阅读说明：本技术 用于使螺旋桨顺桨的方法和系统 (Method and system for feathering a propeller ) 是由 J.查哈尔 C.利希奥 D.麦格拉思 M.尤瑟夫 G.辛嘉罗 于 2020-04-09 设计创作，主要内容包括：本文中描述了用于使螺旋桨顺桨的方法和系统。螺线管配置成在螺线管被激励时,使得螺旋桨顺桨。电子控制器通过第一电连接连接到螺线管用于激励螺线管以使螺旋桨顺桨。辅助机构通过第二电连接连接到螺线管用于激励螺线管以使螺旋桨顺桨。第二电连接独立于第一电连接。(Methods and systems for feathering a propeller are described herein. The solenoid is configured to feather the propeller when the solenoid is energized. The electronic controller is connected to the solenoid through a first electrical connection for energizing the solenoid to feather the propeller. The assist mechanism is connected to the solenoid by a second electrical connection for energizing the solenoid to feather the propeller. The second electrical connection is independent of the first electrical connection.)

1. A system, comprising:

a solenoid configured to feather a propeller when the solenoid is energized;

an electronic controller connected to the solenoid by a first electrical connection for energizing the solenoid to feather the propeller; and

an assist mechanism connected to the solenoid by a second electrical connection for energizing the solenoid to feather the propeller, the second electrical connection being independent of the first electrical connection.

2. The system of claim 1, wherein the assist mechanism is connected to the electronic controller and configured to provide an indication to the electronic controller when the assist mechanism is actuated.

3. The system of claim 2, wherein the electronic controller is configured to disable energization of the solenoid with the electronic controller in response to receiving the indication.

4. The system of claim 2 or 3, wherein the electronic controller is configured to disable fault detection for energizing at least one switch of the solenoid through the first electrical connection in response to receiving the indication.

5. The system of any of claims 2 to 4, wherein the auxiliary mechanism is connected to the electronic controller via an aircraft computer.

6. The system of any one of claims 2 to 5, wherein the electronic controller comprises two channels, and the assist mechanism is connected to each of the two channels to provide the indication thereto.

7. The system of any of claims 1-6, wherein the solenoid comprises two coils, and the second electrical connection connects the assist mechanism to one of the two coils.

8. The system of any one of claims 1 to 7, wherein the assist mechanism is configured to close a high-side switch and a low-side switch when actuated, the solenoid being energized when both the high-side switch and the low-side switch are closed.

9. The system of any one of claims 1 to 8, wherein the assist mechanism comprises a mechanical lever operable to close at least one switch to energize the solenoid.

10. The system of any one of claims 1 to 9, wherein the electronic controller is a first electronic controller, and wherein the assist mechanism comprises a second electronic controller operable to close at least one switch to energize the solenoid when a button connected to the second electronic controller is actuated.

11. A method of feathering a propeller, the method comprising:

upon receiving a first request to energize a solenoid from an electronic controller through a first electrical connection with the solenoid, energizing the solenoid to feather the propeller; and

energizing the solenoid to feather the propeller upon receiving a second request to energize the solenoid from an auxiliary mechanism through a second electrical connection with the solenoid, the second electrical connection being independent of the first electrical connection.

12. The method of claim 11, further comprising providing an indication to the electronic controller when the assist mechanism is actuated.

13. The method of claim 12, further comprising disabling energizing of the solenoid with the electronic controller in response to the electronic controller receiving the indication.

14. The method of claim 12 or 13, further comprising disabling fault detection for energizing at least one switch of the solenoid through the first electrical connection in response to the electronic controller receiving the indication.

15. The method of any of claims 12-14, wherein providing the indication comprises providing the indication via an aircraft computer.

16. The method of any of claims 12-15, wherein the electronic controller comprises two channels, and wherein providing the indication comprises providing the indication to each of the two channels.

17. The method of any of claims 11-16, wherein the solenoid comprises two coils, and wherein energizing the solenoid with the second electrical connection comprises energizing one of the two coils with the second electrical connection.

Technical Field

The present disclosure relates generally to aircraft propeller (propeller) control, and more particularly to feathering propellers (featherers).

Background

For a propeller driven aircraft, the control system may adjust the blade angle of the propeller blades to a feathered position to reduce the forward resistance to the aircraft. For example, the propeller electronic controller may control a feathering solenoid and a protection solenoid, both of which have the ability to drive the propeller blades to a feathered position. Typically, an additional solenoid connected to a rod (lever) in the cockpit of the aircraft is provided for emergency purposes to feather the propeller. However, this additional solenoid adds weight and additional cost to the overall propeller system.

As such, there is a need for improvement.

Disclosure of Invention

In one aspect, a system is provided, the system comprising: a solenoid configured to feather the propeller when the solenoid is energized; an electronic controller connected to the solenoid by a first electrical connection for energizing the solenoid to feather the propeller; and a mechanism connected to the solenoid by a second electrical connection for energizing the solenoid to feather the propeller, the second electrical connection being independent of the first electrical connection.

In another aspect, a method for feathering a propeller is provided. The method comprises the following steps: upon receiving a first request to energize the solenoid from the electronic controller through a first electrical connection with the solenoid, energizing the solenoid to feather the propeller; and energizing the solenoid to feather the propeller upon receiving a second request to energize the solenoid from the auxiliary mechanism through a second electrical connection with the solenoid, the second electrical connection being independent of the first electrical connection.

In another aspect, a method is provided, the method comprising: connecting a solenoid to the electronic controller through a first electrical connection, the solenoid configured to feather the propeller when the solenoid is energized by the electronic controller through the first electrical connection; and connecting a solenoid to the assist mechanism by a second electrical connection, the solenoid configured to feather the propeller when the solenoid is energized by the assist mechanism by the second electrical connection, the second electrical connection being independent of the first electrical connection.

Drawings

Reference is now made to the drawings, in which:

FIG. 1 is a schematic illustration of an example gas turbine engine coupled to a propeller in accordance with one or more embodiments;

FIG. 2A is a schematic diagram illustrating a system for feathering a propeller in accordance with one or more embodiments;

FIG. 2B is a schematic diagram illustrating an example of switches of a system for feathering a propeller in accordance with one or more embodiments;

FIG. 2C is a schematic diagram illustrating an example of a dual coil solenoid and a dual channel electronic controller in accordance with one or more embodiments;

FIG. 3A is a flow diagram of a method for feathering a propeller in accordance with one or more embodiments;

FIG. 3B is a flow diagram of another method in accordance with one or more embodiments; and

FIG. 4 is a block diagram of an example computing device in accordance with one or more embodiments.

It will be noted that throughout the drawings, like reference numerals identify like features.

Detailed Description

FIG. 1 illustrates an aircraft engine 100 for an aircraft of the type preferably provided for use in subsonic flight. Engine 100 generally includes (in serial flow communication): a propeller 120 through which ambient air is propelled and attached to the shaft 108; a compressor section 114 for pressurizing air; a combustor 116 in which compressed air is mixed with fuel and ignited for generating an annular flow of hot combustion gases; and a turbine section 106 for extracting energy from the combustion gases. The propeller 120 converts rotational motion from the shaft 108 of the engine 100 to provide propulsion, also referred to as thrust, for the aircraft. The propeller 120 includes two or more propeller blades 122. The blade angle of the propeller blades 122 may be adjusted to vary the thrust. The blade angle may be referred to as the beta angle, angle of attack, or blade pitch. Engine 100 may be implemented to include a single or multi-spool (spool) gas turbine engine, wherein turbine section 106 is typically coupled to a propeller 120 through a Reduction Gearbox (RGB). It should be appreciated that although engine 100 is a turboprop engine, the methods and systems described herein may be applicable to any other type of gas turbine engine, such as a turbofan engine, a turboshaft engine, or any other suitable aircraft engine.

Referring to fig. 2A, a system 200 for feathering a propeller (e.g., propeller 120 of fig. 1) in accordance with one or more embodiments is illustrated. The system 200 includes a solenoid 210, the solenoid 210 configured to feather the propeller 120 when the solenoid 210 is energized. The system 200 includes an electronic controller 220, the electronic controller 220 being connected to the solenoid 210 by a first electrical connection 201 for energizing the solenoid 210 to feather the propeller 120. The system 200 includes an assist mechanism 230, the assist mechanism 230 connected to the solenoid 210 by a second electrical connection 202 for energizing the solenoid 210 to feather the propeller 120. The electronic controller 220 and the assist mechanism 230 are operable independently of each other to energize the solenoid 210 to feather the propeller 120. The first electrical connection 201 and the second electrical connection 202 are separate connections and independent of each other. Reference to "feathering" propeller 120 or adjusting the blade angle to "feather" propeller 120 refers to pointing the blades of propeller 120 to a feathered position. In the feathered position, the propeller blades are positioned at an angle substantially parallel to the airflow over the propeller 120 in order to reduce the forward drag on the aircraft. While the engine 100 and propeller 120 are illustrated as being part of the system 200, it should be understood that this is for illustrative purposes only, and in some embodiments, the system 200 does not include the engine 100 and propeller 120.

The solenoid 210 is an electro-hydraulic actuator for adjusting the blade angle of the propeller 120. When at least one coil of the solenoid 210 is energized, the solenoid 210 is considered energized. When the coil of the solenoid 210 is energized, the solenoid valve is actuated to regulate the supply of hydraulic fluid to the propeller 120 to drive the blade angle of the propeller 120 toward the feathered position. The solenoid 210, when energized, may hydraulically bypass, for example, a pitch adjustment actuator (such as a pitch change unit) that is used to make fine adjustments to the propeller blade angle over the full range of propeller blade pitches. In some embodiments, solenoid 210 is a feathering solenoid, which may be used for routine (turbine) feathering or auto-feathering operations. In some embodiments, the solenoid 210 is a protective solenoid that may be used when propeller overspeed is detected or in the event that the propeller blade angle is below a minimum allowable in-flight blade angle.

It will be appreciated that by connecting the auxiliary mechanism 230 to the same solenoid 210 to which the electronic controller 220 is connected, a dedicated emergency solenoid, which is conventionally connected to the auxiliary mechanism 230, may be eliminated and the overall weight and/or cost of the propeller system may be reduced.

Electronic controller 220 may be any suitable electronic controller configured to energize solenoid 210 for feathering propeller 120. For example, the electronic controller 220 may close at least one switch to energize the solenoid 210 via the first electrical connection 201. Electronic controller 220 may energize solenoid 210 in response to detecting that propeller 120 should be driven to the feathered position. For example, electronic controller 220 may command the propeller blade angle to a feathered position for routine feathering before engine 100 is shut down on-ground. For example, when engine 100 has failed during takeoff, electronic controller 220 may command the propeller blade angle to a feathered position for auto-feathering. When the rotational speed of the propeller exceeds a threshold, electronic controller 220 may command the propeller blade angle to a feathered position to protect propeller 120 from overspeed. When the blade angle of the propeller 120 is below the minimum in-flight propeller blade angle, the electronic controller 220 may command the propeller blade angle to a feathered position. In some embodiments, electronic controller 220 energizes solenoid 210 in response to receiving a feathering command from, for example, an engine or aircraft computer that detects when propeller 120 should be driven to a feathered position. In some embodiments, electronic controller 220 is a propeller electronic controller.

In some embodiments, the assist mechanism 230 is an emergency mechanism that may be actuated for emergency feathering of the propeller 120. The assist mechanism 230 may be any suitable mechanism configured to energize the solenoid 210 for feathering the propeller 120. For example, the assist mechanism 230 may close at least one switch to energize the solenoid 210 via the second electrical connection 202. The assist mechanism 230 may include a non-electronic controller. For example, the assist mechanism 230 may be a mechanical, pneumatic, hydraulic, or combination thereof mechanism. The assist mechanism 230 may include a mechanical lever in the aircraft that, when actuated by the flight crew (e.g., a pilot or other personnel), causes the solenoid 210 to be energized. For example, the mechanical lever may be operable to close at least one switch to energize the solenoid 210 when the mechanical lever is actuated. The mechanical lever may be considered a fire handle. The assist mechanism 230 may include an electronic controller. For example, the second electronic controller (i.e., separate from the first electronic controller 220) may be operable to close at least one switch to energize the solenoid 210 when an actuator (e.g., a button, a lighted button, a switch, a dial, a knob, any other suitable interface, or the like) connected to the second electronic controller is actuated. The second electronic controller may be an aircraft computer.

In some embodiments, assist mechanism 230 is connected to electronic controller 220 via connection 203 and is configured to provide an indication to electronic controller 220 when assist mechanism 230 is actuated. In some embodiments, the electronic controller 220 is configured to disable energization of the solenoid 210 with the electronic controller 220 in response to receiving the indication. For example, electronic controller 220 may disable energization of solenoid 210 for auto-feathering, routine feathering, propeller overspeed protection, minimum in-flight propeller blade angle, and/or the like. In some embodiments, the electronic controller 220 is configured to disable fault detection for energizing at least one switch of the solenoid 210 via the first electrical connection 201 in response to receiving the indication. The detection of a fault by electronic controller 220 may assess whether electronic controller 220 commands actuation of solenoid 210. If electronic controller 220 does not command the energization of solenoid 210 and solenoid 210 is energized, then electronic controller 220 may detect a failure of at least one switch. Upon detection of a fault, the fault may be output to a display device to indicate the fault. The assist mechanism 230 may be directly or indirectly connected to the electronic controller 220 for providing the indication. The indication may be provided as an analog or digital signal.

Referring to fig. 2B, in some embodiments, the electronic controller 220 and the assist mechanism 230 each include two switches. In some embodiments, electronic controller 220 is configured to operate (i.e., open and close) high-side switch 222 and low-side switch 224. When both the high-side switch 222 and the low-side switch 224 are closed, the coil 211 of the solenoid 210 is energized. The high-side switch 222, when closed, provides a power source (e.g., a 28V source or any other suitable voltage) to the first electrical connection 201, and the low-side switch 224, when closed, provides a ground connection to the first electrical connection 201. If either (or both) of the switches 222, 224 are open, the solenoid 210 will not be energized via the first electrical connection 201. One of the switches 222, 224 may be held in the closed position by default, and the electronic controller 220 may be configured to operate the other of the switches 222, 224 to energize the solenoid 210. Alternatively, in some embodiments, the electronic controller 220 includes one high-side switch or one low-side switch operable to energize the solenoid 210.

In some embodiments, the assist mechanism 230 is configured to close the high-side switch 232 and the low-side switch 234 when actuated. When both the high-side switch 232 and the low-side switch 234 are closed, the coil 211 of the solenoid 210 is energized. As shown, the assist mechanism 230 is connected to the same solenoid coil 211 to which the electronic controller 220 is connected. The high-side switch 232 provides a power source (e.g., a 28V source or any other suitable voltage) to the second electrical connection 202 when closed, and the low-side switch 234 provides a ground connection to the second electrical connection 202 when closed. If either (or both) of the switches 232, 234 are open, the coil 211 of the solenoid 210 will not be energized via the second electrical connection 202. If either (or both) of the switches 222, 224 are open, the coil 211 of the solenoid 210 may be energized via the second electrical connection 202 by closing the switches 232 and 234. One of the switches 232, 234 may be held in a closed position by default, and the assist mechanism 230 may be configured to close the other of the switches 222, 224 when actuated. Alternatively, in some embodiments, the assist mechanism 230 includes one high-side switch or one low-side switch operable to energize the solenoid 210. In some embodiments, the switches 232, 234 can be operated simultaneously by a single control device (also referred to as a "ganged switch") to energize the solenoid 210.

In some embodiments, such as that shown in fig. 2B, the auxiliary mechanism 230 is connected to the electronic controller 220 via an aircraft computer 240. The aircraft computer 240 may monitor the assist mechanism 230 to detect when the assist mechanism 230 is actuated. For example, the aircraft computer 240 may monitor at least one of the switches 232, 234 to detect when the mechanism 230 is actuated. Alternatively, the assistance mechanism 230 may provide an indication to the aircraft computer 240 when actuated. When assist mechanism 230 is actuated, an indication that assist mechanism 230 is actuated may be provided to electronic controller 220 from aircraft computer 240. In some embodiments, the assistance mechanism 230 includes an aircraft computer 240.

Reference numeral 250 illustrates that the electronic controller 220 and the solenoid 210 are positioned in an area subject to a possible fire (hereinafter "fire area"). Since emergency feathering may be required when a fire is present, the hardware and/or components located in the fire zone 250 associated with emergency feathering may be made of fire-resistant or fire-resistant materials. Thus, in some embodiments, the second electrical connection 202 is a fire-resistant or fire-resistant connection. In some embodiments, connection 203 between aircraft computer 240 and electronic controller 220 is a fire-resistant or fire-resistant connection.

Referring to fig. 2C, in some embodiments, electronic controller 220 includes two or more channels, e.g., channels a and B. The lane A, B is a redundant lane and one of the lanes (e.g., lane a) is selected to be active while the other lane is still in standby (e.g., lane B). The tunnel may be used to energize the solenoid 210 to feather the propeller 120 when the tunnel is active, and not to energize the solenoid 210 to feather the propeller 120 when the tunnel is in standby. When a channel is in standby, it is active and can take over control when needed. If it is determined that the currently active channel is faulty or inoperable, the currently active channel may be deactivated and the channel in standby may be activated. Similarly, if during operation, an input to a currently active lane is erroneous or non-existent, the currently active lane may be deactivated and one of the lanes in standby may be activated.

As shown in FIG. 2C, each channel A, B of electronic controller 220 includes a high-side switch 222_AOr 222_BAnd a low side switch 224_AOr 224_B. Each channel A, B operates the high-side switch 222 in a manner similar to that described with respect to the electronic controller 220 of FIG. 2B_AOr 222_BAnd a low side switch 224_AOr 224_B. High side switch 222 at channel A_AAnd a low side switch 224_AWhen both are closed, the first coil 211 of the solenoid 210 is energized via the first electrical connection 201 to energize the solenoid 210. High side switch 222 at channel B_BAnd a low side switch 224_BWhen both are closed, the second coil 212 of the solenoid 210 is energized via a separate electrical connection 205 to energize the solenoid 210. Alternatively, in some embodiments, each channel A, B includes one high-side switch or one low-side switch operable to energize the solenoid 210.

In some embodiments, as illustrated in fig. 2C, the solenoid 210 is configured such that only one of the two coils 211, 212 need to be energized to feather the propeller 120. In some embodiments, the second electrical connection 202 connects the assist mechanism 230 to one of the two coils 211, 212 of the solenoid 210, which is also connected to one of the channels of the electronic controller 220. In some embodiments, the solenoid 210 includes a first connector 261_AAnd a second connector 262. First connector 261_AThe channel a of the electronic controller 220 is connected to the first coil 211, and the second connector 262 connects the assist mechanism 230 to the first coil 211. Another connector 261_BMay be used to connect channel B of the electronic controller 220 to the second coil 212. Although the assist mechanism 230 is shown connected to the first coil 211, in other embodiments, the assist mechanism 230 may be connected to the second coil 212. Alternatively, in some embodimentsThe mechanism 230 is connected to the two coils 211, 212 of the solenoid 210.

As shown in fig. 2C, in some embodiments, the assist mechanism 230 is connected to each of the two channels A, B to provide an indication that the assist mechanism 230 is actuated. The first aircraft computer 241 may obtain an indication that the assist mechanism 230 is actuated. An indication that assist mechanism 230 is actuated may be provided from first aircraft computer 241 to one of the channels (e.g., channel a) of electronic controller 220. In some embodiments, an indication that assist mechanism 230 is actuated may be provided from first aircraft computer 241 to second aircraft computer 242, and second aircraft computer 242 provides the indication to another channel (e.g., channel B) of electronic controller 220. In some embodiments, second aircraft computer 242 may obtain an indication from assist mechanism 230 and provide the indication to one of the channels (e.g., channel B). Alternatively, in some embodiments, a single aircraft computer may be used to provide the indication to both channels A, B.

Diode 225_AOr 225_BHigh side switch 222 which may be positioned at each channel A, B_AOr 222_BAnd the solenoid 210 for current backflow protection. Diode 225_AIt is possible to prevent the electric power from the assist mechanism 230 from damaging the electronic controller 220. Similarly, diode 235 may be used for current backflow protection to prevent electrical power from electronic controller 220 from damaging assist mechanism 230. Other suitable devices and/or mechanisms for reverse flow protection may be used.

Referring to fig. 3A, a flow chart of a method 300 for feathering a propeller (e.g., propeller 120) is illustrated. At step 302, upon receiving a first request to energize the solenoid from the electronic controller 220 over the first electrical connection 201 with the solenoid 210, the solenoid 210 is energized to feather the propeller 120. At step 304, upon receiving a second request to energize the solenoid from the assist mechanism 230 via the second electrical connection 202 with the solenoid 210, the solenoid 210 is energized to feather the propeller 120. The electronic controller 220 and the assist mechanism 230 are operable independently of each other for energizing the solenoid 210. The second electrical connection 202 is independent of the first electrical connection 201. In some embodiments, the solenoid 210 includes two coils, and energizing the solenoid 210 through the second electrical connection 202 at step 304 includes energizing one of the two coils through the second electrical connection 202. In some embodiments, at step 306, method 300 includes providing an indication to electronic controller 220 when assist mechanism 230 is actuated. The indication is provided from the secondary authority 230 and may be provided via an aircraft computer (e.g., aircraft computers 240, 241, and/or 242). In some embodiments, the electronic controller 220 includes two channels A, B, and the indication is provided to each of the two channels A, B. In some embodiments, at step 308, the method 300 includes the electronic controller 220 disabling energization of the solenoid 210 with the electronic controller 220 in response to receiving the indication. In some embodiments, at step 310, the method 300 includes the electronic controller 220 disabling fault detection for energizing at least one switch of the solenoid 210 via the first electrical connection 201 in response to receiving the indication.

Referring to fig. 3B, a flow chart of a method 350 is illustrated. At step 352, the solenoid 210 is connected to the electronic controller 220 via the first electrical connection 201. The solenoid 210 is configured to feather the propeller 120 when the solenoid 210 is energized by the electronic controller 220 through the first electrical connection 201. At step 352, the solenoid 210 is connected to the assist mechanism 230 via the second electrical connection 202. The solenoid 210 is configured to feather the propeller 120 when the solenoid 210 is energized by the assist mechanism 230 through the second electrical connection 202. The second electrical connection 202 is independent of the first electrical connection 201. In some embodiments, at step 354, the assist mechanism 230 is connected to the electronic controller 220 via the third connection 203. The third connection 203 may be used to provide an indication when the assist mechanism 230 is actuated. In some embodiments, assist mechanism 230 is connected to electronic controller 220 through at least one aircraft computer 240, 241, and/or 242. In some embodiments, the solenoid 210 includes two coils 211, 212, and connecting the solenoid 210 to the assist mechanism 230 includes connecting one of the two coils 211, 212 to the assist mechanism 230 via the second electrical connection 202. In some embodiments, the solenoid 210 includes two coils 211, 212, and connecting the solenoid 210 to the electronic controller 220 includes connecting one of the two coils 211, 212 (e.g., the first coil 211) to a first channel a of the electronic controller 220 and connecting the other of the two coils 211, 212 (e.g., the second coil 212) to a second channel B of the electronic controller 220.

Referring to fig. 4, an example of a computing device 400 is illustrated. Electronic controller 220 may be implemented with one or more computing devices 400. In some embodiments, each passage A, B of electronic controller 220 may be implemented by a separate computing device 400. The computing device 400 includes a processing unit 412 and a memory 414, the memory 414 having stored therein computer-executable instructions 416. The processing unit 412 may include any suitable means configured to implement the methods 300 and/or 350 such that the instructions 416, when executed by the computing apparatus 400 or other programmable device, may cause the functions/acts/steps to be performed as part of the methods 300 and/or 350 to be performed as described herein. Processing unit 412 may include, for example, any type of general purpose microprocessor or microcontroller, a Digital Signal Processing (DSP) processor, a Central Processing Unit (CPU), an integrated circuit, a Field Programmable Gate Array (FPGA), a reconfigurable processor, other suitably programmed or programmable logic circuitry, or any combination thereof.

Memory 414 may include any suitable known or other machine-readable storage medium. Memory 414 may include a non-transitory computer-readable storage medium, such as, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. The memory 414 may include any type of computer memory (e.g., a suitable combination of Random Access Memory (RAM), Read Only Memory (ROM), Compact Disc Read Only Memory (CDROM), electro-optic memory, magneto-optic memory, Erasable Programmable Read Only Memory (EPROM) and Electrically Erasable Programmable Read Only Memory (EEPROM), ferroelectric RAM (fram), or the like) located internal or external to the apparatus. Memory 414 may include any storage component (e.g., device) suitable for retrievably storing machine-readable instructions 416 executable by processing unit 412. Note that the computing device 400 can be implemented as part of a full authority digital engine control equipment (FADEC) or other similar device, including an electronic engine control equipment (EEC), an engine control unit (EUC), an electronic propeller control equipment, a propeller control unit, and the like.

The methods and systems for feathering propellers described herein may be implemented using a high level procedural or object oriented programming or scripting language, or a combination thereof, to communicate with or facilitate the operation of a computer system (e.g., computing device 400). Alternatively, the method and system for feathering a propeller may be implemented in assembly or machine language. The language may be a compiled or interpreted language. Program code for implementing the method and system for feathering a propeller may be stored on a storage medium or device (e.g., ROM, magnetic disk, optical disk, flash drive, or any other suitable storage medium or device). The program code can be readable by a general or special purpose programmable computer for configuring and operating the computer when the storage medium or device is read by the computer to perform the procedures described herein. Embodiments of the method and system for feathering a propeller may also be considered to be implemented by a non-transitory computer readable storage medium having a computer program stored thereon. The computer program may comprise computer-readable instructions that cause a computer, or more specifically the processing unit 412 of the computing device 400, to operate in a specific and predefined manner to perform the functions described herein, such as those described in the methods 300 and/or 350.

Computer-executable instructions may take many forms, including program modules, executed by one or more computers or other devices. Generally, program modules include routines, programs, objects, components, data structures, etc. that perform particular tasks or implement particular abstract data types. Typically, the functionality of the program modules may be combined or distributed as desired in various embodiments.

The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. Still other modifications that fall within the scope of the invention will be apparent to those skilled in the art upon review of this disclosure.

Various aspects of the methods and systems for feathering propellers may be used in various arrangements, alone, in combination, or not specifically discussed in the embodiments described above, and are therefore not limited in their application to the details and arrangement of components set forth in the above description or illustrated in the drawings. For example, aspects described in one embodiment may be combined in any manner with aspects described in other embodiments. While particular embodiments have been shown and described, it will be obvious to those skilled in the art that changes and modifications may be made without departing from the invention in its broader aspects. The scope of the claims that follow should not be limited by the embodiments set forth in the examples, but should be given the broadest reasonable interpretation consistent with the description as a whole.