Helicopter rudder connector test device and method

Abstract

The invention provides a helicopter rudder connector test device and method. The device comprises a large device platform (1), a loading cylinder (4), a T-shaped piece (7), a boundary simulation piece (8), a fish-shaped piece (9), a loading rotating bearing (11) and a supporting shaft (13). One end of the fish-shaped piece (9) is connected with the loading cylinder (4) through the loading joint (12), the other end is connected with the rudder connecting joint (6), and the lengths of force arms at the two ends are the same; according to the device, four connector tests can be carried out on one test platform at the same time, loading is converted through a specific mechanical structure, the difficulty that loading cannot be directly applied due to structural limitation of a test piece is effectively overcome, the device is stable in loading and free of additional bending moment, and the loading precision is not affected by the weight of a loading cylinder; and the purpose of completing the fatigue test of the helicopter rudder connector in a most economical and efficient manner can be achieved.

Description

Technical Field

[0001] This invention belongs to the field of fatigue testing technology for helicopter rudder connection joints, specifically relating to a testing device and method for helicopter rudder connection joints. Background Technology

[0002] The rudder is a key component of the helicopter flight control system, playing a crucial role in controlling the helicopter's flight. The reliability of the rudder connector's fatigue performance directly affects the helicopter's handling and safety. To understand the fatigue performance of the rudder connector, ground-based fatigue tests are necessary to determine its fatigue characteristics and ultimately its lifespan.

[0003] Currently, my country lacks fatigue testing equipment for coordinated loading of rudder connection joints in the helicopter field, making it impossible to simulate this test economically and efficiently. No relevant publicly available foreign literature was found. Summary of the Invention

[0004] This invention provides a test device and method for helicopter rudder connection joints. The device adopts an internal force-bearing structure design, which can simultaneously carry out four connection joint tests on a test platform. By converting the loading through a specific mechanical structure, it effectively solves the difficulty of directly applying loads due to structural interference of the test piece. Moreover, the loading point is stable without additional bending moment, which can achieve the purpose of completing the fatigue test of the helicopter rudder connection joint in the most economical and efficient way.

[0005] The first aspect of the present invention provides a test device for a helicopter rudder connection joint, comprising: a large platform 1, a loading cylinder 4, a T-shaped component 7, a boundary simulation component 8, a fish-shaped component 9, a loading rotation bearing 11, and a support shaft 13; The bottom surface of the T-shaped part 7 is fixedly connected to the large platform 1 of the device, and the upper part of the upright plate is provided with a central through hole; The boundary simulation component 8 has a cross-section in the shape of "[". The middle plate is bolted to the upright plate of the T-shaped component 7. The rudder connecting joint 6 is fixedly connected to the middle plate of the boundary simulation component 8 and connected to the two sides. It is located at the middle through hole of the corresponding upright plate. The rudder lugs of the rudder connecting joint 6 are arranged horizontally. The bottom surface of the support shaft 13 is fixed on the large platform 1 of the device, and the middle hole of the fish-shaped part 9 is rotatably connected to the upper part of the support shaft 13 through the loading rotating bearing 11; One end of the fish-shaped component 9 is connected to the loading cylinder 4 via the loading connector 12, and the other end is connected to the rudder connecting connector 6. The lever arm lengths of both ends are the same. Loading cylinder 4 is loaded on the horizontal plane where the rudder lug is located.

[0006] Optionally, the fish-shaped component 9 and the rudder connection joint 6 and the loading joint 12 are both rotatably connected to the fish-shaped component 9 using a single or double ear structure. The other end of the loading connector 12 is cylindrical and is inserted into the movable connection end of the loading cylinder 4.

[0007] Optionally, bushings are provided in both single and double ear structures.

[0008] Optionally, the large platform 1 of the device is also equipped with a loading cylinder base 3 and a loading cylinder weight offset support 5; The loading cylinder base 3 is rotatably connected to the tail of the loading cylinder 4; The load cylinder weight offset support 5 is located at the head of the outer shell of the load cylinder 4.

[0009] Optionally, clamping bushings are provided on the upper and lower surfaces of the load-bearing rotating bearing 11.

[0010] Optionally, the thickness of the clamping bushing is determined based on the height of the horizontal plane where the rudder lug is located.

[0011] Optionally, the rotating bearing 11 can be a spherical bearing.

[0012] Optionally, the shape of the T-shaped part 7 is consistent with the shape of the profile on which the rudder connecting joint 6 is connected to the fuselage; T-shaped part 7 is a metal structure.

[0013] Optionally, the support shaft 13 is a stepped columnar structure with a diameter that gradually increases from top to bottom.

[0014] A second aspect of the present invention provides a method for testing helicopter rudder connection joints, employing the helicopter rudder connection joint testing apparatus as described in any one of the first aspects, the method comprising: After receiving the loading command from the control system, loading cylinder 4 extends. When the loaded load reaches the set value, loading cylinder 4 remains in place for a preset time. After receiving an unloading command from the control system, loading cylinder 4 retracts.

[0015] This invention provides a testing device and method for helicopter rudder connectors. The fatigue test requires simultaneous loading of four rudder connectors, resulting in four loading loads. Previously, such fatigue tests were not conducted in the helicopter field. To achieve simultaneous testing of four rudder connectors, a helicopter rudder connector testing device was designed after research and analysis. This device adopts an internal force-bearing structure design, enabling simultaneous testing of four connectors on a single testing platform. By using a specific mechanical structure to convert the loading, it effectively overcomes the difficulty of directly applying loads due to structural limitations of the test piece. The device provides stable loading without additional bending moments, and the weight of the loading cylinder does not affect loading accuracy. It achieves the goal of completing the fatigue test of helicopter rudder connectors in the most economical and efficient way. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The 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.

[0017] Figure 1 This is a schematic diagram of the overall structure of the device of the present invention; Figure 2 This is a general schematic diagram of one of the typical structures of the device of the present invention; Figure 3 This is a schematic diagram of the load application and conversion structure of the present invention; Figure 4 This is a front view of the load transfer structure of the present invention; Figure 5 This is a schematic diagram of the fish-shaped component structure of the present invention; Explanation of reference numerals in the attached figures: The device consists of: 1. Large platform; 2. Connecting joint loading device; 3. Loading cylinder base; 4. Loading cylinder weight offset support; 5. Rudder connecting joint; 6. T-shaped part; 7. Boundary simulation part; 8. Fish-shaped part; 9. Pressing bushing; 10. Loading rotating bearing; 11. Loading joint; 12. Support shaft; 13. Detailed Implementation

[0018] 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.

[0019] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0020] The present invention will be further described in detail below with reference to the embodiments and accompanying drawings, but the embodiments of the present invention are not limited thereto.

[0021] like Figure 1-5 As shown, the present invention provides a test device for a helicopter rudder connection joint, comprising: a large platform 1, a connection joint loading device 2, a loading cylinder base 3, a loading cylinder 4, a loading cylinder weight offset support 5, a rudder connection joint 6, a T-shaped component 7, a boundary simulation component 8, a fish-shaped component 9, a clamping bushing 10, a loading rotation bearing 11, a loading joint 12, and a support shaft 13; wherein, The device is mounted on a large platform. All connectors, rudder connectors, fixing clamps, loading devices, etc., are fixedly installed on the large platform. This facilitates installation while ensuring that the device is an internally stressed structure, which is not limited by the site to a certain extent. The connecting joint loading device 2 is used for the test connection and loading of 4 rudder connecting joints. It has the ability to fix and transmit a certain load, and can simulate the boundary simulation conditions and load transmission path of the rudder connecting joint. This invention selects one of the test loading devices for detailed description. Load cylinder base 3. (As shown) Figure 2 As shown, it is fixed on the large platform 1 of the device and fixedly connected to the loading cylinder 4; Loading cylinder 4. Test loading mechanism, simulating load input device, connected to loading joint 12; The weight of the loading cylinder is offset by the support component 5. The bottom of this component is fixed to the large platform 1 of the device. The support component must keep the loading cylinder 4 in a horizontal state to eliminate the influence of the weight of the loading cylinder 4 on the loading load error. Rudder connector 6. Bottom surface connection boundary simulation part 8, the connector end is fixed to the fish-shaped part 9 by bolts; T-shaped component 7. The bottom fixed connection device large platform 1, the upper part of which is hollowed out to reduce the constraint on the boundary simulation component 8, so as to maximize the consistency between the boundary simulation of the rudder connection joint 6 and the real situation; Boundary simulation component 8. The bottom is fixedly connected to the T-shaped component 7, and the other side is connected to the rudder connection joint 6 by rivets, simulating the real installation environment of the rudder connection joint 6; Fish-shaped component 9. Fish-shaped component 9 is mounted on the support shaft 13 through the central hole. One end is connected to the loading joint 12, and the other end is connected to the rudder connection joint 6. The fish-shaped design effectively increases the rigidity of the component and reduces the loading error caused by deformation. Bushings are provided at both connection ends to effectively reduce the contact area and improve the load transfer efficiency. The equidistant lever arm setting effectively realizes the equivalent transfer of load, and there is no additional bending moment when loading. This solves the problem that the rudder connection joint cannot be directly loaded due to structural limitations. The clamping bushing 10 is installed on the upper and lower surfaces of the load rotating bearing to fix the load rotating bearing 11, and the height of the fish-shaped part 9 can be adjusted appropriately so that the loading point and the loading point of the rudder connection joint are on the same horizontal plane; Loading rotating bearing 11. The loading rotating bearing is installed between the fish-shaped parts 9 on the support shaft 13 to transfer the load by rolling friction, thereby improving the test loading accuracy; Loading connector 12. One end of the loading connector is connected to the loading cylinder 4, and the other end is connected to the fish-shaped part 9. Both fork mounting surfaces of the loading connector are equipped with bushings. Support shaft 13. The bottom surface of the support shaft is fixed on the large platform 1 of the device. The fish-shaped component 9 is installed on the intermediate shaft as the rotation center, which solves the problem of load transmission under structural constraints. The four connecting bolts on the bottom surface effectively improve the rigidity of the foundation support.

[0022] This application provides a test method for a helicopter rudder connection joint, including the following steps: The loading process; This device has a total of 4 loading actuators. One typical loading actuator is controlled by the control system to apply a specific load according to a given load spectrum. The typical loading actuator cylinder, upon receiving a command from the control system, extends. Once the load reaches the set value, the actuator holds the load for a certain period (load accuracy must meet requirements). Then, the control system issues a command to begin unloading, and the loading actuator cylinder retracts. Similarly, the typical loading actuator cylinder, after receiving a command from the control system, extends. Once the load reaches the set value, the actuator holds the load for a certain period (load accuracy must meet requirements). Then, the control system issues a command to begin unloading, and the typical loading actuator cylinder retracts. The typical loading actuator cylinder, after receiving a command from the control system, extends. Once the load reaches the set value, the actuator holds the load for a certain period (load accuracy must meet requirements). Then, the control system issues a command to begin unloading, and the typical loading actuator cylinder retracts. The typical loading actuator cylinder, after receiving a command from the control system, extends. Once the load reaches the set value, the actuator holds the load for a certain period (load accuracy must meet requirements). Then, the control system issues a command to begin unloading, and the typical loading actuator cylinder retracts.

[0023] Thus, following this process to complete one cycle, the four loads must maintain phase consistency, the load value accuracy must be controllable, and they must be controlled according to a certain load spectrum.

[0024] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A test device for a helicopter rudder connection joint, characterized in that, include: The device includes a large platform (1), a loading cylinder (4), a T-shaped component (7), a boundary simulation component (8), a fish-shaped component (9), a loading rotating bearing (11), and a support shaft (13). The bottom surface of the T-shaped part (7) is fixedly connected to the large platform (1) of the device, and the upper part of the upright plate is provided with a through hole in the middle; The boundary simulation component (8) has a cross-section of "[". The middle plate is bolted to the upright plate of the T-shaped component (7). The rudder connection joint (6) is fixedly connected to the middle plate of the boundary simulation component (8) and connected to both sides. It is located at the middle through hole of the corresponding upright plate. The rudder lugs of the rudder connection joint (6) are arranged horizontally. The bottom surface of the support shaft (13) is fixed on the large platform (1) of the device, and the middle hole of the fish-shaped part (9) is rotatably connected to the upper part of the support shaft (13) through the loading rotating bearing (11); One end of the fish-shaped part (9) is connected to the loading cylinder (4) through the loading connector (12), and the other end is connected to the rudder connecting connector (6). The lever arm lengths of both ends are the same. The loading cylinder (4) is loaded on the horizontal plane where the rudder lug is located.

2. The helicopter rudder connection joint test device according to claim 1, characterized in that, The fish-shaped component (9) and the rudder connection joint (6) and the loading joint (12) are connected to the fish-shaped component (9) by a single and double ear structure. The other end of the loading connector (12) is cylindrical and is inserted into the movable connection end of the loading cylinder (4).

3. The helicopter rudder connection joint testing device according to claim 2, characterized in that, Both single and double ear structures are equipped with bushings.

4. The helicopter rudder connection joint testing device according to claim 1, characterized in that, The large platform (1) of the device is also equipped with a loading cylinder base (3) and a loading cylinder weight offset support (5); The loading cylinder base (3) is rotatably connected to the tail of the loading cylinder (4); The load cylinder weight offset support (5) is located at the head of the outer shell of the load cylinder (4).

5. The helicopter rudder connection joint testing device according to claim 1, characterized in that, The upper and lower surfaces of the load-bearing rotating bearing (11) are provided with clamping bushings.

6. The helicopter rudder connection joint testing device according to claim 5, characterized in that, The thickness of the clamping bushing is determined based on the height of the horizontal plane where the rudder lug is located.

7. The helicopter rudder connection joint testing device according to claim 1, characterized in that, The rotating bearing (11) is a spherical bearing.

8. The helicopter rudder connection joint testing device according to claim 1, characterized in that, The shape of the T-shaped part (7) is consistent with the shape of the profile of the rudder connecting joint (6) connected to the fuselage; The T-shaped part (7) is a metal structure.

9. The helicopter rudder connection joint testing device according to claim 1, characterized in that, The support shaft (13) is a stepped columnar structure whose diameter gradually decreases from top to bottom.

10. A test method for a helicopter rudder connection joint, characterized in that, The method using the helicopter rudder connection joint test apparatus as described in any one of claims 1-9 includes: After receiving the loading command from the control system, the loading cylinder (4) extends. When the load reaches the set value, the loading cylinder (4) remains for a preset time. After receiving the unloading command from the control system, the loading cylinder (4) retracts.

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