Aircraft control surface test device

Abstract

The utility model discloses an aircraft control surface test device, which comprises a test rack assembly, the test rack assembly comprises a test rack body, a control surface connecting joint is arranged on one side of the test rack body, a control surface is arranged on the control surface connecting joint, a steering engine is arranged on one side of the control surface, the steering engine is arranged on the test rack body, and the test rack body is connected with the test rack body. The control surface is connected with a steering engine, and a loading structure is installed on the control surface. The device has multiple examination structures: a fatigue test is carried out on the ground, reciprocating motion is carried out for multiple times, the structural strength of a control surface is examined, and the strength of a connecting rod and a steering engine connecting joint and the reliability of a steering engine are examined; the lower part of the test assembly is provided with fixable trundles, so that the test assembly is convenient to move, and meanwhile, during a test, fixing screws of the trundles are adjusted to complete fixation.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, in particular to an aircraft control surface test device. Background Art

[0002] The rudder refers to the wing surface on the wing and tail of the aircraft that can be controlled by manipulation or follow-up control. During the flight, the aircraft can change the aerodynamic force by controlling the rudder to adapt to the flight requirements of the current flight environment and meet the aircraft control requirements, such as completing the change of the aircraft's roll, yaw, pitch and other flight attitudes. The importance of the rudder in the flight process is self-evident, so it is necessary to fully verify it to ensure that the rudder and the rudder control system are safe enough. Before the aircraft test flight, it is necessary to design a rudder test device on the ground to verify the rudder to ensure the structural strength of the rudder and the reliability of the mechanism and equipment that control the rudder. However, some existing rudder test devices, such as the device published in Patent 202311756337.0 (A kind of aircraft rudder loading test device and aircraft rudder loading test method), although completed the loading of the rudder, it did not assess the entire system and was only suitable for the rudder test of large transport aircraft. For small and medium-sized aircraft, the system is complex and the cost is high. Utility Model Content

[0003] The purpose of the utility model is to provide an aircraft rudder surface test device to solve the problems mentioned in the background technology. To achieve the above purpose, the utility model provides the following technical solutions: an aircraft rudder surface test device, including a test frame assembly, the test frame assembly includes a test frame body, a rudder surface connection joint is installed on one side of the test frame body, a rudder surface is installed on the rudder surface connection joint, a steering gear is provided on one side of the rudder surface, the steering gear is installed on the test frame body, the rudder surface is connected to the steering gear, and a loading structure is installed on the rudder surface.

[0004] Preferably, the test frame body includes a plurality of spliced ​​beams, and the plurality of spliced ​​beams are spliced ​​into a frame structure through diagonally braced steel plates, a supporting beam is installed on one side of the top of the frame structure, a servo connecting plate is connected between the supporting beam and the frame structure, the servo is installed on the servo connecting plate, the rudder surface connecting joint is installed on one side of the supporting beam, and casters are installed at the bottom of the frame structure.

[0005] Preferably, the steering gear connecting plate is provided with a mounting opening, and the steering gear is mounted at the mounting opening.

[0006] Preferably, a mounting seat is installed on the rudder surface, a connecting rod is installed on the mounting seat, and the connecting rod is connected to the steering gear.

[0007] Preferably, the loading structure comprises a lifting eye screw, one end of which passes through the rudder surface to connect an inclined washer and a nut.

[0008] The technical effects and advantages of the utility model are as follows: the device has multiple test structures: fatigue tests are carried out on the ground, with multiple reciprocating movements. In addition to testing the structural strength of the rudder surface, the strength of the connecting rod and the steering gear connection joint and the reliability of the steering gear are also tested;

[0009] Easy to move: The lower part of the test assembly is equipped with fixed casters for easy movement. During the test, the fixing screws of the casters can be adjusted to complete the fixation.

[0010] Low cost: The test frame body is welded with standard square steel profiles and flat plates, and the cost of raw materials is low;

[0011] High safety: Tests are conducted on ground benches instead of on aircraft. When the ground meets the requirements, the safety of the entire system can be ensured in flight.

[0012] The rudder surface is reusable: After the test is completed, the loading structure is removed and the holes on the rudder surface are plugged with countersunk rivets. The rudder surface can still be installed on the aircraft for flight, saving the rudder surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is an axonometric drawing of the utility model;

[0014] Figure 2 It is an exploded view of the utility model;

[0015] Figure 3 It is an axonometric drawing of the test stand assembly of the utility model;

[0016] Figure 4 This is an axonometric view of the test stand body of the utility model;

[0017] Figure 5 It is an axonometric diagram of the rudder surface and the loading structure of the utility model installed together;

[0018] Figure 6 It is a partial axonometric diagram of the rudder surface of the utility model at a loading structure;

[0019] Figure 7 It is a cross-sectional view of the loading structure of the utility model.

[0020] In the figure, 1. test frame assembly; 11. test frame body; 111. support beam; 112. servo connection plate; 113. caster; 114. splicing beam; 12. rudder surface connection joint; 2. rudder surface; 21. connecting rod; 3. loading structure; 31. lifting eye screw; 32. inclined gasket; 33. nut; 4. servo. DETAILED DESCRIPTION

[0021] In order to make the technical means for realizing the utility model, creative features, objectives and effects easy to understand, the utility model is further explained below in conjunction with specific diagrams. In the description of the utility model, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, an integral connection or a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two components.

[0022] Example

[0023] like Figure 1 and Figure 2 As shown, the utility model is an aircraft control surface test device, including a test frame assembly 1, a control surface 2, a loading structure 3, and a steering gear 4, wherein the structural form and relative position of the connection between the control surface 2 and the steering gear 4 are consistent with those on the aircraft, so as to test the real state to the greatest extent and make the test more accurate.

[0024] like Figure 3 As shown, the test frame assembly 1 includes a test frame body 11 and a rudder surface connection joint 12. The rudder surface connection joint 12 is installed on one side of the test frame body 11, and the rudder surface 2 is installed on the rudder surface connection joint 12; the rudder surface connection joint uses the same material, the same position, and the same structure as the connection joint on the aircraft. In this way, when doing the test, the strength of the rudder surface connection joint can be assessed. Once the problem of insufficient strength occurs during the test, it can be reinforced in time to prevent problems during flight and improve safety. The test frame body is the foundation of the entire test device, providing support to ensure that the test can be completed smoothly; the servo 4 is located on one side of the rudder surface 2, the servo 4 is installed on the test frame body 1, and the rudder surface 2 is connected to the servo 4.

[0025] like Figure 4As shown, the test frame body 11 includes a support beam 111, a steering gear connecting plate 112, a caster 113, and a splicing beam 114. There are multiple splicing beams 114, which are spliced ​​into a frame structure through diagonal steel plates. The support beam 111 is installed on one side of the top of the frame structure. The steering gear connecting plate 112 is connected between the support beam 111 and the frame structure. The steering gear 4 is installed on the steering gear connecting plate 112, and the rudder surface connection joint 12 is installed on one side of the support beam 111. The caster 113 is installed at the bottom of the frame structure; the support beam 111 and the splicing beam 114 are square profiles with the same cross-sectional size, preferably made of Q345 steel to ensure the strength requirements when connected to the rudder surface connection joint 12, and at the same time have good welding characteristics to reduce manufacturing costs. This example uses a square steel section with a wall thickness of 150mm and a thickness of 3mm. The steering gear connecting plate 112 is connected to the steering gear 4 by bolts to support the steering gear 4 and bear the working force of the steering gear 4. The steering gear connecting plate 112 is welded together with the support beam 111 and the splicing beam 114, providing the steering gear connecting plate 112 with high rigidity. The support beam 111 is designed with an opening at the back of the connection between the rudder surface connection joint 12, which is convenient for the installation of the fasteners connecting the rudder surface connection joint 12 to the support beam 111. A larger installation opening is designed at the position of the steering gear connecting plate 112, and the steering gear is installed at the installation opening. The installation opening provides a channel for the installation and removal of the steering gear 4. The caster 113 is a horizontal adjustment wheel. When the test frame body needs to be transferred, it is adjusted to a rolling state and can be pushed manually. When doing a test, the test frame body 11 is fixed to the ground by adjusting the screws to keep it still. The splicing beams 114 are welded and strengthened by the steel plates of the diagonal braces to form a frame structure. The entire test frame body adopts a steel structure. In addition to low cost, the test frame body 11 structure is also relatively heavy. In this way, the weight of the entire test frame body 11 can resist the weight mounted on the rudder surface 2 during the test, and the stability of the test device can be maintained without adding additional ballast.

[0026] like Figure 5 and Figure 6 As shown, the rudder surface 2 is connected with a loading structure 3, which is connected to the skeleton inside the rudder surface 2. The front and rear positions are determined by calculating the bending moment and aerodynamic distribution of the aerodynamic force on the rudder surface 2. First, the aerodynamic distribution is integrated to determine the load size of the three places, and then the distance from the axis of the rudder surface 2 is obtained by dividing the bending moment by the load size according to the load size and the position of the rudder surface rotating shaft. The loading structure includes a lifting eye screw 21, an inclined washer 21, and a nut 33. The length of the lifting eye screw 21 is long enough to penetrate the depth of the entire rudder surface 2. The inclined washer 21 makes the surface that cooperates with the nut 22 into a plane to prevent the surface of the rudder surface 2 from being crushed when the nut 22 is directly installed. A mounting seat is installed on the rudder surface 2, and a connecting rod 21 is installed on the mounting seat. The connecting rod 21 is connected to the steering gear 4. When using the device, the rudder surface 2 and the steering gear 4 are installed on the test frame assembly 1. By applying a heavy object to the loading structure 3, the steering gear 4 pushes the rudder surface 2 to reciprocate through the connecting rod 21 to complete the test.

[0027] like Figure 7 As shown, the eye of the eye screw 21 faces downward. In this way, when testing, the rudder surface 2 is loaded by hanging heavy objects. The bottom surface of the inclined gasket 32 ​​is consistent with the upper surface of the rudder surface 2 in shape to ensure accurate fitting. The inclined gasket 32 ​​is preferably made of aluminum alloy, and its diameter is larger than the diameter of the nut. When the nut 33 is tightened, the preload on the rudder surface 2 is dispersed to prevent the rudder surface 2 from being crushed. A through hole is designed at the position where the rudder surface 2 is connected to the eye screw 31. After the test is completed, the hole is filled with resin or a countersunk rivet is used to fill the hole, while ensuring that the surface is flush. In this way, the rudder surface can still be installed on the aircraft for flight, saving the rudder surface.

[0028] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft control surface test device, comprising a test frame assembly, characterized in that: The test frame assembly includes a test frame body, a rudder surface connection joint is installed on one side of the test frame body, a rudder surface is installed on the rudder surface connection joint, a steering gear is provided on one side of the rudder surface, the steering gear is installed on the test frame body, the rudder surface is connected to the steering gear, and a loading structure is installed on the rudder surface.

2. The aircraft control surface test device according to claim 1, characterized in that: The test frame body includes a plurality of spliced ​​beams, and the plurality of spliced ​​beams are spliced ​​into a frame structure through diagonally braced steel plates. A support beam is installed on one side of the top of the frame structure, a steering gear connecting plate is connected between the support beam and the frame structure, the steering gear is installed on the steering gear connecting plate, the rudder surface connecting joint is installed on one side of the support beam, and casters are installed on the bottom of the frame structure.

3. The aircraft control surface test device according to claim 2, characterized in that: The steering gear connecting plate is provided with a mounting opening, and the steering gear is mounted at the mounting opening.

4. The aircraft control surface test device according to claim 1, characterized in that: A mounting seat is installed on the rudder surface, a connecting rod is installed on the mounting seat, and the connecting rod is connected to the steering gear.

5. The aircraft control surface test device according to claim 1, characterized in that: The loading structure comprises a lifting eye screw, one end of which passes through the rudder surface and is connected to an inclined washer and a nut.

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