Experimental equipment for simulating flight motion overload

Abstract

The invention relates to the field of aircraft devices, in particular to test equipment of an aircraft device. The invention aims to provide the experimental equipment for simulating flight motion overload, the motor drives the test piece to perform horizontal circular motion, and the generated centrifugal acceleration is utilized to accurately simulate flight overload. Independent and safe testing of a single device is realized, the single cost is obviously reduced, and convenient reproduction of an overload environment is realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of flight devices, in particular to the test equipment of flight devices. BACKGROUND

[0002] In the field of flight aviation equipment, flight devices are core functional components in flight equipment, such as sensors, fuses, control cabin sections, etc. These devices need to withstand and respond to complex mechanical environments during the flight of the equipment, such as 3g to 50g overload, and their performance and reliability directly determine the final efficiency of the flight equipment. Therefore, independent and accurate ground simulation testing of such devices is crucial during the development stage.

[0003] Motion overload testing is an important part of the simulation testing mentioned above, which is a test method for verifying the working state, performance indicators and reliability of the above flight devices in the acceleration environment generated during flight by simulation.

[0004] In the prior art, the main verification methods for implementing such testing are mounting flight tests and shooting tests. Among them, the mounting flight test is to mount the complete ammunition with the test device on the test aircraft, generate an overload environment through the specific flight maneuvers of the aircraft, and thus examine the performance of the device. The shooting test is to perform a launch to test whether the functions of the device are normal in the real flight trajectory.

[0005] Both methods are to obtain overload environment data by directly participating in or completing a real flight process, and the essence is to comprehensively verify the entire weapon system.

[0006] However, these two testing schemes have obvious defects. The testing cost is high and the economy is poor. The cost of a single mounting flight test and the cost of a shooting test are very high. Since it is a system-level test, any minor changes to the device require repeating the entire expensive process, which places a heavy economic burden on research projects. On the other hand, the test results are affected by various uncontrollable factors such as weather conditions and carrier performance, resulting in poor test data reproducibility and difficulty in precise performance evaluation and optimization. SUMMARY

[0007] The purpose of the present application is to provide an experimental device for simulating flight motion overload, which drives the test piece to move horizontally in a circle by a motor, and accurately simulates flight overload by using the generated centrifugal acceleration. Independent and safe testing of a single device is achieved, the single cost is significantly reduced, and the convenient reproduction of the overload environment is achieved.

[0008] The present application is realized by the following technical scheme: an experimental device for simulating flight motion overload, comprising a test frame, a driving device and a clamping device for clamping a component to be tested.

[0009] The driving device comprises a body mounted on the test frame and an output shaft connected with the body;

[0010] The clamping device comprises a base plate and a fixing clamp mounted on the base plate,

[0011] A connecting shaft hole is formed on the base plate and matched with the output shaft, and the base plate is configured to rotate under the driving of the output shaft.

[0012] As a preferred embodiment of the present application, the fixing frame is two sets, an adjusting groove is formed on the base plate, and the two sets of fixing clamps are configured to slide along the adjusting groove to adjust the position away from the connecting shaft hole.

[0013] As a preferred embodiment of the present application, the fixing frame comprises a sliding seat connected with the adjusting groove and a containing ring cavity formed in the sliding seat, an open ring is arranged in the containing ring cavity, and a locking bolt for locking the open ring is connected to the sliding seat.

[0014] According to the experimental equipment for simulating flight motion overload according to claim or or, further comprising an adapter plate, the adapter plate is fixedly connected to the lower surface of the base plate, an end face bearing is arranged below the adapter plate, and the output shaft passes through the end face bearing.

[0015] As a preferred embodiment of the present application, the rotating surface of the end face bearing is in contact with the adapter plate, and the static surface of the end face bearing is in contact with the test frame.

[0016] As a preferred embodiment of the present application, a pad plate is arranged on the test frame, and the static surface of the end face bearing is in contact with the pad plate.

[0017] As a preferred embodiment of the present application, the adapter plate is circular.

[0018] As a preferred embodiment of the present application, the test frame comprises a table top and a support, and the support comprises a leveling part.

[0019] As a preferred embodiment of the present application, a main control box is arranged on the base plate, and the main control box comprises a shell and a controller for adjusting the rotation parameters of the driving device.

[0020] As a preferred embodiment of the present application, a human-computer interaction device is further arranged in communication connection with the main control box.

[0021] In summary, the present application has the following advantages:

[0022] 1. A low-cost and convenient-to-operate ground experimental equipment is provided, which can accurately simulate flight overload through the centrifugal force generated by the rotation of the clamping device, thereby eliminating the dependence on expensive and dangerous live ammunition or hanging flight tests, and significantly reducing the test cost and risk.

[0023] 2. By setting the fixed frame that can slide along the adjusting groove, the continuous adjustment of the rotation radius of the test piece is realized. By introducing the rotation radius as a key variable into the overload control and combining the rotation speed adjustment, the range and accuracy of the overload simulation are greatly widened, and the differentiated requirements of different test pieces for the overload value are met.

[0024] 3. The cooperation structure of the split ring and the ring cavity is adopted, and the locking bolt is configured. The uniform and adjustable radial clamping force can be applied to the cylindrical test piece, ensuring that the test piece is firm and does not loosen during high-speed rotation, and at the same time, it is suitable for test pieces of different diameters, improving the applicability of the equipment.

[0025] 4. The adapter plate effectively transmits torque, and the face bearing is specially used to bear the vertical load of the rotating system, effectively protecting the output shaft of the driving device from radial bending moment, improving the reliability and life of the equipment operation.

[0026] 5. The rotating surface of the face bearing and the adapter plate are in contact, and the static surface and the test stand are in contact. The reliable separation and load transmission of the rotating part and the static part are realized, ensuring that the driving device only bears the torque, and the test stand bears the main gravity, optimizing the stress distribution and ensuring the stability of rotation.

[0027] 6. The gasket provides a local high-precision installation reference surface for the face bearing, ensuring the installation flatness and levelness of the bearing, thereby significantly improving the rigidity and stability of the entire rotating support system.

[0028] 7. The adapter plate is circular, the mass distribution of the rotating part is more uniform, the dynamic balance performance is optimized from the structure, the vibration and noise that may be generated due to mass eccentricity during high-speed rotation are effectively reduced, and the stability of the experimental equipment operation and the accuracy of the test data are ensured.

[0029] 8. The test stand has a horizontal leveling function, providing a stable and accurately leveled foundation for the entire equipment, ensuring that the rotation axis is perpendicular to the direction of gravity, eliminating additional lateral forces caused by foundation inclination from the source, and ensuring the accuracy of the centrifugal overload direction and the reproducibility of the experiment.

[0030] 9. The main control box has a built-in controller. The test piece rotates synchronously and outputs the simulated flight signal in real time, realizing the full-process working state simulation of the test piece in the real overload environment, improving the realism and effectiveness of the test, and enabling precise control of the driving device. BRIEF DESCRIPTION OF DRAWINGS

[0031] Figure 1 shows a perspective view of an embodiment;

[0032] Figure 2 shows Figure 1a side sectional view of the device;

[0033] Figure 3 a schematic view of the clamping device is shown. Figure 2 a detail enlargement of A in

[0034] Figure 4 a schematic view of the clamping device is shown.

[0035] In the figure: 1, test frame, 11, table top, 12, foot, 2, clamping device, 21, bottom plate, 22, shaft hole, 23, adjusting groove, 24, fixing clamp, 241, sliding seat, 242, split ring, 243, ring cavity, 3, main control box, 4, driving device, 41, body, 42, output shaft, 5, backing plate, 6, end face bearing, 7, adapter plate. DETAILED DESCRIPTION

[0036] The present application will be further described below in conjunction with the accompanying drawings of the embodiments.

[0037] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present application.

[0038] The present embodiments are merely explanatory of the present application, and are not a limitation of the present application, and those skilled in the art can make modifications to the present embodiments without creative contribution, as long as the modifications are within the scope of the claims of the present application.

[0039] The following description provides examples, and does not limit the scope, applicability, or examples set forth in the claims. Changes can be made in the function and arrangement of elements described without departing from the scope of the description. Various examples can omit, substitute, or add various procedures or components as appropriate. For instance, the methods described can be performed in an order different than described, and various steps can be added, omitted, or combined. Also, features described with respect to some examples can be combined in other examples.

[0040] The present embodiments provide an experimental device for simulating flight motion overload, which has a whole structure as shown in Figure 1 The device generates centrifugal acceleration through horizontal circular motion to accurately simulate flight overload environment. The following describes the implementation of the technical solutions in the order of device assembly, test piece installation, running test, and stopping.

[0041] Firstly, the test stand 1 is placed on a horizontal ground, which is composed of a platform 11 and a support 12 equipped with leveling parts, such as adjustable feet. By adjusting the height of the feet, the platform 11 is ensured to be in a horizontal state. The leveling ensures that the rotation axis is perpendicular to the direction of gravity, eliminating additional lateral forces caused by the inclination of the foundation from the source, ensuring the accuracy of the direction of centrifugal overload, and improving the reproducibility and reliability of the experiment.

[0042] After leveling, the body 41 of the driving device 4 is fixedly installed on the platform 11 of the test stand 1, and the output shaft 42 extends vertically upward. Exemplarily, the driving device 4 is a motor, and the output shaft 42 is the motor output shaft.

[0043] Subsequently, the clamping device and the adapter component are installed.

[0044] The clamping device 2 is used to fix the component to be tested, which has a structure as shown in Figure 4 , including a bottom plate 21, a fixed clamp 24, and an adjusting groove 23. The center of the bottom plate 21 is provided with a shaft hole 22 matched with the output shaft 42 of the driving device 4. The adapter plate 7 is fixedly connected to the lower surface of the bottom plate 21.

[0045] Exemplarily, the adapter plate 7 has a circular structure. It can ensure uniform mass distribution during high-speed rotation, thereby minimizing air resistance and centrifugal force imbalance caused by shape asymmetry, avoiding vibration and noise. Non-circular structures, such as squares, will generate a large imbalance force. At the same time, the adapter plate 7 needs to have sufficient thickness to withstand the torque from the motor shaft and transmit it to the entire load above, while itself cannot be bent and deformed. It can use high-quality carbon structural steel, such as 45 steel, or alloy structural steel. The material has high strength and stiffness, which can ensure that plastic deformation or fracture does not occur when transmitting large torque.

[0046] The adapter plate 7 is provided below with a face bearing 6, which is a bearing element specially used to bear axial load. In this device, it is mainly responsible for handling the vertical force generated by the rotating system, thereby protecting the output shaft 42 of the driving device 4 from unnecessary radial bending moments.

[0047] The rotating surface of the face bearing 6 directly abuts the lower surface of the adapter plate 7, while the stationary surface abuts the platform 11 of the test stand 1 through the backing plate 5. This design realizes the physical separation of rotating components, such as the clamping device 2 and the adapter plate 7, from stationary components, such as the test stand 1. Figure 2 and Figure 3As shown, when the output shaft 42 drives the base plate 21 to rotate, the end face bearing 6 specially bears the axial load caused by the weight and centrifugal force of the rotating system, while the output shaft 42 of the driving device 4 only needs to transmit torque and does not need to bear bending stress. This optimizes the overall stress distribution, avoids deformation or wear of the output shaft 42 caused by lateral force, and significantly improves the operating life and reliability of the equipment. Moreover, the end face bearing 6 has a high-precision rotating interface, which can reduce friction and vibration.

[0048] Between the end face bearing 6 and the table 11, a backing plate 5 is arranged, which mainly provides a high-precision support plane to ensure the installation quality of the end face bearing 6. It is usually made of wear-resistant materials such as quenched steel, and the surface is finished to ensure flatness and levelness. Figure 2 and Figure 3 As shown, the stationary face of the end face bearing 6 is in contact with the backing plate 5, and the flatness of the backing plate 5 directly determines the perpendicularity of the axis of the end face bearing 6. If it is directly installed on the table 11 of the test stand 1, the slight unevenness of the table 11 may be amplified as a rotating deviation, and the backing plate 5 as a local reference eliminates this error source, making the installation of the end face bearing 6 more accurate and reducing vibration during high-speed rotation.

[0049] In addition, during equipment operation, the dynamic load generated by the rotating system is transmitted to the backing plate 5 through the end face bearing 6, and the rigid structure of the backing plate 5 can effectively suppress deformation and avoid resonance phenomenon. Moreover, as an independent component, the backing plate 5 can be replaced individually after wear, reducing maintenance costs.

[0050] Subsequently, the test piece is installed and fixed.

[0051] As shown, Figure 4 The fixing clamp 24 is in two sets, which slides along the adjusting groove 23 on the base plate 21 to adjust the distance from the continuous shaft hole 22, thereby changing the rotating radius of the test piece.

[0052] The fixing clamp 24 includes a sliding seat 241, a ring cavity 243, and an open ring 242. The sliding seat 241 is connected with the adjusting groove 23 through a locking bolt. The test piece is placed in the open ring 242, and a uniform radial clamping force is applied through the locking bolt to ensure that the test piece is firmly fixed without loosening during high-speed rotation. Threaded holes can be formed on the sliding seat 241, and the locking bolt is threadedly connected with the threaded holes. When the locking bolt is tightened, the open ring 242 tightly holds the test piece. The clamping force can be adjusted by the tightening degree. For example, the clamping force can be adjusted in the range of 50-500N, which is suitable for cylindrical test pieces with a diameter of 50-300mm.

[0053] The design of the adjusting groove 23 realizes continuous adjustment of the rotation radius. Combined with the rotation speed control, the 3g-50g overload range can be accurately simulated, meeting the differentiated needs of different test pieces. In addition, the split ring structure is suitable for test pieces of different diameters, improving the versatility and operation convenience of the equipment.

[0054] Subsequently, the main control box is connected with the man-machine interaction device.

[0055] The main control box 3 is installed on the base plate 21, and the shell inside contains a controller for adjusting the input action signal of the driving device 4, such as the release command, the detonation command, etc. The controller can contain common control and communication equipment in the prior art, such as PLC controller, wireless communication module, energy storage unit and electrical interface components, etc. The key components are inserted into the test piece through the extension line to input the action signal to the test piece, and the signal generation, transmission and control functions are realized through the standardized hardware architecture.

[0056] The main control box 3 rotates synchronously with the test piece, can output real-time simulation flight signals, and realize the full-process working state simulation of the test piece in the real overload environment. The main control box 3 is also in communication connection with the man-machine interaction device such as the touch screen, and the operator can set the input signal timing and monitor the running state through the interface. This design improves the realism and effectiveness of the test, avoids complex wiring, and reduces maintenance costs.

[0057] Finally, start the driving and overload simulation.

[0058] The driving device 4 is started through the main control box 3, and the output shaft 42 drives the adapter plate 7 and the clamping device 2 to move horizontally in a circle. The centrifugal acceleration is calculated by the formula a = ω 2 r, where ω is the angular velocity and r is the rotation radius.

[0059] The equipment accurately controls the overload value by adjusting the rotation speed and the position of the fixed clamp 24. The cooperation of the face bearing 6 and the adapter plate 7 ensures the stability of rotation and effectively suppresses vibration and noise. During the test, the main control box 3 collects data in real time to ensure that the overload environment is consistent with the preset value. This simulation method gets rid of the expensive and dangerous flight test, significantly reduces the single cost, and realizes the convenient reproduction of the overload environment.

[0060] After the test is completed, the rotation speed of the driving device 4 is gradually reduced to zero through the main control box 3, avoiding the impact caused by sudden braking. The locking pin of the fixed clamp 24 is loosened, and the test piece is taken out for performance analysis. The equipment is designed in a modular manner, which is easy to disassemble, maintain and replace.

[0061] The above merely describes the preferred embodiments of the present application and is not intended to limit the scope of the present application. In addition, the terms "vertical", "horizontal", "front", "back" and the like mentioned in the embodiments of the present application indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product is usually placed in use, and are merely for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. It needs to be further explained that, unless otherwise clearly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like in the description should be understood in a broad sense, for example, "connecting" can be fixedly connected, or can be detachably connected, or integrally connected; can be directly connected, or indirectly connected through an intermediate medium, or the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0062] Although the embodiments of the present application have been shown and described, those skilled in the art can understand that various changes, modifications, replacements and variations can be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the claims and their equivalents.

Claims

1. An experimental device for simulating flight motion overload, comprising a test frame (1), characterized in that: The utility model also comprises a driving device (4) and a clamping device (2) for clamping a component to be tested. The driving device (4) comprises a body (41) mounted on the test rack (1) and an output shaft (42) connected with the body (41). The clamping device (2) comprises a bottom plate (21) and a fixing clamp (24) mounted on the bottom plate (21), The bottom plate (21) is provided with a connecting shaft hole (22) matched with the output shaft (42), and the bottom plate (21) is configured to rotate under the driving of the output shaft (42).

2. The experimental apparatus for simulating flight motion overload according to claim 1, wherein: The fixing clamp (24) is provided in two sets, the bottom plate (21) is provided with an adjusting groove (23), and the two sets of fixing clamps (24) are configured to slide along the adjusting groove (23) to adjust the position away from the connecting shaft hole (22).

3. The experimental apparatus for simulating flight motion overload according to claim 2, wherein: The fixing clamp (24) comprises a sliding seat (241) connected with the adjusting groove (23) and a ring accommodating cavity (243) provided in the sliding seat (241), the ring accommodating cavity (243) is provided with an open ring (242), and the sliding seat (241) is connected with a locking bolt for locking the open ring (242).

4. The experimental apparatus for simulating flight motion overload according to claim 1 or 2 or 3, characterized in that: The utility model also comprises an adapter plate (7) fixedly connected to the lower surface of the bottom plate (21), the adapter plate (7) is provided below with an end face bearing (6), and the output shaft (42) penetrates through the end face bearing (6).

5. The experimental apparatus for simulating flight motion overload according to claim 4, wherein: The rotating surface of the end face bearing (6) is in contact with the adapter plate (7), and the stationary surface of the end face bearing (6) is in contact with the test rack (1).

6. The experimental apparatus for simulating flight motion overload according to claim 5, wherein: The test rack (1) is provided with a backing plate (5), and the stationary surface of the end face bearing (6) is in contact with the backing plate (5).

7. The experimental apparatus for simulating flight motion overload according to claim 4, wherein: The adapter plate (7) is circular.

8. The experimental apparatus for simulating flight motion overload according to claim 1 or 2 or 3, characterized in that: The test rack (1) comprises a table top (11) and a support (12), and the support (12) comprises a leveling part.

9. The experimental apparatus for simulating flight motion overload according to claim 1 or 2 or 3, characterized in that: The bottom plate (21) is provided with a main control box (3), and the main control box (3) comprises a shell and a controller for adjusting the rotation parameters of the driving device (4).

10. The experimental apparatus for simulating flight motion overload according to claim 9, wherein: The utility model also comprises a man-machine interaction device in communication connection with the main control box (3).

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