阅读说明：本技术 一种大修飞机座舱盖骨架及其监控使用方法 (Overhauled aircraft canopy framework and monitoring and using method thereof ) 是由 刘汉海 隋福成 解放 王成波 于淼 于 2019-09-24 设计创作，主要内容包括：本申请涉及一种大修飞机座舱盖骨架监控使用方法,包括：根据静力和疲劳试验确定座舱盖骨架中的多个薄弱部位；获取大修厂和外场使用场景中相近系列飞机的座舱盖骨架的故障信息；大修厂内座舱盖检查；对静力和疲劳试验中应力较大及外场使用中出现故障的部位进行损伤容限分析；根据试验结果以及损伤容限分析结果确定使用中的危险薄弱部位；根据危险薄弱部位确定检查部位和检查方法；对损伤容限分析中不满足到二次大修的危险薄弱部位进行预防性补强修理；确定座舱盖骨架监控使用时的检查部位和检查周期；对座舱盖骨架监控使用进行风险评估,并给出监控使用结论。通过本申请的方法所确定的座舱盖骨架可以保证使用到二次大修,降低了零部件的使用成本。(The application relates to a monitoring and using method for a canopy framework of an overhauled airplane, which comprises the following steps: determining a plurality of weak parts in the canopy framework according to static force and fatigue tests; acquiring fault information of canopy frameworks of similar series of airplanes in the use scenes of major repair factories and outfields; inspecting a cabin cover in a overhaul plant; analyzing damage tolerance of parts with larger stress and faults in the use of an external field in static force and fatigue tests; determining a dangerous weak part in use according to the test result and the damage tolerance analysis result; determining an inspection part and an inspection method according to the dangerous weak part; performing preventive reinforcement repair on dangerous weak parts which do not meet secondary overhaul in damage tolerance analysis; determining an inspection part and an inspection period when the canopy framework is monitored and used; and carrying out risk assessment on monitoring use of the canopy framework, and giving a monitoring use conclusion. The canopy framework determined by the method can be guaranteed to be used for secondary overhaul, and the use cost of parts is reduced.)

1. A monitoring and using method for a canopy framework of an overhauled aircraft is characterized by comprising the following steps

Determining a plurality of weak parts in a canopy framework according to a static test and a fatigue test of the canopy;

acquiring fault information of a plurality of weak parts corresponding to canopy frameworks of similar series of airplanes in the use scenes of major repair plants and external fields;

inspecting a canopy for first overhaul in an overhaul factory;

analyzing damage tolerance of parts with larger stress and faults in the use of an external field in a static test and a fatigue test;

determining dangerous weak parts in use according to the results of the static test and the fatigue test and the damage tolerance analysis result;

determining an inspection part and a corresponding inspection method according to the dangerous weak part;

performing preventive reinforcement repair on dangerous weak parts which do not meet secondary overhaul in damage tolerance analysis;

determining the inspection position and the inspection period requirement when the canopy framework of the overhaul airplane is monitored and used;

and (4) carrying out risk assessment on the monitoring use of the canopy framework by combining multiple factors, and giving a monitoring use conclusion of the canopy framework of the overhaul airplane.

2. A method of using and monitoring canopy frameworks of an overhaul aircraft as claimed in claim 1, wherein the canopy frameworks comprise a front arc, a middle arc, a rear arc and side profiles for carrying the front arc, the middle arc and the rear arc.

3. The method for monitoring and using canopy frameworks of an overhauled aircraft as defined in claim 1, wherein the weak portion is a portion with a maximum numerical value in a stress measurement result.

4. The method for monitoring and using the canopy framework of an overhauled aircraft as claimed in claim 1, wherein the camera-series aircraft is an aircraft capable of being used universally with more than a predetermined proportion of components.

5. The overhauled aircraft canopy framework monitoring use of claim 1 wherein the inspection methods include, but are not limited to, visual inspection, non-destructive inspection, dye penetrant inspection.

6. The method for monitoring and using the canopy framework of an overhauled aircraft of claim 1, wherein the plurality of factors comprise at least one or more of process factors, material factors, canopy throw factors, fatigue failure factors, and calendar life factors.

7. An overhauled aircraft canopy framework, characterized in that the service life of the overhauled aircraft canopy framework reaches the first turn over period, which is determined according to the overhauled aircraft canopy framework monitoring use method of claims 1 to 5.

Technical Field

The application belongs to the technical field of aircraft structure maintenance, and particularly relates to a cabin cover framework of an overhauled aircraft and a monitoring and using method thereof.

Background

The monitoring use means that the parts do not conform to the theoretical design and the test requirements, and corresponding technical measures are adopted to ensure that the parts can be continuously and safely used.

According to the development requirement of an airplane, the target service life of the canopy framework is 6000 flight hours, but because irreparable damage occurs to glass in a fatigue test, the subsequent fatigue test is not completed, and therefore, in order to ensure the flight safety, the canopy framework needs to be replaced when the canopy framework is repaired for the first time. The canopy glass is a brittle material, and when the canopy is designed for fatigue, the service life of the canopy is determined by adopting a safety life criterion, namely, only the crack formation life is considered, and the crack propagation life is not considered, so that the corresponding service life of the canopy can be provided only by completing a spectrum-loading fatigue test with a 6-time service life. Because the development cycle of the canopy fatigue test is slow, the problems of long cycle and high cost of purchasing a canopy framework by a repair shop are solved by adopting a new design rule from the design point of view. Considering that the canopy metal framework is made of aluminum alloy materials and has good crack propagation resistance, a monitoring use method suitable for the canopy metal framework can be established based on the design criterion of damage tolerance, the metal framework is guaranteed to have enough residual strength before damage is detected, and the metal framework can be detected and repaired in time before the damage is propagated to the critical dimension.

In view of the above, there is a need for a method for monitoring and using a canopy framework of an overhauled aircraft, which can provide a conclusion about monitoring and using the canopy framework of the overhauled aircraft more safely and reliably.

Disclosure of Invention

The invention aims to provide a canopy framework of an overhauled aircraft and a monitoring and using method thereof, which aim to solve or reduce at least one problem in the background art.

In one aspect, the technical solution provided by the present application is: a monitoring and using method for a canopy framework of an overhauled aircraft comprises the following steps:

determining a plurality of weak parts in a canopy framework according to a static test and a fatigue test of the canopy;

acquiring fault information of a plurality of weak parts corresponding to canopy frameworks of similar series of airplanes in the use scenes of major repair plants and external fields;

inspecting a canopy for first overhaul in an overhaul factory;

analyzing damage tolerance of parts with larger stress and faults in the use of an external field in a static test and a fatigue test;

determining dangerous weak parts in use according to the results of the static test and the fatigue test and the damage tolerance analysis result;

determining an inspection part and a corresponding inspection method according to the dangerous weak part;

performing preventive reinforcement repair on dangerous weak parts which do not meet secondary overhaul in damage tolerance analysis;

determining the inspection position and the inspection period requirement when the canopy framework of the overhaul airplane is monitored and used;

and (4) carrying out risk assessment on the monitoring use of the canopy framework by combining multiple factors, and giving a monitoring use conclusion of the canopy framework of the overhaul airplane.

In the method of the present application, the canopy framework includes a front arc, a middle arc, a rear arc, and side profiles for carrying the front arc, the middle arc, and the rear arc.

In the method of the present application, the weak portion is a portion having a maximum numerical value in the stress measurement result.

In the method of the application, the camera-series airplane refers to an airplane with more than a predetermined proportion of parts and components capable of being used in common.

In the methods of the present application, the inspection methods include, but are not limited to, visual inspection, non-destructive inspection, dye penetrant inspection.

In the method of the present application, the plurality of factors include at least one or more of process factors, material factors, canopy throw factors, fatigue failure factors, calendar life factors.

On the other hand, the technical scheme provided by the application is as follows: a overhauled aircraft canopy framework, the service life of which reaches the first-turn period, determined according to the overhauled aircraft canopy framework monitoring use method of claims 1-5.

The canopy framework determined by the monitoring and using method for the canopy framework of the overhaul airplane can be guaranteed to be used for secondary overhaul, and the using cost of parts is reduced.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

Fig. 1 is a schematic view of a monitoring and using method of a canopy framework of an overhauled aircraft according to the present application.

Fig. 2 is a schematic view of the aircraft cabin structure of the present application.

FIG. 3 is a graph of the residual strength of the side section bar after reinforcement repair and crack length relationship in the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In order to solve the problems pointed out in the background art, the application provides a monitoring and using method suitable for the canopy framework of the overhaul airplane, and a feasibility conclusion of monitoring and using the canopy framework of the overhaul airplane is provided more safely and reliably.

As shown in fig. 1, the canopy framework monitoring method for an overhauled aircraft of the present application includes the following steps:

step S11: and determining a plurality of weak parts according to the test results of the static test and the fatigue test of the canopy.

As shown in fig. 1, which is a schematic structural view of a canopy, the canopy includes a front glass 1, a rear glass 2 (openable), a front arc 3, a middle arc 4, a rear arc 5, and side profiles 6. Wherein, the front arc 3, the middle arc 4 and the rear arc 5 are connected to the side section bars 6 to form the canopy framework.

According to the stress measurement results of the metal parts of the front arc 3, the middle arc 4, the rear arc 5 and the side section bar 6 of the canopy in the completed canopy static test and fatigue test, a plurality of weak parts of the canopy framework are extracted, and the weak parts, namely a plurality of parts with the largest values in the stress measurement results are designed weak parts.

For example, through static and fatigue tests on the canopy, the stress of the front arc 3 and the side section 6 of the canopy is determined to be large through analysis of stress measurement results of metal parts of the front arc 3, the middle arc 4, the rear arc 5 and the side section 6 of the canopy, in the static tests, the joint of the side section 6 and the third lock ring is damaged due to overload, and in the fatigue tests, the side section 6 is cracked due to fatigue. Therefore, the above-mentioned portions are weak portions.

Step S12: and acquiring fault information of canopy frameworks of similar series of airplanes in the service scene of the overhaul factory and the service scene of the external field.

The similar series of airplanes generally refer to airplanes with more than a predetermined ratio of parts and components which can be used in common. The predetermined ratio is not less than 60% in the case where a certain float occurs according to the aircraft family.

In this embodiment, through statistics and analysis of the failure information of the metal parts of the canopy front arc 3, the middle arc 4, the rear arc 5 and the side profile 6 of the similar series of airplanes in the service scene of the overhaul plant and the external field, the failure of the crack is found.

Step S13: and (4) carrying out depth inspection on the cabin cover framework in the repair shop.

Inspection methods include, but are not limited to, visual inspection, non-destructive inspection, and dye penetrant inspection, among others. In the present embodiment, the damage of the metal parts such as the front arc 3, the middle arc 4, the rear arc 5, and the side profile 6 of the canopy, which are first overhauled in the overhaul factory, is inspected by a method combining visual inspection and nondestructive inspection, and as a result, no damage such as cracks is found.

S14: and (3) performing damage tolerance calculation analysis on the parts with larger stress and faults in the use of an external field in the static test and the fatigue test.

In the embodiment, the root of the front arc 3 of the canopy and the connection section of the side section 6 and the third locking ring are selected at the calculation part, the analysis result of the front arc of the canopy meets the target service life requirement through crack propagation rate analysis and residual strength calculation, the connection section of the side section 6 and the third locking ring does not meet the target service life requirement, pre-reinforcement repair is required, and the target service life requirement is met after reinforcement repair.

S15: and (4) screening dangerous weak parts in use according to analysis of results of the static test and the fatigue test, faults found in the use scenes of major repair factories and outfields and the calculation of the damage tolerance strength.

In the embodiment, the connecting section of the front arc root part of the canopy, the side section bar and the third locking ring is screened out to be a dangerous weak part in use.

S16: and determining the inspection part and the inspection method of the corresponding part according to the screening result of the dangerous weak part.

For example, the portions to be inspected are the root of the canopy front arc 3 and the section of the side profile 6 joined to the third shackle, and the inspection method is dye penetrant inspection.

S17: and performing preventive reinforcement repair on the dangerous weak part which is not satisfied with the secondary overhaul in the damage tolerance analysis.

In this embodiment, the dangerous weak part is a joint between the side profile 6 and the third locking ring, so that the joint between the side profile and the third locking ring, which does not satisfy the secondary overhaul in the damage tolerance analysis, is subjected to preventive reinforcement repair, and the reinforcement repair method is not described herein again.

S18: and determining the inspection position and the inspection period requirement when the canopy framework of the overhaul airplane is monitored and used.

For example, the inspection positions of the monitoring use of the canopy framework of the overhauled airplane are determined as the root of the canopy front arc 3 and the connection section of the side section bar 6 and the third locking ring, the inspection period is every 50 +/-5 flight hours, and the inspection period is smaller than the crack propagation speed.

S19: and (4) carrying out risk assessment on the monitoring use of the canopy framework by combining multiple factors, and giving a monitoring use conclusion of the canopy framework of the overhaul airplane.

Among these, many factors include, but are not limited to, process factors, material factors, canopy throw factors, fatigue failure factors, calendar life.

In the present embodiment, the canopy repair process in a major repair facility is mature; selecting a canopy framework material system without risk; after the cabin cover part is strengthened, the weight and the gravity center meet the design requirements, and no risk factor is thrown by the cabin cover; crack propagation rate analysis and residual strength calculation are carried out on dangerous weak parts, the analysis results meet the target service life requirements, the connection section of the side section bar 6 and the third locking ring is pre-repaired, and the canopy framework has no risk of fatigue failure; the canopy framework protection system is the same as that of similar series of airplanes, and risk factors of calendar life are avoided.

As shown in fig. 3, by analyzing the results of the static test and the fatigue test of the canopy framework of the airplane and combining the use experiences of an overhaul factory and an outfield, the fatigue dangerous weak part of the canopy framework of the airplane is accurately grasped, a monitoring or preventive repair scheme is formulated, and the canopy framework of the airplane is monitored and used in the outfield, so that the canopy framework of the airplane can be safely used for secondary overhaul.

Finally, the application also provides a canopy framework of the overhaul aircraft, the service life of the canopy framework of the overhaul aircraft reaches the first turning period, and the canopy framework of the overhaul aircraft is monitored and used according to the monitoring and using method of the canopy framework of the overhaul aircraft.

The canopy framework determined by the monitoring and using method for the canopy framework of the overhaul airplane can be guaranteed to be used for secondary overhaul, and the using cost of parts is reduced.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.