oxidation state, a predicted amount of energy absorbed by the brake during the corresponding braking event, and a corresponding predicted brake density parameter for the corresponding braking event.
The number of good future use cycles is the number of cycles after which brake assembly 200 or components of brake assembly 200 may need to be serviced or replaced. It should be appreciated that when one of the thermal oxidation threshold or the brake wear threshold is first reached, service or replacement associated with brake assembly 200 may be performed. Which threshold value is reached first may depend, for example, on the manner in which the aircraft 100 is maneuvered during use and its flight schedule. For example, if the schedule of aircraft 100 involves flying to an airport, which mostly has long runways, short taxi routes, etc., then the brake wear threshold may be reached first. This is because, in such examples, the temperature of the brake assembly 200 may not often exceed any temperature thresholds associated with thermal oxidation. On the other hand, the aircraft 100 may often experience high energy braking (e.g., due to a short runway), resulting in temperatures above thresholds associated with thermal oxidation. In such an example, the thermal oxidation threshold may be reached first.
However, as described above, in some examples, it may be determined whether the brake 200 is capable of performing a future aborted takeoff event. The brake 200 may be considered safe for use if it is determined that the brake is capable of performing future rejected takeoff events regardless of whether the threshold value is reached. However, in some examples, brake 200 may be deemed unsafe to use if the predicted future oxidation state is too severe to make use of brake 200 undesirable.
At block 1202 of the method 1200, a future thermal oxidation state after the predicted future usage period is predicted. The prediction of the future thermal oxidation state is performed as described above, e.g. using a suitable thermal oxidation model based on the predicted temperature profile of the predicted future use period in question. At block 1204 of the method 1200, a future amount of brake wear after the same predicted future period of use is predicted. This prediction is performed in the context of method 1100 as described above.
At block 1206 of the method 1200, it is determined whether a thermal oxidation threshold and/or a brake wear threshold is reached. For example, if the thermal oxidation threshold is reached, the method 1200 proceeds to block 1208, at block 1208, the number of good future use cycles before either the thermal oxidation threshold or the brake wear threshold is reached is determined, and the method 1200 ends. For example, if the thermal oxidation threshold is strictly reached or exceeded after a given number of predicted future cycles of use, the number of good future cycles of use is one less than the given number. For example, if the thermal oxidation threshold is expected to be reached in the next predicted future use period, the number of good future use periods is determined as the number of predicted future use periods for which method 1200 has been currently performed.
On the other hand, if it is determined that the brake wear threshold is reached, the method proceeds to block 1208, the number of good future use cycles is determined at block 1208, and the method 1200 ends. For example, if the brake wear threshold is strictly reached or exceeded after a given number of predicted future usage cycles, the number of good future usage cycles is one less than the given number. For example, if the brake wear threshold is expected to be reached in the next predicted future use period, the number of good future use periods is determined as the number of predicted future use periods for which method 1200 has been performed currently.
For example, if both thresholds are reached, the method 1200 proceeds to block 1208, the number of good future use cycles remaining before the thermal oxidation threshold or the brake wear threshold is reached is determined at block 1208, and the method 1200 ends. In this example, the number of good future use cycles is one less than a given number of predicted future use cycles if at least one of the thresholds is strictly met or exceeded after the given number. Otherwise, the number of good future use cycles is determined as the number of predicted future use cycles for which method 1200 has been performed at the present time.
If the brake wear threshold has not been reached, the method 1200 proceeds to block 1210 and blocks 1202-1210 are repeated for the next predicted future use period.
In this way, the number of good future cycles of use can be predicted based on which of the thermal oxidation threshold and the brake wear threshold is reached first. This is because once the first of these thresholds is reached, the brake assembly 200 may need to be repaired or replaced, or the components of the brake assembly 200 may need to be repaired or replaced. It should be appreciated that brake assembly 200 will not continue to be used, for example, in the event that the thermal oxidation threshold is reached but the brake wear threshold is not reached. It should also be understood that the blocks of method 1200 may be performed in any suitable order. For example, block 1204 may be performed before block 1202, and/or block 1210 may be performed before block 1206.
One or more of the above-described methods, i.e., methods 700, 800, 1100, 1200, or any variation thereof (e.g., an immediate determination of oxidation or brake wear, or a prediction of future thermal oxidation state or future brake wear, etc.) may be performed by a processor of the computing system 106 of the aircraft 100, e.g., based on instructions stored in a computer-readable storage medium of the computing system 106. For example, the processor of the computing system 106 may perform monitoring of the thermal oxidation state (either subsequent to the use period or immediately). Alternatively or additionally, the processor of the computing system may perform monitoring of brake wear (subsequent to or immediately after the period of use). Alternatively or in addition to any of these examples, the prediction related to the future thermal oxidation state and/or the future brake wear state may be performed by a processor of the computing system 106. These methods may be performed, for example, using data from instrument 108. For example, temperature data measured by temperature sensor 218 may be used. In the case of prediction, the future temperature profile and/or other prediction data may be predicted by the processor of the computing system 106. Alternatively, the data for the predictions may be determined on a computing system not onboard the aircraft 100 and may be stored in a computer-readable storage medium of the computing system 106.
Instructions for performing all or a portion of the methods described above may be generated and/or any suitable software or combination of software may be used to perform the methods. In one example, "MATLAB" may be used to generate all or a portion of instructions for a processor (e.g., processor 502 or a processor of computing system 104) to perform any of the above-described methods. In other examples, other software packages may be used. For example, any suitable programming language, development environment, software package, or the like may be used. Other examples of programming languages include PYTHON, C + +, C, JAVASCRIPT, FORTRAN, and the like.
It should be noted that the term "or" as used herein should be interpreted to mean "and/or" unless explicitly stated otherwise. It should be appreciated that the temperature characteristic determined according to the above method may be an expected temperature characteristic expected from a model applied for determining the relationship information.
