Air rudder load simulation device

Abstract

The invention provides an air rudder load simulation device, and relates to the technical field of aerospace. The air rudder load simulation device comprises a table body, a support A, a support B and a support C are arranged on the upper portion of the table body, guide columns are fixedly connected to the two adjacent sides of the support B and the support C, sliding blocks are arranged in the middles of the guide columns, a main shaft slides in the middle of the support B, an actuator is fixedly connected to the rear end of the support A, and the actuator is fixedly connected to the rear end of the support B. And a tension meter is hinged and fixed at the rear end of the actuator. The air rudder load simulation device provided by the invention can simulate an air rudder load, the actuator provides a driving force, the guide column and the slide block ensure the stability and accuracy of movement, and the inertia disc and the spiral spring are respectively used for simulating rotational inertia and an elastic load, so that an effective platform is provided for testing an air rudder servo system; and compared with a traditional mode of testing by using a real air rudder, the research and development cost is saved.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to an air rudder load simulation device. Background Art

[0002] During the maneuvering phase of a rocket or missile's flight within the atmosphere, a vector servo control system operates the air rudders to achieve attitude control, such as pitch, yaw, and roll. During this process, the servo system must overcome hinge torque and inertia moments to execute control system commands. Typically, servo control characteristics must be debugged together with the rocket's air rudders to ensure full matching. Load testing of traditional rocket air rudder servo mechanisms requires custom-made, identical rudders from the rocket manufacturer for servo system testing. Rocket air rudders present drawbacks such as difficulty in design and manufacturing, long lead times, high costs, and a limited number of oscillations. Furthermore, high-speed aerodynamic flow simulations are required to simulate the hinge torques of the rudders at various deflection angles during flight. This significantly limits the matching and calibration of the servo system characteristics with the rocket's air rudders, restricting load testing of mass-produced servo systems.

[0003] Currently, servo system testing of air rudders in aerospace servo systems typically involves fabricating simulated rudder blades to simulate the inertia of rudder blade deflection, or using steel plate torsion structures for low-power systems to simulate hinge torque. However, when an air rudder moves in a high-speed flow field, the greater the rudder deflection angle, the greater the corresponding hinge torque. While such hinge torque under real-world conditions requires high-speed flow field simulation, this approach is expensive and time-consuming, and typically relies on finite element aerodynamic simulation analysis and calculation. However, all of these methods have drawbacks: Simulating and analyzing the actual missile, rudder blade, and air flow field is not only time-consuming and expensive, severely limiting the development of air rudder servo systems for aerospace applications, but the hinge torque parameters derived from finite element fluid aerodynamic simulation of the rudder blades lack experimental data support, making it difficult to test the extreme performance of the product design under working conditions. Data deviations can even lead to accidents. Summary of the Invention

[0004] (1) Technical problems solved

[0005] In response to the shortcomings of the existing technology, the present invention provides an air rudder load simulation device, which solves the problems of long air flow field simulation analysis cycle and high cost in traditional devices, and solves the problem of lack of real test data support for the hinge torque parameters of the rudder blades of traditional devices through finite element fluid aerodynamic simulation.

[0006] (2) Technical solution

[0007] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0008] An air rudder load simulation device comprises a platform, wherein a support A, a support B, and a support C are provided on the upper portion of the platform, guide columns are fixedly connected to the adjacent sides of the supports B and C, a slider is provided in the middle of the guide columns, a main shaft slides on the middle of the support B, an actuator is fixedly connected to the rear end of the support A, a dynamometer is hingedly fixed to the rear end of the actuator, inertia disks are rotatably connected to both sides of the rear end of the platform, and coil springs are provided at the front and rear ends of the two guide columns.

[0009] The above technical solution can simulate the load of an air rudder, in which the actuator provides the driving force, the guide column and slider ensure the stability and accuracy of the movement, and the inertia disk and coil spring are used to simulate the moment of inertia and elastic load, respectively. This provides an effective platform for testing the air rudder servo system and saves R&D costs compared to the traditional testing method using a real air rudder.

[0010] Preferably, the rear end of the dynamometer is fixedly connected to the front end of the main shaft;

[0011] Through the above technical solution, the dynamometer can measure the tension applied by the actuator to the main shaft in real time, and then obtain the size of the elastic load, which provides a basis for the acquisition and analysis of test data and helps to evaluate the performance of the servo system under different loads.

[0012] Preferably, an inertia adjustment disk is fixed on one side of the upper part of the inertia disk away from the center of the platform, and both sides of the slider move in the reserved grooves on the inner wall of the corresponding inertia disk. The inertia adjustment disk is bolted to the inertia disk through a positioning pin hole, and the inertia of a single inertia adjustment disk is a configurable parameter.

[0013] Through the above technical solution, the moment of inertia can be easily adjusted. According to the characteristics and test requirements of different air rudders, the number of inertia adjustment disks can be increased or decreased, or adjustment disks with different inertias can be replaced to achieve precise adjustment of the moment of inertia, thereby improving the versatility and flexibility of the device and adapting to the test requirements of the servo system for new models of air rudders.

[0014] Preferably, the inner walls of the slider slide between the outer walls of the two guide pillars;

[0015] The above technical solution ensures the smooth sliding of the slider on the guide column, reduces friction and shaking during movement, ensures the accuracy and stability of elastic load simulation, and makes the test results reliable.

[0016] Preferably, the front ends of the front coil springs are in contact with the outer wall of the support B, the rear ends of the front coil springs are in contact with the outer wall of the slider, the front ends of the rear coil springs are in contact with the outer wall of the slider, and the rear ends of the rear coil springs are in contact with the outer wall of the support C;

[0017] Through the above technical solution, when the slider slides on the guide column, the coil spring will be compressed or stretched accordingly, thereby generating elastic force to simulate the elastic load of the air rudder. This fitting connection method can effectively transmit force and ensure the effect of elastic load simulation. By changing the position of the slider, the compression amount of the spring can be easily adjusted, thereby changing the size of the elastic load.

[0018] (3) Beneficial effects

[0019] The present invention provides an air rudder load simulation device, which has the following beneficial effects:

[0020] 1. The present invention provides an air rudder load simulation device. This device achieves air rudder load simulation through a purely mechanical structural design. Compared with traditional testing solutions that rely on real rudder blades and high-speed flow fields, it can save R&D costs. The device uses four sets of cylindrical coil springs to replace the elastic load characteristics of real rudder blades. Elastic torque simulation is achieved by adjusting the spring compression or replacing the stiffness. A detachable fan-shaped inertia adjustment disk is combined with a basic inertia disk to adjust the inertial load. There is no need to customize high-precision rudder blades or build expensive flow field equipment. The cost of a single set of devices is lower than that of traditional solutions, providing a cost-effective solution for batch testing of servo systems.

[0021] 2. This invention provides an air rudder load simulation device. For adapting to new servo system models, the device utilizes a modular, adjustable structure to create a flexible testing platform. The elastic torque can be adjusted by varying the compression of four coil springs or by replacing coil springs with different stiffnesses. The inertial load is adjusted by adjusting the coaxially mounted inertia adjustment dial to match the rotational inertia requirements of different air rudder models. This independent load adjustment provides a reliable basis for feature matching and operating condition testing during servo system upgrades. This allows a single device to cover the testing requirements of most aerospace servo systems, improving R&D efficiency and reducing the cost of technology iteration. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the main structure of the present invention;

[0023] Figure 2 is an axonometric drawing of the present invention;

[0024] Figure 3 is a side view of the present invention;

[0025] Figure 4 for Figure 3 Enlarged view of point A in the middle.

[0026] in,

[0027] 1. Platform; 2. Support A; 3. Support B; 4. Slider; 5. Coil spring; 6. Support C; 7. Guide column; 8. Inertia adjustment plate; 9. Inertia plate; 10. Dynamometer; 11. Actuator; 12. Spindle. DETAILED DESCRIPTION

[0028] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0029] like Figure 1-4 As shown, the embodiment of the present invention provides

[0030] An air rudder load simulation device includes a platform 1. A support A2, a support B3 and a support C6 are provided on the upper part of the platform 1. Guide columns 7 are fixedly connected to the adjacent sides of the supports B3 and C6. A slider 4 is provided in the middle of the guide columns 7. A main shaft 12 slides in the middle of the support B3. An actuator 11 is fixedly connected to the rear end of the support A2. A dynamometer 10 is hingedly fixed to the rear end of the actuator 11. Inertia disks 9 are rotatably connected to both sides of the rear end of the platform 1. Coil springs 5 ​​are provided at the front and rear ends of the two guide columns 7.

[0031] It can simulate the load of an air rudder, where the actuator 11 provides the driving force, the guide column 7 and the slider 4 ensure the stability and accuracy of the movement, the inertia disk 9 and the coil spring 5 are used to simulate the moment of inertia and the elastic load, respectively. This provides an effective platform for testing the air rudder servo system and saves R&D costs compared to the traditional testing method using a real air rudder.

[0032] The rear end of the dynamometer 10 is fixedly connected to the front end of the main shaft 12. The dynamometer 10 can measure the tension applied by the actuator 11 to the main shaft 12 in real time, and then obtain the size of the elastic load, which provides a basis for obtaining and analyzing test data and helps to evaluate the performance of the servo system under different loads. An inertia adjustment disk 8 is fixed on one side of the upper part of the inertia disk 9 away from the center of the platform 1. Both sides of the slider 4 move in the reserved grooves on the inner wall of the corresponding inertia disk 9. The inertia adjustment disk 8 is bolted to the inertia disk 9 through the locating pin hole. The inertia of a single inertia adjustment disk 8 is a configurable parameter, which can conveniently adjust the rotational inertia. According to the characteristics and test requirements of different air rudders, the number of inertia adjustment disks 8 can be increased or decreased, or adjustment disks of different inertias can be replaced to achieve precise adjustment of the rotational inertia, thereby improving the versatility and flexibility of the device and adapting to the test requirements of the servo system for new models of air rudders.

[0033] The inner walls of the slider 4 slide between the outer walls of the two guide columns 7, ensuring the smooth sliding of the slider 4 on the guide columns 7, reducing friction and shaking during movement, ensuring the accuracy and stability of the elastic load simulation, and making the test results reliable. The front end of the front end coil spring 5 is in contact with the outer wall of the support B3, and the rear end of the front end coil spring 5 is in contact with the outer wall of the slider 4. The front end of the rear end coil spring 5 is in contact with the outer wall of the slider 4, and the rear end of the rear end coil spring 5 is in contact with the outer wall of the support C6. When the slider 4 slides on the guide column 7, the coil spring 5 will be compressed or stretched accordingly, thereby generating elastic force to simulate the elastic load of the air rudder. This fitting connection method can effectively transmit force, ensure the effect of elastic load simulation, and by changing the position of the slider 4, the compression amount of the spring can be conveniently adjusted, thereby changing the size of the elastic load.

[0034] Specific method of loading elastic force;

[0035] During testing, one end of the actuator 11 to be tested is fixedly connected to the support A2, and the other end is connected to the dynamometer 10. The rear end of the dynamometer 10 is rigidly connected to the spindle 12. When the actuator 11 is working, its front end rod extends or retracts, driving the spindle 12 to translate horizontally, thereby driving the slider 4 to slide on the guide post 7.

[0036] Specifically, when the front rod of actuator 11 extends, it pushes dynamometer 10, spindle 12, and slider 4 to the right. At this point, support B secures the left end of left-hand coil spring 5, while support C secures the right end of right-hand coil spring 5, constraining both ends of the springs. As slider 4 translates rightward, right-hand coil spring 5 is compressed and left-hand coil spring 5 is stretched, with the amount of deformation of both equal to the stroke of actuator 11.

[0037] According to Hooke's law, the elastic load force F, spring stiffness k, and compression x satisfy F = 2kx (the coefficient is 2 because there are two springs on each side). This results in an elastic load that is linearly related to the stroke of actuator 11. Its magnitude can be controlled by adjusting the stroke of actuator 11 or changing the spring stiffness. When the servo actuator 11 under test pushes the main shaft 12, the displacement of slider 4 is directly converted into the compression of the right-hand coil spring 5, which in turn generates an elastic reaction force F that is linearly proportional to the deflection angle of the rudder blade, simulating the elastic load characteristics of an actual air rudder. The dynamometer 10 collects this elastic force in real time, which can be used to verify theoretical calculations and provide measured data for load characteristic analysis of the servo system, ensuring the accuracy and reliability of the test results.

[0038] Working principle: Two guide columns 7 are set in parallel on the platform 1 of the device. The support A2 fixes the actuator 11 and is connected to the main shaft 12 through the tension meter 10. The main shaft 12 passes through the support B3 and is rigidly connected to the slider 4. Four groups of cylindrical coil springs 5 ​​are arranged in parallel on both sides of the slider 4 with the guide column 7 as the symmetry axis. One end of the two groups of springs at the front end is fixed to the support B3 and the other end is connected to the slider 4. One end of the two groups of springs at the rear end is connected to the slider 4 and the other end is fixed to the support C6. When the actuator 11 to be tested drives the main shaft 12 During horizontal movement, the slider 4 slides synchronously along the guide column 7, forcing the spring to undergo elastic compression or tension deformation. Based on Hooke's law, an elastic torque linearly related to the displacement of the main shaft 12 is generated. The inertial load is achieved through a linked inertia adjustment mechanism. The cam protrusions on both sides of the slider 4 are embedded in the oblong holes on the edge of the inertia disk 9. When the slider 4 translates, the inertia disk 9 is driven to swing. Its basic inertia is provided by the sector-shaped inertia disk 9. The inertia requirements of different test conditions are matched by the coaxial and removable sector-shaped inertia adjustment disk 8. By arranging the spring group and the inertia disk 9 in parallel and collinearly, this device effectively reduces lateral force interference and ensures independent adjustability of the elastic torque and inertial load. While ensuring test accuracy, it also improves debugging convenience and solves the problems of high cost, long cycle time, and insufficient simulation accuracy caused by traditional testing relying on real rudder blades and high-speed flow fields.

[0039] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include," "comprise," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a series of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0040] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. An air rudder load simulation device, comprising a platform (1), characterized in that: The upper part of the platform (1) is provided with a support A (2), a support B (3) and a support C (6), the adjacent two sides of the support B (3) and the support C (6) are fixedly connected with a guide column (7), the middle part of the guide column (7) is provided with a slider (4), the middle part of the support B (3) is provided with a main shaft (12), the rear end of the support A (2) is fixedly connected with an actuator (11), the rear end of the actuator (11) is hingedly fixed with a tension meter (10), both sides of the rear end of the platform (1) are rotatably connected with an inertia disk (9), and the front and rear ends of the two guide columns (7) are provided with a coil spring (5).

2. The air rudder load simulation device according to claim 1, characterized in that: The rear end of the dynamometer (10) is fixedly connected to the front end of the main shaft (12).

3. The air rudder load simulation device according to claim 1, characterized in that: An inertia adjustment disk (8) is fixed on one side of the upper part of the inertia disk (9) away from the center of the platform (1), and both sides of the slider (4) move in the reserved grooves on the inner wall of the corresponding inertia disk (9). The inertia adjustment disk (8) is bolted to the inertia disk (9) through a positioning pin hole, and the inertia of a single inertia adjustment disk (8) is a configurable parameter.

4. The air rudder load simulation device according to claim 1, characterized in that: The inner walls of the slider (4) slide between the outer walls of the two guide pillars (7).

5. The air rudder load simulation device according to claim 1, characterized in that: The front end of the front coil spring (5) is in contact with the outer wall of the support B (3), the rear end of the front coil spring (5) is in contact with the outer wall of the slider (4), the front end of the rear coil spring (5) is in contact with the outer wall of the slider (4), and the rear end of the rear coil spring (5) is in contact with the outer wall of the support C (6).

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