Reliability testing methods, apparatus and equipment for near-space low-speed aircraft products

Abstract

This invention provides a reliability testing method, apparatus, and equipment for near-space low-speed aircraft products. The method includes determining the composition and structure of the low-speed aircraft product; determining the failure modes corresponding to the product's composition and structure; determining the environmentally sensitive stresses of the low-speed aircraft in near-space under each failure mode; determining a test profile based on these environmentally sensitive stresses; applying the environmentally sensitive stresses according to the test profile; and testing the functional and performance indicators of the low-speed aircraft product during the test. Based on the test results of the product's functional and performance indicators, the design and manufacturing process of the low-speed aircraft product are improved. By specifically determining the test profile for the characteristics of near-space, and then conducting the test, this method significantly improves the accuracy and efficiency of reliability testing results compared to general testing methods.

Description

Technical Field

[0001] This invention relates to the field of reliability testing technology, and in particular to a reliability testing method, apparatus and equipment for near-space low-speed aircraft products. Background Technology

[0002] Reliability enhancement testing primarily induces product failure by intensifying various stresses. Its core lies in the selection of stresses and the formulation of test profiles. Considering the sensitive stresses of aircraft products and limited by testing equipment capabilities and costs, common aircraft reliability enhancement tests mainly simulate these stresses by applying environmental stresses such as temperature, humidity, vibration, and electrical stress.

[0003] Currently, most aircraft reliability tests use general-purpose standards, resulting in relatively low accuracy of reliability test results. Summary of the Invention

[0004] This invention provides a reliability testing method, apparatus, and equipment for near-space low-speed aircraft products, which solves the problem of poor accuracy in general reliability tests in the prior art.

[0005] In a first aspect, the present invention provides a reliability testing method for near-space low-speed aircraft products, comprising:

[0006] Determine the composition and structure of low-speed aircraft products;

[0007] Determine the failure modes corresponding to the composition and structure of the product;

[0008] In the aforementioned failure mode, the environmentally sensitive stresses of the low-speed aircraft in near space are determined;

[0009] Based on the aforementioned environmentally sensitive stress, the test profile was determined;

[0010] The environmentally sensitive stress is applied according to the test profile, and the functions and performance indicators of the low-speed aircraft product are tested during the test.

[0011] Based on the test results of the product's functions and performance indicators, the low-speed aircraft was disassembled, and the design and manufacturing process of the low-speed aircraft product were improved.

[0012] According to the present invention, a reliability testing method for a near-space low-speed aircraft product is provided, wherein determining the composition and structure of the low-speed aircraft product includes:

[0013] Determine the location, structure, function, and type of the low-speed aircraft product.

[0014] According to the reliability testing method for a near-space low-speed aircraft product provided by the present invention, determining the failure modes corresponding to the composition and structure of the product includes:

[0015] Determine the fault detection method corresponding to the composition and structure of the product;

[0016] A fault handling table is established to correspond to the fault detection method and the fault mode, and the fault phenomenon, fault time and test stress data are recorded through the fault handling table.

[0017] According to the present invention, a reliability testing method for a near-space low-speed aircraft product, wherein determining the environmentally sensitive stress of the low-speed aircraft in near space includes:

[0018] The application scenario for the low-speed aircraft is determined, and the application scenario is near space;

[0019] Collect environmental stress-related information about the adjacent space;

[0020] The collected environmental stress-related information was screened to identify the excitation stress that had the greatest impact on reliability and was most effective in triggering potential defects as the environmentally sensitive stress.

[0021] According to the present invention, a reliability testing method for near-space low-speed aircraft products, wherein determining the test profile based on the environmentally sensitive stress includes:

[0022] Determine the development progress and product technical status of the low-speed aircraft;

[0023] If the development progress and product technical status indicate that environmental qualification tests have been completed, then reliability test start conditions are set in conjunction with the environmental qualification test conditions.

[0024] If the development progress and product technical status indicate that no environmental assessment tests have been conducted, then the reliability test start conditions are set based on the stress level that covers environmental assessment tests.

[0025] Based on the aforementioned reliability test initiation conditions, the test profile is determined.

[0026] According to the present invention, a reliability testing method for near-space low-speed aircraft products, wherein determining the test profile based on the reliability test initiation conditions includes:

[0027] Based on the aforementioned reliability test starting conditions, the following tests were conducted sequentially: low temperature and low pressure combined step stress test, high temperature and low pressure test, rapid temperature change test, and vibration step stress test.

[0028] According to the reliability testing method for near-space low-speed aircraft products provided by the present invention, the low-temperature and low-pressure combined step stress test includes:

[0029] Based on the working environment and design specifications of low-speed aircraft products, determine the low-pressure range and the corresponding low-temperature range;

[0030] Within the low-pressure range and the corresponding low-temperature range, the low-speed aircraft is divided into several low-pressure steps based on the altitude experienced during its operation. Each low-pressure step contains several temperatures.

[0031] The low-pressure profile of the entire section is controlled to drop from normal pressure to the minimum pressure. The temperature of each low-pressure step is reduced from the highest temperature in that step to the lowest temperature. When the temperature drops to the lowest temperature, it remains constant. The low pressure is reduced to the next step. This process is repeated until the minimum working pressure and working temperature are reached.

[0032] During the process of reducing the operating pressure and operating temperature to the minimum operating temperature experienced by the low-speed aircraft product, a power-on test is performed.

[0033] According to the present invention, a reliability test method for a near-space low-speed aircraft product is provided, wherein the composition and structure of the low-speed aircraft product includes a power controller;

[0034] The fault modes corresponding to the power controller include: under preset conditions, the power controller cannot work or loses some functions; under preset conditions, the power controller parameter detection results exceed the allowable range of the specification; the mechanical, structural parts or components of the power controller become loose, cracked, broken or damaged.

[0035] The power controller is sensitive to stresses including temperature, air pressure, and vibration.

[0036] Secondly, the present invention also provides a reliability testing apparatus for near-space low-speed aircraft products, comprising:

[0037] The determination module is used to determine the composition and structure of the low-speed aircraft product; determine the failure mode corresponding to the composition and structure of the product; determine the environmentally sensitive stress of the low-speed aircraft in near space under the failure mode; and determine the test profile based on the environmentally sensitive stress.

[0038] The test module is used to apply the environmentally sensitive stress according to the test profile, and to test the function and performance indicators of the low-speed aircraft product during the test.

[0039] An improvement module is used to improve the design and manufacturing process of the low-speed aircraft product based on the test results of the product's functions and performance indicators.

[0040] Thirdly, the present invention also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement a reliability testing method for any of the near-space low-speed aircraft products described above.

[0041] Fourthly, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements a reliability testing method for near-space low-speed aircraft products as described above.

[0042] Fifthly, the present invention also provides a computer program product, including a computer program that, when executed by a processor, implements a reliability testing method for any of the near-space low-speed aircraft products described above.

[0043] This invention provides a reliability testing method, apparatus, and equipment for near-space low-speed aircraft products. The method includes determining the composition and structure of the low-speed aircraft product; determining the failure modes corresponding to the product's composition and structure; determining the environmentally sensitive stresses of the low-speed aircraft in near-space under each failure mode; determining a test profile based on the environmentally sensitive stresses; applying the environmentally sensitive stresses according to the test profile; and testing the functionality and performance indicators of the low-speed aircraft product during the test. Based on the test results of the product's functionality and performance indicators, the design and manufacturing process of the low-speed aircraft product are improved. This method, which specifically determines the test profile for the characteristics of near-space and then conducts the test, improves the accuracy and efficiency of reliability testing results compared to general testing methods. Attached Figure Description

[0044] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0045] Figure 1 This is a flowchart illustrating the reliability testing method for near-space low-speed aircraft products provided in this embodiment;

[0046] Figure 2 This is the low-temperature and low-pressure test profile of the power controller provided in this embodiment;

[0047] Figure 3 This is the high temperature and low pressure test profile of the power controller provided in this embodiment;

[0048] Figure 4 This is the rapid temperature change test profile of the power controller provided in this embodiment;

[0049] Figure 5 This is the vibration function test spectrum of the power controller provided in this embodiment;

[0050] Figure 6 This is the vibration test profile with energy controller provided in this embodiment;

[0051] Figure 7 This is the comprehensive environmental stress test profile provided in this embodiment;

[0052] Figure 8 This is a schematic diagram of the structure of the reliability testing device for near-space low-speed aircraft products provided in this embodiment;

[0053] Figure 9 This is a schematic diagram of the structure of the electronic device provided in this embodiment. Detailed Implementation

[0054] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0055] Figure 1 This is a flowchart illustrating the reliability testing method for near-space low-speed aircraft products provided in this embodiment.

[0056] like Figure 1 As shown, the reliability testing method for near-space low-speed aircraft products provided in this embodiment of the invention mainly includes the following steps:

[0057] 101. Determine the composition and structure of low-speed aircraft products.

[0058] In a specific implementation process, low-speed aircraft refer to aircraft with relatively slow flight speeds, generally below 15 meters per second and Mach numbers less than 0.3. Compared to high-speed aircraft, low-speed aircraft are lighter, more flexible, and less expensive. Their applications are wide-ranging, including remote sensing, security patrols, agricultural spraying, building inspection, and environmental monitoring. The products mentioned in this article all refer to low-speed aircraft products. To accurately simulate the environment experienced by the product, induce potential failures, and identify product defects, it is first necessary to clarify the composition and structure of low-speed aircraft products. This mainly includes the following points:

[0059] Location of low-speed aircraft products: Due to the presence of temperature control devices inside the cabin, the environment experienced by products outside the cabin is significantly harsher. Furthermore, factors such as proximity to heat sources and direct sunlight will affect the distribution of environmental stress experienced by the product. Therefore, it is necessary to clearly define the product's location and divide the area according to the surrounding environmental stress distribution.

[0060] Structure and function of low-speed aircraft products: To facilitate subsequent product failure mode analysis, it is necessary to clarify the structure and function of the product, and based on this, formulate the content and stress level of product testing during subsequent test implementation.

[0061] Types of low-speed aircraft products: For electromechanical products, such as servos and motors, vibration step stress tests are conducted using an electromagnetic vibration table; for electronic products such as power controllers and equipment distributors, vibration step stress tests and comprehensive environmental tests are conducted using an air hammer vibration table.

[0062] Near space refers to the region approximately 20km to 100km above the Earth's surface. This region has unique spatial environmental characteristics, such as low air pressure and high radiation. Taking the power controller on a low-speed near-space aircraft as an example, this section clarifies the product's composition and structure. The power controller is an electromechanical product that operates within the cabin. Its spatial location is evenly distributed along the span of the UAV within the wing. The power controller mainly consists of structural and circuit components. The structural components mainly include the outer shell, base plate, and heat pipes, while the circuit components mainly include power circuits, sampling circuits, and control circuits.

[0063] 102. Determine the failure modes corresponding to the product's composition and structure.

[0064] Identify common failure modes and failure detection methods for the product, develop a failure handling table, and record detailed data such as failure phenomena, timing of discovery, and test stress during subsequent testing.

[0065] Possible failure modes of the power controller include:

[0066] Under preset conditions, the power controller may not work or may lose some of its functions;

[0067] Under preset conditions, the power controller parameter test results exceed the allowable range specified in the standard.

[0068] The mechanical or structural parts or components of the power controller become loose, cracked, broken, or damaged.

[0069] If the power controller experiences an irreversible failure such as structural damage or loss of function, the test should be stopped, the cause of the failure should be identified, the process and design should be improved, and then a regression verification test should be conducted.

[0070] 103. Under fault mode, determine the environmentally sensitive stress of the low-speed aircraft in near space.

[0071] Based on the operating scenarios of low-speed aircraft, information related to the environmental stresses they may experience is collected and analyzed. For low-speed aircraft operating in near-space, common sensitive stress characteristics include vibration, mechanical shock, relative humidity, temperature, solar radiation, wind, altitude (air pressure), and hail. Based on the collected information, the excitation stresses that have the greatest impact on product reliability and are most effective in inducing potential defects are selected as environmentally sensitive stresses for specifying subsequent test profiles.

[0072] For low-speed aircraft operating in near-space environments, the humidity stress commonly used in reliability tests has little impact due to the low air pressure in their working environment. Therefore, the environmentally sensitive stresses are determined to be temperature, vibration, and low air pressure, while the combined effects of low air pressure and temperature changes must also be considered.

[0073] Therefore, the sensitive stresses of a power controller include temperature, air pressure, and vibration.

[0074] 104. Determine the test profile based on environmentally sensitive stress.

[0075] Determine the development schedule and actual technical status of the product. If the product development schedule has completed routine environmental qualification tests, then reasonably set the starting conditions for reliability enhancement tests based on the environmental qualification test conditions. If the product has not yet undergone environmental qualification tests, the design of the starting conditions for reliability enhancement tests should cover the stress levels of the environmental qualification tests. The tests should be completed in the most economical and optimal way, ensuring that the product reliability meets the specified requirements with minimal cost. Specifically, this includes:

[0076] (1) In order to quickly trigger the possible failure of the product, a step stress test of low temperature and low pressure composite was first carried out.

[0077] Based on the product's operating environment and design specifications, determine the low-pressure range (P... min ~P max ) and the corresponding low temperature range (T min ~T max The scope can be appropriately broadened and the assessment tightened as needed to expedite product failure detection.

[0078] Within a defined range of low pressure and low temperature, the area is divided into several low-pressure steps based on the typical altitudes experienced by the low-speed aircraft. Each low-pressure step contains several typical temperatures. The low-pressure profile of the entire section decreases from atmospheric pressure to the lowest pressure P. minEach low-pressure step is maintained in a phase where the temperature decreases from the highest temperature within that step to the lowest temperature. When the temperature decreases to the lowest temperature, it remains constant, and the low pressure decreases to the next step. This process is repeated until the lowest working pressure and working temperature are reached.

[0079] Because the temperature and altitude experienced at different locations on a low-speed aircraft vary, to assess the reliability levels of all typical products as comprehensively as possible, low-pressure and temperature tests can be conducted simultaneously within the same vacuum equipment, according to different low-pressure and temperature levels. When the low-pressure-temperature reaches the operating environment temperature experienced by the product, the corresponding product is powered on for testing; products that do not need to experience this operating environment remain in standby without being powered on for testing. Simultaneously, during the pressurization process, the temperature steps not experienced during depressurization can be supplemented, further improving the efficiency and coverage of reliability testing.

[0080] (2) High temperature and low pressure test

[0081] The principles for developing experimental profiles are the same as those for developing low-temperature, low-pressure profiles.

[0082] (3) Rapid temperature change test.

[0083] Based on the low temperature and low pressure test, the lower limit of the rapid temperature change is determined according to the test data. Then, the upper limit of the product's working temperature is used as the upper limit of the rapid temperature change. In the preliminary step stress test, the upper limit of the working temperature is reduced by 5°C.

[0084] (4) Vibration step stress test.

[0085] Determine the vibration function test spectrum of the product based on its location, and gradually increase the total vibration level to the design limit.

[0086] Specifically, based on the results of the sensitive stress analysis, the power controller is subjected to low-temperature low-pressure step stress test, high-temperature low-pressure step stress test, rapid temperature change test, and vibration step stress test in sequence. If the product passes the step stress test, it is then subjected to low-temperature low-pressure stress limit test, vibration stress limit test, and comprehensive environmental stress test involving temperature-vibration-electric stress coupling in sequence.

[0087] Figure 2 This is the low-temperature, low-pressure test profile of the power controller provided in this embodiment. For example... Figure 2As shown, based on the power controller's operating environment and design specifications, and combined with the results of previous environmental tests, the required low-pressure range for testing is determined to be from atmospheric pressure to 0.1 kPa, and the temperature range is from 0℃ to -90℃. Temperature steps of 0℃, -20℃, -40℃, -55℃, -70℃, -80℃, and -90℃, and low-pressure steps of 12.05 kPa, 7.56 kPa, 1.8 kPa, and 0.1 kPa are set. To efficiently complete a sufficient number of temperature-low-pressure coupling profiles, the pressure is gradually reduced to the lowest pressure to be examined, and three temperature steps are lowered at each low-pressure step. Upon reaching the lowest pressure and temperature, the lowest temperature is maintained while the pressure level is gradually increased to assess whether the product functions normally at each pressure step at the lowest temperature. Finally, when the pressure returns to the highest typical low-pressure step of 12.05 kPa, the temperature is gradually increased to examine the final three typical temperature steps of -40℃, -55℃, and -70℃.

[0088] Figure 3 This is the high-temperature, low-pressure test profile of the power controller provided in this embodiment. For example... Figure 3 As shown, based on the power controller's operating environment and design specifications, and combined with the results of previous environmental tests, the required temperature and pressure ranges for testing were determined. Temperature steps of 15℃, 35℃, 50℃, 60℃, 70℃, 75℃, and 80℃, and low pressure steps of 70.1kPa, 7.56kPa, and 1.8kPa were selected. The pressure was first lowered to the lowest level, and then the low pressure step was gradually increased while simultaneously increasing the temperature step, completing the corresponding tests for the product under different coupling conditions.

[0089] Figure 4 This is the rapid temperature change test profile of the power controller provided in this embodiment. For example... Figure 4 As shown, based on the results of low-temperature low-pressure and high-temperature low-pressure step stress tests, the high-temperature holding conditions and low-temperature holding conditions for rapid temperature change tests are determined. Then, the temperature change rate and the number of cycles are gradually increased to rapidly expose product design and process defects.

[0090] Figure 5 This is the vibration function test spectrum of the power controller provided in this embodiment. For example... Figure 5 As shown, the functional test spectrum of the vibration step stress test is determined based on the working environment and design specifications of the power controller on the aircraft.

[0091] Figure 6 This is the vibration test profile with energy controller provided in this embodiment. For example... Figure 6 As shown, the step size of the vibration step stress is determined according to the design specifications. The holding time of each vibration step is determined according to the operating conditions of the power controller during flight.

[0092] Figure 7 This is the comprehensive environmental stress test profile provided in this embodiment. For example... Figure 7 As shown, the high and low temperature holding conditions of the comprehensive profile are determined based on the high and low temperature operating limits obtained from the tests already conducted. The vibration spectrum adopts the functional test spectrum of the product environmental test. Each temperature cycle corresponds to a vibration level, and the highest vibration level is the vibration stress limit that has been found. In each cycle, the corresponding working conditions are set according to the working state of the product to test until all cycles of testing are completed.

[0093] 105. Apply environmentally sensitive stress according to the test profile, and test the function and performance indicators of the low-speed aircraft product during the test.

[0094] The environmental stress on the product is applied according to the established test profile. During the test, the product's function and performance indicators are tested periodically, and the stress level and product condition are recorded during the test.

[0095] Unlike reliability enhancement tests for low-speed aircraft in the conventional atmosphere, the low-pressure environment of near space is far lower than that of conventional aircraft flight environments, rendering conventional low-pressure chambers inadequate for testing requirements. Vacuum equipment with controllable working fluid temperature is used to simulate the low-pressure environment of near space, and high- and low-temperature stresses can be coupled according to the actual operating environment of the product. Furthermore, to improve testing efficiency, products with similar pressure and temperature environments can be tested simultaneously in a single vacuum chamber during low-pressure testing.

[0096] Specifically, for the power controller, a temperature-low pressure profile simulation of the near-space environment was achieved using a vacuum device, followed by a rapid temperature change profile simulation using a temperature chamber, a vibration step stress profile simulation using an electromagnetic vibration table, and finally, a comprehensive environmental stress profile simulation using a combined temperature chamber and vibration table setup. Before, during, and after the test, the power controller underwent visual and functional inspections, and stress levels and product condition were recorded.

[0097] 106. Based on the test results of the product's functions and performance indicators, improve the design and manufacturing process of low-speed aircraft products.

[0098] The reliability of the product is analyzed based on the test results. If the product fails during the test, the product is disassembled and analyzed based on the failure modes triggered by the test. After the product design or process is improved, the improved product is then subjected to regression verification test.

[0099] The reliability testing method of this invention is designed for adaptability testing and verification of low-speed aircraft in near space. Compared with the traditional unified method, it is more targeted and solves the problem that reliability enhancement testing is not applicable to the special environmental conditions of low temperature and low air pressure in near space. It effectively improves the accuracy of reliability testing for low-speed aircraft in near space.

[0100] Based on the same general inventive concept, this invention also protects a reliability testing device for near-space low-speed aircraft products. The reliability testing device for near-space low-speed aircraft products provided by this invention will be described below. The reliability testing device for near-space low-speed aircraft products described below and the reliability testing method for near-space low-speed aircraft products described above can be referred to in correspondence.

[0101] Figure 8 This is a schematic diagram of the reliability testing device for near-space low-speed aircraft products provided in this embodiment.

[0102] like Figure 8 As shown in the figure, this embodiment provides a reliability testing device for near-space low-speed aircraft products, comprising:

[0103] Module 801 is used to determine the composition and structure of the low-speed aircraft product; determine the failure modes corresponding to the composition and structure of the product; determine the environmentally sensitive stress of the low-speed aircraft in near space under the failure modes; and determine the test profile based on the environmentally sensitive stress.

[0104] Test module 802 is used to apply environmentally sensitive stress according to the test profile and to test the function and performance indicators of the low-speed aircraft product during the test.

[0105] Improvement module 803 is used to improve the design and manufacturing process of low-speed aircraft products based on the test results of the product's functions and performance indicators.

[0106] Figure 9 This is a schematic diagram of the structure of the electronic device provided in this embodiment.

[0107] like Figure 9As shown, the electronic device may include a processor 910, a communication interface 920, a memory 930, and a communication bus 940. The processor 910, communication interface 920, and memory 930 communicate with each other via the communication bus 940. The processor 910 can call logical instructions in the memory 930 to execute a reliability testing method for a near-space low-speed aircraft product. This method includes: determining the composition and structure of the low-speed aircraft product; determining the failure mode corresponding to the composition and structure of the product; determining the environmentally sensitive stress of the low-speed aircraft in near space under the failure mode; determining a test profile based on the environmentally sensitive stress; applying the environmentally sensitive stress according to the test profile; detecting the function and performance indicators of the low-speed aircraft product during the test; and disassembling the low-speed aircraft based on the detection results of the function and performance indicators of the product to improve the design and manufacturing process of the low-speed aircraft product.

[0108] Furthermore, the logical instructions in the aforementioned memory 930 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0109] On the other hand, the present invention also provides a computer program product, which includes a computer program that can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the reliability testing method for near-space low-speed aircraft products provided by the above methods. The method includes: determining the composition and structure of the low-speed aircraft product; determining the failure mode corresponding to the composition and structure of the product; determining the environmentally sensitive stress of the low-speed aircraft in near space under the failure mode; determining a test profile based on the environmentally sensitive stress; applying the environmentally sensitive stress according to the test profile; detecting the function and performance indicators of the low-speed aircraft product during the test; and disassembling the low-speed aircraft based on the detection results of the function and performance indicators of the product to improve the design and manufacturing process of the low-speed aircraft product.

[0110] In another aspect, the present invention also provides a non-transitory computer-readable storage medium storing a computer program thereon. When executed by a processor, the computer program implements a reliability testing method for near-space low-speed aircraft products provided by the methods described above. This method includes: determining the composition and structure of the low-speed aircraft product; determining a failure mode corresponding to the composition and structure of the product; determining the environmentally sensitive stress of the low-speed aircraft in near space under the failure mode; determining a test profile based on the environmentally sensitive stress; applying the environmentally sensitive stress according to the test profile; detecting the function and performance indicators of the low-speed aircraft product during the test; and disassembling the low-speed aircraft based on the detection results of the function and performance indicators of the product to improve the design and manufacturing process of the low-speed aircraft product.

[0111] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0112] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0113] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A reliability testing method for near-space low-speed aircraft products, characterized in that, include: Determine the composition and structure of low-speed aircraft products; Determine the failure modes corresponding to the composition and structure of the product; In the aforementioned failure mode, the environmentally sensitive stresses of the low-speed aircraft in near space are determined; Based on the aforementioned environmentally sensitive stress, the test profile was determined; The environmentally sensitive stress is applied according to the test profile, and the functions and performance indicators of the low-speed aircraft product are tested during the test. Based on the test results of the product's functions and performance indicators, the design and manufacturing process of the low-speed aircraft product are improved.

2. The reliability testing method for near-space low-speed aircraft products according to claim 1, characterized in that, The determination of the composition and structure of the low-speed aircraft product includes: Determine the location, structure, function, and type of the low-speed aircraft product.

3. The reliability testing method for near-space low-speed aircraft products according to claim 1, characterized in that, Determining the failure modes corresponding to the composition and structure of the product includes: Determine the fault detection method corresponding to the composition and structure of the product; A fault handling table is established to correspond to the fault detection method and the fault mode, and the fault phenomenon, fault time and test stress data are recorded through the fault handling table.

4. The reliability testing method for near-space low-speed aircraft products according to claim 1, characterized in that, The determination of the environmentally sensitive stresses of low-speed aircraft in near space includes: The application scenario for the low-speed aircraft is determined, and the application scenario is near space; Collect environmental stress-related information about the adjacent space; The collected environmental stress-related information was screened to identify the excitation stress that had the greatest impact on reliability and was most effective in triggering potential defects as the environmentally sensitive stress.

5. The reliability testing method for near-space low-speed aircraft products according to claim 1, characterized in that, The determination of the test profile based on the environmentally sensitive stress includes: Determine the development progress and product technical status of the low-speed aircraft; If the development progress and product technical status indicate that environmental qualification tests have been completed, then reliability test start conditions are set in conjunction with the environmental qualification test conditions. If the development progress and product technical status indicate that no environmental assessment tests have been conducted, then the reliability test start conditions are set based on the stress level that covers environmental assessment tests. Based on the aforementioned reliability test initiation conditions, the test profile is determined.

6. The reliability testing method for near-space low-speed aircraft products according to claim 5, characterized in that, The determination of the test profile based on the reliability test initiation conditions includes: Based on the aforementioned reliability test starting conditions, the following tests were conducted sequentially: low temperature and low pressure combined step stress test, high temperature and low pressure test, rapid temperature change test, and vibration step stress test.

7. The reliability testing method for near-space low-speed aircraft products according to claim 6, characterized in that, The low-temperature, low-pressure composite step stress test includes: Based on the working environment and design specifications of low-speed aircraft products, determine the low-pressure range and the corresponding low-temperature range; Within the low-pressure range and the corresponding low-temperature range, the low-speed aircraft is divided into several low-pressure steps based on the altitude experienced during its operation. Each low-pressure step contains several temperatures. The low-pressure profile of the entire section is controlled to drop from normal pressure to the minimum pressure. The temperature of each low-pressure step is reduced from the highest temperature in that step to the lowest temperature. When the temperature drops to the lowest temperature, it remains constant. The low pressure is reduced to the next step. This process is repeated until the minimum working pressure and working temperature are reached. During the process of reducing the operating pressure and operating temperature to the minimum operating temperature experienced by the low-speed aircraft product, a power-on test is performed.

8. The reliability test method for near-space low-speed aircraft products according to any one of claims 1-7, characterized in that, The composition and structure of the low-speed aircraft product includes a power controller; The fault modes corresponding to the power controller include: under preset conditions, the power controller cannot work or loses some functions; under preset conditions, the power controller parameter detection results exceed the allowable range of the specification; the mechanical, structural parts or components of the power controller become loose, cracked, broken or damaged. The power controller is sensitive to stresses including temperature, air pressure, and vibration.

9. A reliability testing device for near-space low-speed aircraft products, characterized in that, include: The determination module is used to determine the composition and structure of low-speed aircraft products; Determine the failure modes corresponding to the composition and structure of the product; In the aforementioned failure mode, the environmentally sensitive stresses of the low-speed aircraft in near space are determined; Based on the aforementioned environmentally sensitive stress, the test profile was determined; The test module is used to apply the environmentally sensitive stress according to the test profile, and to test the function and performance indicators of the low-speed aircraft product during the test. An improvement module is used to improve the design and manufacturing process of the low-speed aircraft product based on the test results of the product's functions and performance indicators.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the program, it implements the reliability testing method for the near-space low-speed aircraft product as described in any one of claims 1 to 8.

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