Aircraft control surface torsion element accelerated storage test system and method

Abstract

The invention relates to the technical field of element detection, and provides an aircraft control surface torsion element accelerated storage test system which comprises a temperature control box. A single side of the temperature control box is open and is provided with a temperature control box door plate which can be opened and closed, a torsion testing device used for installing a torsion element is fixed in the temperature control box, and an angular displacement sensor used for measuring the torsion angle of the torsion element and a torque sensor used for measuring the torque of the torsion element are installed on the torsion testing device. The invention also provides an aircraft control surface torsion element accelerated storage test method. The method comprises the following steps: S1, clamping; s2, twisting is carried out; s3, measuring; and S4, analyzing. According to the method, the load condition of the aerospace craft control surface torsion element under the combined action of mechanical stress and temperature stress can be processed, the storage life of the torsion element can be obtained in a short time, and then the forward design of a product is supported.

Description

Technical Field

[0001] The invention relates to an accelerated storage test system and method for a torsion element of an aircraft control surface, belonging to the technical field of element detection. Background Art

[0002] As a dynamic element for deployment, the torsion element of the control surface of aerospace vehicle plays the role of storing energy and controlling movement. Its storage reliability plays a vital role in the safe service of the spacecraft. During the storage process, the torsion element will undergo a certain elastic deformation under the action of constant stress, store elastic potential energy, and put the control surface in a folded state; after the external load is removed, the elastic potential energy in the torsion element is converted into mechanical energy again, driving the folding rudder to deploy in a very short time (usually within tens of milliseconds), so that the spacecraft forms a predetermined aerodynamic shape. In this process, the torsion element plays the role of storing energy and controlling movement. If the torsion element fails during storage, its elastic force will gradually decrease, resulting in the inability to twist the control surface to the specified position, affecting the safe service of the spacecraft. Therefore, studying the storage reliability of torsion elements can provide strong technical support for the storage life assessment of equipment and give full play to the strategic and economic benefits of aerospace equipment.

[0003] At the beginning of the development of my country's aerospace industry, the storage failure problem of spacecraft control surface torque components was basically not paid attention to in engineering, and there were no large quantities of stored spacecraft torque components at that time. However, with the development of engineering technology and the improvement of spacecraft performance requirements, the storage life assessment of spacecraft control surface torque components has become a technical problem that needs to be solved urgently.

[0004] Currently, one solution to this problem is to use a long storage test. This method stores the aerospace control surface test piece and the aircraft together in natural storage to obtain the storage life of the torsion element. However, since the storage period of the torsion element is between 10 and 20 years, which is extremely time-consuming, the long storage test method cannot obtain the storage life in a short period of time, and this method cannot support the forward design of the product.

[0005] In addition, there are some solutions for accelerated storage, but most of them are for accelerated storage methods or devices with only temperature stress storage environment, such as "Electronic Product Accelerated Storage Life Test Evaluation System", "An Electronic Product Accelerated Storage Life Evaluation Method" and "A Cabin Accelerated Storage Method Based on Arrhenius Equation". This type of solution uses Arrhenius equation as the acceleration model, with temperature as the only controlled variable. During the storage process, the torsion element of the control surface of the aerospace vehicle is subject to the combined effects of temperature stress and mechanical stress. The mechanical stress is sometimes close to the torsional strength of the torsion element itself, and coupled with the influence of temperature stress, its stress relaxation mechanism and failure mechanism are different from those of pure temperature stress. The Arrhenius equation is not suitable for the storage condition of the torsion element of the aerospace vehicle, and it is difficult to handle the load condition of the structure under the combined effect of mechanical stress and temperature stress.

[0006] In summary, the current long-storage test method for evaluating the storage life of spacecraft control surface torsion elements cannot obtain the storage life of torsion elements in the short term, nor can it support product forward design; and in terms of accelerated storage, the existing solutions are not suitable for the long-term storage of spacecraft torsion elements, and it is difficult to handle the load conditions of torsion elements under the combined effects of mechanical stress and temperature stress. Summary of the invention

[0007] In order to solve the above technical problems, the present invention provides an accelerated storage test system and method for aircraft control surface torque elements. The accelerated storage test system and method for aircraft control surface torque elements can realize the storage life evaluation of aerospace vehicle control surface torque elements under constant mechanical stress and variable temperature environment, support the forward design of the storage life of aerospace vehicle control surface torque elements, and provide technical support for the remaining life estimation of long-term storage torque elements.

[0008] The present invention is achieved through the following technical solutions.

[0009] The invention provides an accelerated storage test system for a torsion element of an aircraft control surface, comprising a temperature control box; the temperature control box has a single-sided opening on the side and is provided with a temperature control box door panel that can be opened and closed; a torque test device for installing the torsion element is fixed in the temperature control box; an angular displacement sensor for measuring the torsion angle of the torsion element and a torque sensor for measuring the torque of the torsion element are installed on the torque test device; the angular displacement sensor and the torque sensor are electrically connected to a data acquisition system; and the data acquisition system is placed outside the temperature control box.

[0010] A temperature sensor is mounted on the inner wall of the temperature control box, and a temperature control panel is mounted on the outer wall of the temperature control box. The temperature control panel is electrically connected to the temperature sensor and displays the temperature value collected by the temperature sensor.

[0011] The temperature sensors are installed on multiple inner walls of the temperature control box.

[0012] The torque testing device consists of a front frame component and a rear frame component that are relatively installed. The position between the front frame component and the rear frame component is used to install the torque element. A driving device is installed at the end of the front frame component to drive the installed torque element to rotate; the front frame component is fixed to a base plate, and the rear frame component is installed on a sliding base. A linear guide rail is fixed to the base plate. The sliding base is placed on the base plate and cooperates with the linear guide rail to move along the linear guide rail. The installation direction of the linear guide rail is consistent with the installation direction of the torque element.

[0013] A limit block is fixed on the bottom plate at the end of the linear guide rail; a self-locking cylinder is installed on the sliding base for self-locking.

[0014] The bottom of the front frame component is fixed to the end of the bottom plate through the head frame component pad.

[0015] The present invention also provides an accelerated storage test method for a torsion element of an aircraft control surface, comprising the following steps:

[0016] S1. Clamping: adjust the position of the rear frame component and clamp the torsion element between the front frame component and the rear frame component;

[0017] S2, twisting: start the driving device to drive the torsion element to twist;

[0018] S3, measurement: during the torsion process of the torsion element, the torsion angle and torque values ​​are measured in real time based on the angular displacement sensor and the torque sensor, and the temperature within 1 is obtained in real time based on the temperature sensor;

[0019] S4. Analysis: Based on the values ​​of torsion angle, torque and temperature, calculate the relationship between temperature stress, mechanical stress and angular displacement.

[0020] The step S4 specifically comprises the following steps:

[0021] S41, determining the type: determining the stress type according to the storage profile of the torsion element;

[0022] S42, select model: select acceleration model according to stress type;

[0023] S43, determine the limit: determine the upper limit of stress according to the material properties, and load it through the step-reducing stress loading method;

[0024] S44, determining the model: establishing a storage life characteristic accelerated storage test model through an accelerated test according to the accelerated model;

[0025] S45. Life evaluation: Based on the storage life characteristic accelerated storage test model, the storage life of the torque element is calculated using the extrapolation method.

[0026] In step S41, the stress types include "temperature stress", "mechanical stress", and "coexistence of temperature stress and mechanical stress"; in step S42, if the stress type is "temperature stress", the Arrhenius model is selected; if the stress type is "mechanical stress", the inverse power law model is selected; if the stress type is "coexistence of temperature stress and mechanical stress", the Irene model is selected.

[0027] In step S44, there are five loading modes of the accelerated test: step stress, sequential stress, constant stress, sequential stress reduction and step stress reduction.

[0028] The beneficial effects of the present invention are that it can handle the load conditions of the torsion elements of the control surface of a spacecraft under the combined effects of mechanical stress and temperature stress, and can obtain the storage life of the torsion elements in a short period of time, thereby supporting the forward design of the product; it is proposed for the storage life profile of the torsion elements of the control surface of a spacecraft, and compared with the existing methods, it has the advantages of high efficiency and high precision. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 is a schematic diagram of the structure of at least one embodiment of the present invention;

[0030] Figure 2 yes Figure 1 Schematic diagram of the structure of the medium torque test device;

[0031] Figure 3 yes Figure 2 A top view of

[0032] Figure 4 yes Figure 2 Side view of

[0033] Figure 5 It is a schematic diagram of stress changes in an accelerated test loading method in at least one embodiment of the present invention.

[0034] In the figure: 1-torque testing device, 11-torque element, 12-angular displacement sensor, 13-torque sensor, 14-driving device, 15-front frame component, 16-head frame component pad, 17-bottom plate, 18-rear frame component, 19-self-locking cylinder, 110-sliding base, 111-linear guide rail, 112-limiting block, 2-temperature control box, 21-temperature control box door panel, 22-temperature sensor, 23-temperature control panel, 3-data acquisition system. DETAILED DESCRIPTION

[0035] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0036] Example 1

[0037] like Figures 1 to 4 An aircraft control surface torsion element accelerated storage test system shown in the figure includes a temperature control box 2; the temperature control box 2 has a single-sided opening on the side and a temperature control box door panel 21 that can be opened and closed, a torque testing device 1 for installing a torsion element 11 is fixed in the temperature control box 2, an angular displacement sensor 12 for measuring the torsion angle of the torsion element 11 and a torque sensor 13 for measuring the torque of the torsion element 11 are installed on the torque testing device 1, the angular displacement sensor 12 and the torque sensor 13 are electrically connected to a data acquisition system 3, and the data acquisition system 3 is placed outside the temperature control box 2.

[0038] Example 2

[0039] Consistent with Example 1, and further optimized in details, a temperature sensor 22 is installed on the inner wall of the temperature control box 2, and a temperature control panel 23 is installed on the outer wall of the temperature control box 2. The temperature control panel 23 is electrically connected to the temperature sensor 22 and displays the temperature value collected by the temperature sensor 22.

[0040] Furthermore, the temperature sensors 22 are installed on multiple inner walls of the temperature control box 2 .

[0041] Furthermore, the torque testing device 1 is composed of a front frame component 15 and a rear frame component 18 that are relatively installed. The position between the front frame component 15 and the rear frame component 18 is used to install the torsion element 11. A driving device 14 is installed at the end of the front frame component 15 to drive the installed torsion element 11 to rotate; the front frame component 15 is fixed to the base plate 17, and the rear frame component 18 is installed on a sliding base 110. A linear guide 111 is fixed on the base plate 17. The sliding base 110 is placed on the base plate 17 and cooperates with the linear guide 111 to move along the linear guide 111. The installation direction of the linear guide 111 is consistent with the installation direction of the torsion element 11.

[0042] Furthermore, a limit block 112 is fixed at the end of the linear guide rail 111 on the bottom plate 17; and a self-locking cylinder 19 is installed on the sliding base 110 for self-locking.

[0043] Furthermore, the bottom of the front frame component 15 is fixed to the end of the bottom plate 17 through the head frame component pad 16.

[0044] Example 3

[0045] An accelerated storage test method for a torsion element of an aircraft control surface implemented based on Embodiment 1 and Embodiment 2 comprises the following steps:

[0046] S1, clamping: adjusting the position of the rear frame component 18, and clamping the torsion element 11 between the front frame component 15 and the rear frame component 18;

[0047] S2, twisting: starting the driving device 14 to drive the torsion element 11 to twist;

[0048] S3, measurement: during the torsion process of the torsion element 11, the torsion angle and torque values ​​are measured in real time based on the angular displacement sensor 12 and the torque sensor 13, and the temperature inside 1 is obtained in real time based on the temperature sensor 22;

[0049] S4. Analysis: Based on the values ​​of torsion angle, torque and temperature, calculate the relationship between temperature stress, mechanical stress and angular displacement.

[0050] Example 4

[0051] Consistent with Example 3, and further optimized in details, step S4 specifically includes the following steps:

[0052] S41, determining the type: determining the stress type according to the storage profile of the torsion element 11;

[0053] S42, select model: select acceleration model according to stress type;

[0054] S43, determine the limit: determine the upper limit of stress according to the material properties, and load it through the step-reducing stress loading method;

[0055] S44, determining the model: establishing a storage life characteristic accelerated storage test model through an accelerated test according to the accelerated model;

[0056] S45. Evaluate the lifespan: Based on the storage life characteristics accelerated storage test model, the storage lifespan of the torsion element 11 is calculated using the extrapolation method.

[0057] Furthermore, in step S41, the stress types include "temperature stress", "mechanical stress", and "coexistence of temperature stress and mechanical stress"; in step S42, if the stress type is "temperature stress", the Arrhenius model is selected; if the stress type is "mechanical stress", the inverse power law model is selected; if the stress type is "coexistence of temperature stress and mechanical stress", the Irene model is selected.

[0058] Furthermore, in step S44, there are five loading modes of the accelerated test, namely, step stress, sequential stress, constant stress, sequential stress reduction and step stress reduction.

[0059] Example 5

[0060] In combination with the above-mentioned embodiment 1 and embodiment 2, a torque element 11 is installed on the torque testing device 1, which is the workpiece to be tested; the main structure of the torque testing device 1 is as follows Figure 2As shown, its functional elements also include an angular displacement sensor 12 and a torque sensor 13, which are responsible for measuring the torsion angle and torque of the torsion element respectively, and transmit them to the data acquisition system 3. The torque test device is composed of a drive device 14, a front frame component 15, a head frame component pad 16, a bottom plate 17, a rear frame component 18, a self-locking cylinder 19, a sliding base 110, a linear guide 111, and a limit block 112. The torsion element 11 is clamped between the front frame component 16 and the rear frame component 18, as shown in the attached figure. Figure 2 As shown. The driving device 14 contains a reduction device, which transmits motion to the front frame component through axial rotation to apply torque to the torsion element 11 (the workpiece to be measured). The rear frame component 18 is connected to the sliding base 110 by bolts and can slide back and forth on the linear guide rail 111 to adjust the clamping distance according to the length of the torsion element. The self-locking cylinder 19 controls the locking and unlocking of the sliding base 110 to fix the clamping position of the torsion element. The limit block 112 is used to limit the maximum movement position of the sliding base 110.

[0061] The temperature control box 2 mainly includes a temperature control box door panel 21, a temperature sensor 22 and a temperature control panel 23, in addition to the box body itself. The temperature sensor 22 mainly functions to collect the temperature conditions inside the box from different positions, and the temperature control panel mainly functions to adjust the temperature inside the box according to the temperature design requirements.

[0062] The data acquisition system 3 collects the temperature in the box body, the twisted angle of the torsion element 11, and the torque used for twisting through the angular displacement sensor 12, the torque sensor 13 and the temperature sensor 22.

[0063] Example 6

[0064] In combination with the above-mentioned embodiment 3 and embodiment 4, the torsion element 1-1 is clamped between the front frame component 1-5 and the rear frame component 1-8 of the torque test device, and then the driving device 1-4 is energized. The driving device drives the torsion element 1-1 to twist through the built-in speed reduction device. During the twisting process, the angular displacement sensor 1-2 and the torque sensor 1-3 measure the torsion angular displacement and torque values ​​in real time, thereby obtaining the corresponding relationship between the torque and the angular displacement. Among them, the data acquisition system 3 can control the data sampling frequency through the built-in computer program. In the accelerated storage test, after loading through the driving device 1-4, the torsion element 1-1 is loaded on the torque test device 1, and then kept in the loaded state and moved to the temperature control box 2, and the ambient temperature is adjusted through the temperature control panel 2-3, and the ambient temperature is detected through the temperature sensor 2-2, and transmitted back to the data acquisition system 3 together with the angular displacement and torque, thereby obtaining the relationship between temperature stress, mechanical stress (torque) and angular displacement.

[0065] The first step of "determining the stress type" must be determined based on the storage profile of the torsion element of the control surface of the aerospace vehicle. Temperature stress, mechanical stress, or both temperature and mechanical stress can be selected.

[0066] The second step, "Selecting the Acceleration Model", should select a suitable acceleration model based on the stress selected in the first step. The selection principles of the acceleration model are as follows:

[0067] 1. If the storage section only has temperature stress, it is recommended to use the Arrhenius model. s Model), see formula (1).

[0068]

[0069] Among them, V S is the stress relaxation rate, γ is a specific constant, E is the activation energy (eV), T is the thermodynamic temperature (K), k is the Boltzmann constant (k = 8.6 × 10- 5 eV / K).

[0070] 2. If the storage profile only has mechanical stress, it is recommended to use the inverse power law model, see formula (2).

[0071] VS = γ·Sn(2)

[0072] Among them, V S , γ and formula (1) have the same meaning, S is the stress level, and n is a constant.

[0073] 3. If there are both temperature stress and mechanical stress, the Eyring model is recommended, see formula (3).

[0074]

[0075] Among them, V S is the stress relaxation rate, ψ, χ, and n are unknown constants, k is the Boltzmann constant, and T and S are temperature stress and mechanical stress, respectively.

[0076] The third step, "determine the stress limit", requires the determination of the upper and lower limits of stress respectively. The upper and lower limits of stress should be determined by combining the material stress characteristics through a bottom-up test. Specifically, the upper limit of stress can be determined based on the material characteristics and engineering experience, and then the lower limit of stress can be determined by loading in a step-reducing stress loading mode until the test termination condition (such as a sufficient number of product failures or the bottom-up test samples are used up).

[0077] The fourth step, "determine the parameters of the accelerated model", is to determine the constants of the model selected in the third step above through accelerated testing, so as to establish an accelerated storage test model that meets the storage life characteristics of the product. There are five loading methods for accelerated testing: step stress, sequential stress, constant stress, sequential stress reduction and step stress reduction. Figure 5 shown.

[0078] The fifth step, "Evaluate the storage life", is to use the accelerated storage test model established in the fourth step to calculate the product storage life by extrapolation. You can also refer to the mathematical processing method in the appendix of the Q / QJB 13502-2019 standard to convert the storage life.

[0079] Therefore, the present invention first determines the stress type according to the product storage profile, then determines the stress limit according to the product material characteristics and the bottom test, and then selects a suitable acceleration model according to the stress type involved in the storage profile, and conducts the test through the accelerated storage test device provided by the present invention to determine the acceleration model parameters, and evaluates the product storage life. This method is proposed for the storage profile of the torsion element of the control surface of the aerospace vehicle, fills the technical gap in the storage life evaluation of the torsion element in terms of test technology, and solves the problem of rapid life evaluation of the torsion element. This method is suitable for the situation where the torsion element is only subjected to temperature stress or environmental stress, and is also suitable for the actual storage environment where the torsion element is subjected to the combined action of temperature stress and environmental stress.

[0080] Compared with the long storage test method, the present invention can complete the storage life evaluation of the spacecraft control surface torque element within a few months, which is time-saving and efficient, and the storage life can be obtained in a short period of time; the preliminary design of the product is often completed within a few months. The accelerated storage test system and test method of the spacecraft control surface torque element disclosed in the present invention can support the forward design of the product.

[0081] Compared with the existing accelerated storage methods, the present invention invents a torque testing device that can simultaneously apply and detect temperature stress and environmental stress in response to the storage environment of the torsion elements of the control surfaces of spacecraft, and adopts an accelerated test model that can simultaneously consider temperature stress and environmental stress. It can simultaneously consider the combined effects of temperature stress and mechanical stress, and solves the problem that the existing accelerated storage methods are difficult to accurately evaluate the accelerated storage life of the torsion elements of spacecraft.

Claims

1. An accelerated storage test system for a torsion element of an aircraft control surface, comprising a temperature control box (2), characterized in that: The temperature control box (2) is open on one side and has a temperature control box door panel (21) that can be opened and closed. A torque testing device (1) for installing a torque element (11) is fixed inside the temperature control box (2). An angular displacement sensor (12) for measuring the torsion angle of the torque element (11) and a torque sensor (13) for measuring the torque of the torque element (11) are installed on the torque testing device (1). The angular displacement sensor (12) and the torque sensor (13) are electrically connected to a data acquisition system (3). The data acquisition system (3) is placed outside the temperature control box (2).

2. The aircraft control surface torque element accelerated storage test system according to claim 1, characterized in that: The temperature control box (2) is provided with a temperature sensor (22) on the inner wall thereof, and a temperature control panel (23) is provided on the outer wall thereof; the temperature control panel (23) is electrically connected to the temperature sensor (22) and displays the temperature value collected by the temperature sensor (22).

3. The aircraft control surface torque element accelerated storage test system according to claim 2, characterized in that: The temperature sensors (22) are installed on multiple inner walls of the temperature control box (2).

4. The aircraft control surface torque element accelerated storage test system according to claim 1, characterized in that: The torque testing device (1) is composed of a front frame component (15) and a rear frame component (18) which are relatively installed. The position between the front frame component (15) and the rear frame component (18) is used to install the torque element (11). The end of the front frame component (15) is installed with a driving device (14) for driving the installed torque element (11) to rotate. The front frame component (15) is fixed to a base plate (17), and the rear frame component (18) is installed on a sliding base (110). A linear guide rail (111) is fixed on the base plate (17). The sliding base (110) is placed on the base plate (17) and cooperates with the linear guide rail (111) to move along the linear guide rail (111). The installation direction of the linear guide rail (111) is consistent with the installation direction of the torque element (11).

5. The aircraft control surface torque element accelerated storage test system according to claim 1, characterized in that: A limit block (112) is fixed on the bottom plate (17) at the end of the linear guide rail (111); and a self-locking cylinder (19) is installed on the sliding base (110) for self-locking.

6. The aircraft control surface torque element accelerated storage test system according to claim 1, characterized in that: The bottom of the front frame component (15) is fixed to the end of the bottom plate (17) through the head frame component pad (16).

7. An accelerated storage test method for aircraft control surface torque elements, characterized in that: The following steps are involved: S1, clamping: adjusting the position of the rear frame component (18) and clamping the torsion element (11) between the front frame component (15) and the rear frame component (18); S2, twisting: starting the driving device (14) to drive the torsion element (11) to twist; S3, measurement: during the torsion process of the torsion element (11), the torsion angle and torque values ​​are measured in real time based on the angular displacement sensor (12) and the torque sensor (13), and the temperature inside 1 is obtained in real time based on the temperature sensor (22); S4. Analysis: Based on the values ​​of torsion angle, torque and temperature, calculate the relationship between temperature stress, mechanical stress and angular displacement.

8. The accelerated storage test method for aircraft control surface torque elements according to claim 7, characterized in that: The step S4 specifically comprises the following steps: S41, determining the type: determining the stress type according to the storage cross section of the torsion element (11); S42, select model: select acceleration model according to stress type; S43, determine the limit: determine the upper limit of stress according to material properties, and load it through step-reduced stress loading; S44, determining the model: establishing a storage life characteristic accelerated storage test model through an accelerated test according to the accelerated model; S45. Evaluate the life: Based on the storage life characteristic accelerated storage test model, the storage life of the torsion element (11) is calculated by using the extrapolation method.

9. The accelerated storage test method for aircraft control surface torque elements according to claim 8, characterized in that: In step S41, the stress types include "temperature stress", "mechanical stress", and "coexistence of temperature stress and mechanical stress"; in step S42, if the stress type is "temperature stress", the Arrhenius model is selected, if the stress type is "mechanical stress", the inverse power law model is selected, and if the stress type is "coexistence of temperature stress and mechanical stress", the Irene model is selected.

10. The accelerated storage test method for aircraft control surface torque elements according to claim 8, characterized in that: In step S44, there are five loading modes of the accelerated test: step stress, sequential stress, constant stress, sequential stress reduction and step stress reduction.

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