Aircraft folding rudder deployment testing device and testing system thereof
By designing a test device for folding rudders of aircraft and using mechanical energy storage to simulate aerodynamic loads, the problems of low safety and high cost in wind tunnel testing were solved, and efficient and safe rudder deployment testing was achieved on a static test bench.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
- Filing Date
- 2025-11-21
- Publication Date
- 2026-06-23
AI Technical Summary
Existing wind tunnel tests for folding rudder deployment performance testing suffer from low safety and high cost.
A test device for folding and deploying control surfaces of an aircraft was designed, including a base, a load simulation component, and a measurement unit. It simulates aerodynamic loads through mechanical energy storage, and uses the load simulation component to store mechanical energy when the control surfaces are folded and to provide assist loads when they are deployed. The deployment time is measured by combining sensors.
The test achieved safe and efficient rudder deployment testing in a static test bench environment, simplifying wind tunnel testing that relies on large facilities, solving measurement problems caused by airflow shielding and vibration, and improving the stability and safety of the test.
Smart Images
Figure CN121291797B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the technical field of aerospace testing, and in particular to a test device and system for testing the folding and unfolding of aircraft rudders. Background Technology
[0002] Folding rudders have been widely used in modern aerospace due to their ability to effectively reduce aircraft storage volume, improve launch flexibility, and enhance stealth capabilities. The ability of folding rudders to quickly and reliably unfold and lock after launch directly affects the aircraft's flight stability, control precision, and ultimate mission effectiveness.
[0003] Currently, the performance of folding rudder deployment is mainly assessed through wind tunnel testing. Although wind tunnel testing can realistically simulate the aerodynamic environment, it suffers from high testing costs, limited resources, and impact loads during high-speed deployment of the rudder surface, posing a potential safety risk to wind tunnel testing equipment. Therefore, wind tunnel testing has relatively low safety. Summary of the Invention
[0004] This invention provides an aircraft folding rudder deployment test device and system to solve the technical problem of low safety when using wind tunnel testing in related technologies.
[0005] In a first aspect, embodiments of the present invention provide an aircraft folding rudder deployment test device, the test device comprising:
[0006] A base, which is used to fix the fixed rudder surface of the folding rudder to be tested;
[0007] A load simulation component is mounted on the base and is connected to the moving control surface of the folding rudder under test.
[0008] The measurement unit includes two sensors and a data processor. The two sensors are respectively located at the folding start position and the unfolded position of the moving control surface, and both sensors are electrically connected to the data processor.
[0009] When an external force drives the moving control surface to fold and limit its position, the load simulation component stores energy. When the moving control surface is released, the load simulation component applies a simulated assist load to the unfolding of the moving control surface. The data processor calculates the rudder deployment time based on the position signals measured by the two sensors.
[0010] In some embodiments, the load simulation component includes:
[0011] A torsion bar is provided on the base and the axis of the torsion bar is parallel to the axis of the central bulge of the moving rudder surface. One end of the torsion bar is fixedly connected to the base.
[0012] A universal joint, which connects the other end of the torsion bar to the moving control surface, is used to transmit torque to the moving control surface.
[0013] In some embodiments, the load simulation assembly further includes: a transmission rod, one end of which is connected to the universal joint and the other end of which is inserted into the moving control surface to transmit torque;
[0014] A connector, one end of which is connected to the universal joint and the other end of which is connected to the torsion bar, wherein the cross-section of the connector is hexagonal.
[0015] In some embodiments, the gimbal has at least three degrees of freedom.
[0016] In some embodiments, the base includes:
[0017] Base plate;
[0018] Torsion bar fixing seat, the torsion bar fixing seat is fixedly mounted on the base plate;
[0019] A first torsion bar fixing member and a second torsion bar fixing member are spaced apart and opposite to each other on the torsion bar fixing base. The first torsion bar fixing member is fixedly connected to the first end of the torsion bar. The second torsion bar fixing member is provided with a mounting through hole. The second end of the torsion bar is inserted into the mounting through hole. The connecting member is inserted into the mounting through hole and fixedly connected to the torsion bar.
[0020] In some embodiments, the device further includes a fixing component, which includes a mounting base and a fixing pin. The mounting base is fixedly disposed on the base plate, and the fixing pin is slidably disposed in the mounting base. The fixing pin can slide to a locking position to restrict the deployment of the moving control surface or slide to a release position to release the lock.
[0021] In some embodiments, the first torsion bar fixing member has a square groove, and the first end of the torsion bar is a connecting structure that mates with the square groove.
[0022] In some embodiments, the stiffness coefficient K of the torsion bar is determined based on the ratio of the work done by the aerodynamic load on the moving control surface during a preset multiple of the rudder deployment process to the maximum folding angle of the moving control surface.
[0023] In some embodiments, the load simulation component is detachably connected to both the base and the moving control surface.
[0024] Secondly, embodiments of the present invention provide an aircraft folding rudder deployment test system, the test system including the aforementioned aircraft folding rudder deployment test device.
[0025] The beneficial effects of the technical solution provided by this invention include:
[0026] This invention provides a test device and system for testing the deployment of a folding rudder on an aircraft. The test device includes a base, a load simulation component, and a measurement unit. The base is used to fix the fixed control surface of the folding rudder under test. The load simulation component is mounted on the base and is drively connected to the moving control surface of the folding rudder under test. The measurement unit has two sensors and a data processor. The two sensors are respectively located at the folding start position and the unfolded position of the moving control surface, and are both electrically connected to the data processor. When an external force drives the moving control surface to fold and limit its position, the load simulation component stores energy. When the moving control surface is released, the load simulation component applies a simulated assist load to the unfolding of the moving control surface, and the data processor calculates the deployment time based on the position signals measured by the two sensors. This testing device simulates aerodynamic loads during flight through mechanical energy storage. When the moving control surface is folded, it drives the load simulation component to store mechanical energy as elastic potential energy. When the moving control surface is released and unfolded, the torque generated by the load simulation component's deformation recovery continues to act on the moving control surface through the universal joint, without introducing additional constraints to the control surface. By placing sensors at the folding start and unfolding positions for measurement, the device realistically reproduces the assisting effect of aerodynamic drag on the control surface unfolding process. In a static bench environment, wind tunnel testing, which relies on large facilities and complex flow fields, is simplified to mechanical motion testing on a bench. This improves the stability and safety of the test, and by directly placing sensors at key positions, it completely solves the measurement problems caused by airflow shielding and vibration in the wind tunnel, as well as the drawbacks of introducing additional constraints during loading in traditional control surface unfolding test devices. Attached Figure Description
[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0028] Figure 1 This is a schematic diagram of a folded state structure of an aircraft folding rudder deployment test device provided in an embodiment of the present invention;
[0029] Figure 2 This is a schematic diagram of another folded state structure of an aircraft folding rudder deployment test device provided in an embodiment of the present invention;
[0030] Figure 3 A schematic diagram of the unfolded state structure of an aircraft folding rudder deployment test device provided in an embodiment of the present invention;
[0031] Figure label:
[0032] 1. Base; 11. Base plate; 12. Torsion bar fixing seat; 13. First torsion bar fixing component; 131. Square groove; 14. Second torsion bar fixing component; 141. Mounting through hole;
[0033] 2. Load simulation component; 21. Torsion bar; 22. Universal joint; 23. Drive rod; 24. Connecting component;
[0034] 3. Measurement unit; 31. Sensor;
[0035] 4. Folding rudder to be tested; 41. Fixed rudder surface; 42. Moving rudder surface;
[0036] 5. Fixing components; 51. Mounting base; 52. Fixing pin. Detailed Implementation
[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0038] This invention provides a test device and system for testing the folding and unfolding of aircraft rudders, which can solve the technical problem of low safety when using wind tunnels for testing in related technologies.
[0039] See Figure 1 , Figure 2 and Figure 3As shown in the figure, an embodiment of the present invention provides an aircraft folding rudder deployment test device. The test device includes a base 1, a load simulation component 2, and a measurement unit 3. The base 1 is used to fix the fixed control surface 41 of the folding rudder 4 under test. The load simulation component 2 is disposed on the base 1 and is drively connected to the moving control surface 42 of the folding rudder 4 under test. The measurement unit 3 is provided with two sensors 31 and a data processor. The two sensors 31 are respectively disposed at the folding start position and the unfolded position of the moving control surface 42. Both sensors 31 are electrically connected to the data processor. When an external force drives the moving control surface 42 to fold and limit its position, the load simulation component 2 stores energy. When the moving control surface 42 is released, the load simulation component 2 applies a simulated assist load to the unfolding of the moving control surface 42. The data processor calculates the deployment time based on the position signals measured by the two sensors 31. The testing device provided in this embodiment of the invention simulates aerodynamic loads during flight through mechanical energy storage. When the moving control surface 42 is folded, it drives the load simulation component 2 to store mechanical energy in the form of elastic potential energy. When the moving control surface 42 is released and unfolded, the assist torque generated by the deformation of the load simulation component 2 continues to act on the moving control surface 42. By placing sensors 31 at the folding start and unfolding positions respectively for measurement, the aerodynamic assistance on the control surface unfolding process is realistically reproduced. In a static test bench environment, wind tunnel testing, which relies on large facilities and complex flow fields, is simplified to mechanical motion testing on a test bench, improving the stability and safety of the test. Furthermore, in a static test bench environment, by directly placing sensors at the folding start and unfolding positions, the measurement difficulties caused by airflow shielding and vibration in the wind tunnel are completely solved, and the drawbacks of introducing additional constraints during loading of traditional control surface unfolding test devices are also resolved.
[0040] This invention provides a test device for testing the deployment of a folding control rudder of an aircraft. The test device includes a base, a load simulation component, and a measurement unit. The base is used to fix the fixed control surface of the folding control rudder under test. The load simulation component is mounted on the base and is connected to the moving control surface of the folding control rudder under test. The measurement unit has two sensors and a data processor. The two sensors are respectively located at the folding start position and the unfolded position of the moving control surface, and are both electrically connected to the data processor. When an external force drives the moving control surface to fold and limit its position, the load simulation component stores energy. When the moving control surface is released, the load simulation component applies a simulated assist load to the unfolding of the moving control surface. The data processor calculates the deployment time based on the position signals measured by the two sensors. This test device simulates aerodynamic loads in flight through mechanical energy storage. When the moving control surface is folded, it drives the load simulation component to store mechanical energy in the form of elastic potential energy. When the moving control surface is released and unfolded, the assist torque generated by the deformation of the load simulation component continues to act on the moving control surface. By placing sensors at the folding start position and the unfolded position for measurement, the device realistically reproduces the obstructive effect of aerodynamic assistance on the deployment process. In a static test bench environment, wind tunnel testing, which relies on large facilities and complex flow fields, is simplified to mechanical motion testing on the test bench. This not only improves the stability and safety of the test, but also completely solves the measurement problems caused by airflow shielding and vibration in the wind tunnel by directly deploying sensors at key locations.
[0041] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 As shown, the load simulation component 2 includes a torsion bar 21 and a universal joint 22. The torsion bar 21 is mounted on the base 1 and its axis is parallel to the axis of the central bulge of the moving rudder surface 42. One end of the torsion bar 21 is fixedly connected to the base 1. The universal joint 22 is connected between the other end of the torsion bar 21 and the moving rudder surface 42 to transmit torque to the moving rudder surface 42. In this embodiment of the invention, the combination of torsion bar 21 and universal joint 22 in the load simulation component 2 achieves high-precision simulation of flight aerodynamic loads without introducing additional constraints during the loading process. The torsion bar 21 is arranged on the base 1 with its axis parallel to the central bulge axis of the moving control surface 42, and one end is fixedly connected to the base 1. When the connecting piece 24 is rotated by an external force, both the moving control surface 42 and the torsion bar 21 are torsionated, converting mechanical energy into stored elastic potential energy. When the moving control surface 42 is released and deployed, the restoring torque generated by the deformation of the torsion bar 21 is transmitted in the opposite direction to the moving control surface 42 through the universal joint 22, forming a continuous and linear simulated assist load. The introduction of the universal joint 22 ensures smooth and accurate torque transmission and also ensures that the loading device does not introduce additional constraints on the free deployment of the control surface. The load simulation component 2 has a simple and reliable structure, providing a stable, repeatable, and physically realistic aerodynamic load loading environment for the deployment test of the folding control surface 4 under test, ensuring accurate measurement of the deployment time.
[0042] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 As shown, the load simulation component 2 also includes a transmission rod 23. One end of the transmission rod 23 is connected to the universal joint 22, and the other end is inserted into the moving rudder surface 42 to transmit torque. In this embodiment of the invention, by adding a transmission rod 23 to the load simulation component 2, the torque transmission path is further improved. One end of the transmission rod 23 is reliably connected to the universal joint 22, and the other end is directly inserted into the rear end interface of the moving rudder surface 42. On the one hand, this fully utilizes the ability of the universal joint 22 to compensate for axial deviation. On the other hand, the transmission rod 23, as a rigid connecting component, ensures the directness and efficiency of torque transmission, improves connection rigidity, avoids the influence of transmission clearance on test accuracy, and enables the entire load simulation component 2 to adapt to the test requirements of folding rudders 4 of different sizes.
[0043] As an optional implementation, in one embodiment of the invention, the universal joint 22 has at least three degrees of freedom. In this embodiment, the universal joint 22 is defined to have at least three degrees of freedom. This characteristic allows the universal joint 22 to fully compensate for complex positional deviations between the torsion bar 21 and the moving control surface 42 in multiple directions, including axial, radial, and angular displacements and deflections. When there are installation errors or motion trajectory fluctuations during the unfolding process of the folding rudder 4 under test, the multi-degree-of-freedom universal joint 22 can effectively absorb these deviations, ensuring that the torque transmission path from the torsion bar 21 to the transmission rod 23 and then to the moving control surface 42 remains smooth, completely eliminating jamming or additional friction caused by motion interference. This not only ensures the uniformity and accuracy of the simulated auxiliary load, making the test data more realistically reflect the unfolding performance of the folding rudder 4 under aerodynamic loads, but also significantly reduces the requirements of the testing device on the machining and assembly accuracy of components.
[0044] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1As shown, the base 1 includes a base plate 11, a torsion bar fixing seat 12, and a first torsion bar fixing member 13 and a second torsion bar fixing member 14 spaced apart and opposite to each other on the torsion bar fixing seat 12. The torsion bar fixing seat 12 is fixedly mounted on the base plate 11. The first torsion bar fixing member 13 is fixedly connected to the first end of the torsion bar 21. The second torsion bar fixing member 14 has a mounting through hole 141, into which the second end of the torsion bar 21 is inserted. The connecting member 24 is inserted into the mounting through hole 141 and fixedly connected to the torsion bar 21. In this embodiment of the invention, by adopting a base 1 structure consisting of a base plate 11, a torsion bar fixing seat 12, a first torsion bar fixing member 13, and a second torsion bar fixing member 14, a stable and reliable mounting foundation is provided for the load simulation component 2. The torsion bar fixing seat 12 is fixed to the base plate 11, forming the main support frame. The connection between the first torsion bar fixing member 13 and the first end of the torsion bar 21 ensures the effective transmission of torque reaction, while the mounting through hole 141 on the second torsion bar fixing member 14 accommodates both the second end of the torsion bar 21 and the connecting member 24. This coaxial design ensures precise guidance of the torsional motion of the torsion bar 21 and also achieves connection with the universal joint 22. This ensures the structural rigidity of the testing device, effectively suppresses vibration and deformation during the testing process, and provides precise axial positioning and a stable torsional fulcrum for the torsion bar 21 through the interval setting of the first torsion bar fixing member 13 and the second torsion bar fixing member 14.
[0045] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 As shown, the system also includes a fixing component 5, which has a mounting base 51 and a fixing pin 52. The mounting base 51 is fixedly mounted on the base plate 11, and the fixing pin 52 is slidably inserted into the mounting base 51. The fixing pin 52 can slide to a locking position to restrict the deployment of the moving control surface 42 or slide to a releasing position to unlock it. This embodiment of the invention provides reliable process control for the testing process by adding a fixing component 5 composed of the mounting base 51 and the fixing pin 52. The mounting base 51 is fixed to the base plate 11, and the fixing pin 52, which can slide through it, can limit and deploy the moving control surface 42 by switching between different positions. That is, when the fixing pin 52 slides to the locking position, it can effectively restrict the deployment of the moving control surface 42, ensuring stability during the energy storage stage of the torsion bar 21 and during test preparation. When testing is required, the fixing pin 52 slides to the release position, instantly releasing the constraint on the moving control surface 42, ensuring the triggering of the rudder deployment action, thereby ensuring the accuracy of the rudder deployment time measurement and improving the convenience and safety of the test operation.
[0046] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 2As shown, a square groove 131 is provided on the first torsion bar fixing member 13, and the first end of the torsion bar 21 is a connection structure that mates with the square groove 131. This embodiment of the invention achieves efficient and reliable torque transmission between the two by providing a square groove 131 on the first torsion bar fixing member 13 and designing the first end of the torsion bar 21 as a precisely mating connection structure. This avoids relative rotation between the torsion bar 21 and the first torsion bar fixing member 13 when subjected to torque, ensuring accurate energy transmission and conversion during the torsion energy storage and release process of the torsion bar 21. The structure is simple and easy to install, improving the practicality of the testing device.
[0047] As an optional implementation, in one embodiment of the invention, the stiffness coefficient K of the torsion bar 21 is determined based on the ratio of the work done by the aerodynamic load on the moving control surface 42 during the deployment process (a preset multiple) to the maximum folding angle of the moving control surface 42. In this embodiment of the invention, based on the aircraft speed and attitude, and control surface deflection angle during deployment, aerodynamic simulation or wind tunnel tests are performed on the folding control surface 42 under test at different deployment angles to determine the bending moment of the normal aerodynamic force on the rotation axis of the moving control surface 42. A bending moment-deployment angle curve is plotted, and the work A done by the aerodynamic load on the moving control surface 42 during deployment is determined based on the area A enclosed by the bending moment curve and the angle abscissa in the figure. The torsion bar 21 is set in the ground deployment test device, and the stiffness coefficient of the torsion bar 21 is determined to be K=2*A / φ0 based on the maximum folding angle φ0, ensuring the accuracy of the simulated starting force.
[0048] As an optional implementation, in one embodiment of the invention, the load simulation component 2 is detachably connected to both the base 1 and the moving control surface 42. Designing the connection between the load simulation component 2 and the base 1 and the moving control surface 42 as detachable improves the versatility and ease of maintenance of the testing device.
[0049] This invention also provides an aircraft folding rudder deployment test system. The test system includes the aforementioned aircraft folding rudder deployment test device. The test device includes a base 1, a load simulation component 2, and a measurement unit 3. The base 1 is used to fix the fixed control surface 41 of the folding rudder 4 under test. The load simulation component 2 is disposed on the base 1 and is drively connected to the moving control surface 42 of the folding rudder 4 under test. The measurement unit 3 is provided with two sensors 31 and a data processor. The two sensors 31 are respectively disposed at the folding start position and the unfolded position of the moving control surface 42. Both sensors 31 are electrically connected to the data processor. When an external force drives the moving control surface 42 to fold and limit its position, the load simulation component 2 stores energy. When the moving control surface 42 is released, the load simulation component 2 applies a simulated assist load to the unfolding of the moving control surface 42. The data processor calculates the deployment time based on the position signals measured by the two sensors 31. The testing device provided in this embodiment of the invention simulates aerodynamic loads during flight through mechanical energy storage. When the moving control surface 42 is folded, it drives the load simulation component 2 to store mechanical energy in the form of elastic potential energy. When the moving control surface 42 is released and unfolded, the assist torque generated by the deformation of the load simulation component 2 continues to act on the moving control surface 42. By placing sensors 31 at the folding start and unfolding position respectively for measurement, the aerodynamic assistance on the control surface unfolding process is realistically reproduced. In a static test bench environment, wind tunnel testing, which relies on large facilities and complex flow fields, is simplified to mechanical motion testing on a test bench, improving the stability and safety of the test. Furthermore, in a static test bench environment, by directly placing sensors at the folding start and unfolding position, the measurement problems caused by airflow shielding and vibration in the wind tunnel are completely solved, and the additional constraints brought by traditional load loading devices to the control surface unfolding process are eliminated.
[0050] In the description of this invention, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this invention can be understood according to the specific circumstances.
[0051] It should be noted that in this invention, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.
[0052] The above description is merely a specific embodiment of the present invention, enabling those skilled in the art to understand or implement the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features of the invention herein.
Claims
1. A test device for testing the deployment and folding of rudders on an aircraft, characterized in that, include: Base (1), the base (1) is used to fix the fixed rudder surface (41) of the folding rudder (4) to be tested. Load simulation component (2), the load simulation component (2) is disposed on the base (1), and the load simulation component (2) is connected to the moving rudder surface (42) of the folding rudder (4) to be tested; The measurement unit (3) includes two sensors (31) and a data processor. The two sensors (31) are respectively located at the folding start position and unfolding position of the moving rudder surface (42). Both sensors (31) are electrically connected to the data processor. When the external force drives the moving rudder surface (42) to fold and limit its position, the load simulation component (2) stores energy. When the moving rudder surface (42) is released, the load simulation component (2) applies a simulated assist load to the unfolding of the moving rudder surface (42). The data processor calculates the rudder unfolding time based on the position signals measured by the two sensors (31). The load simulation component (2) includes: Torsion bar (21), the torsion bar (21) is provided on the base (1) and the axis of the torsion bar (21) is parallel to the axis of the central bulge of the moving rudder surface (42), and one end of the torsion bar (21) is fixedly connected to the base (1); Universal joint (22), which is connected between the other end of the torsion bar (21) and the moving rudder surface (42), is used to transmit torque to the moving rudder surface (42). The load simulation component (2) also includes: A transmission rod (23), one end of which is connected to the universal joint (22) and the other end is inserted into the moving rudder surface (42) to transmit torque; Connector (24), one end of which is connected to the universal joint (22) and the other end of which is connected to the torsion bar (21), the cross-section of which is hexagonal; The base (1) includes: Base plate (11); Torsion bar fixing seat (12), the torsion bar fixing seat (12) is fixedly mounted on the base plate (11); A first torsion bar fixing member (13) and a second torsion bar fixing member (14) are spaced apart and opposite to each other on the torsion bar fixing seat (12). The first torsion bar fixing member (13) is fixedly connected to the first end of the torsion bar (21). The second torsion bar fixing member (14) is provided with a mounting through hole (141). The second end of the torsion bar (21) is inserted into the mounting through hole (141). The connecting member (24) is inserted into the mounting through hole (141) and fixedly connected to the torsion bar (21). The fixing component (5) includes a mounting base (51) and a fixing pin (52). The mounting base (51) is fixedly mounted on the base plate (11). The fixing pin (52) is slidably inserted in the mounting base (51). The fixing pin (52) can slide to the locking position to restrict the unfolding of the moving rudder surface (42) or slide to the release position to unlock. The first torsion bar fixing member (13) has a square groove (131) and the first end of the torsion bar (21) is a connection structure that cooperates with the square groove (131).
2. The aircraft folding rudder deployment test device according to claim 1, characterized in that: The universal joint (22) has at least three degrees of freedom.
3. The aircraft folding rudder deployment test device according to claim 1, characterized in that: The stiffness coefficient K of the torsion bar (21) is determined based on the ratio of the work done by the aerodynamic load on the moving rudder surface (42) during the rudder deployment process to the maximum folding angle of the moving rudder surface (42).
4. The aircraft folding rudder deployment test device according to claim 1, characterized in that: The load simulation component (2) is detachably connected to the base (1) and the moving rudder surface (42).
5. A test system for testing the deployment and folding of rudders on an aircraft, characterized in that, The invention includes a test device for testing the folding rudder deployment of an aircraft as described in any one of claims 1-4.