Adjusting device for horizontal loading test of control surface of unmanned aerial vehicle

Abstract

The invention provides an unmanned aerial vehicle control surface horizontal loading test adjusting device, and belongs to the technical field of unmanned aerial vehicle tests.The device comprises a fixed rack, a control surface base, an adjusting assembly and a control surface movement assembly, and the control surface base is hinged to the fixed rack and can rotate up and down; the adjusting assembly is connected to the control surface base and can drive the control surface base to rotate; the control surface movement assembly is installed on the control surface base and used for controlling the control surface to act. According to the device, the angle of the control surface base can be adjusted through the adjusting assembly, so that the control surface is always kept in a horizontal state, a loading test can be conveniently carried out through the gravity effect in the later period, and stress measurement can be carried out on the control surface under the condition that a wind tunnel test is not carried out. And the device can adapt to different control surface gravity loading tests by replacing different control surface motion assemblies, and has good universality.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicle testing, and more specifically, relates to a horizontal loading test adjustment device for a rudder surface of an unmanned aerial vehicle. Background Art

[0002] Before the drone's rudder is officially installed, it is necessary to conduct a static loading test on the aircraft's rudder, and at the same time test the accessibility of the rudder movement, etc., to ensure that the performance of the rudder can meet the relevant technical requirements of the aircraft. The test of the aircraft's rudder is a key technical means to assess the success of the rudder design, and is an indispensable link to ensure the normal flight and maneuvering of the aircraft.

[0003] At present, the structure of the transmission rudder surface test device is relatively fixed, the angles of the rudder surface and the test fixture cannot be adjusted at the same time, and it is impossible to use the same test device to simulate various working conditions of the aircraft's rudder surface during flight. Summary of the invention

[0004] The purpose of the present invention is to provide a device for adjusting the horizontal loading test of the rudder surface of an unmanned aerial vehicle, so as to solve the problem that the angle of the existing test device and the rudder surface cannot be adjusted at the same time.

[0005] In order to achieve the above object, the present invention provides a UAV rudder horizontal loading test adjustment device, comprising:

[0006] Fixed stand;

[0007] A rudder base, the rudder base is hinged to the fixed frame and can rotate up and down;

[0008] An adjusting component, the adjusting component is connected to the rudder surface base and can drive the rudder surface base to rotate;

[0009] A rudder surface motion component is installed on the rudder surface base and is used to control the movement of the rudder surface.

[0010] Optionally, the UAV rudder horizontal loading test adjustment device further includes:

[0011] The reaction wall, the fixed platform is fixedly installed on the reaction wall.

[0012] Optionally, the reaction wall is L-shaped.

[0013] Optionally, the fixed stand comprises:

[0014] Fixed frame;

[0015] An ear hinge mounting base plate, the ear hinge mounting base plate is arranged on the fixing frame, and the ear hinge mounting base plate is provided with a pair of ear hinge mounting ears;

[0016] The screw support ear connection base is fixedly connected to the fixing frame, and the screw support ear connection base is provided with a pair of screw hinge mounting ears.

[0017] Optionally, the adjustment component includes:

[0018] Lead screw;

[0019] A lead screw nut, the lead screw nut being threadedly connected to one end of the lead screw;

[0020] A bearing mounting block, the bearing mounting block being movably sleeved on the outer periphery of the lead screw nut and connected to the lead screw nut;

[0021] A tapered roller bearing, the tapered roller bearing having a first rotating part and a second rotating part that can rotate relative to each other, the first rotating part being mounted on the bearing mounting block;

[0022] A pair of screw nut connecting ears, the pair of screw nut connecting ears are arranged on the second rotating part, and the pair of screw nut connecting ears are hinged to the pair of screw hinge mounting ears;

[0023] A joint bearing is arranged at the other end of the lead screw and is rotatably connected to the rudder surface base.

[0024] Optionally, the rudder base comprises:

[0025] A base fixing bracket, the base fixing bracket having a vertically arranged vertical frame and a horizontally arranged horizontal frame, the horizontal frame being fixedly connected to the middle of the vertical frame and extending in a direction away from the fixed stand;

[0026] A base fixing plate, the base fixing plate is vertically mounted on the upper part of the vertical frame;

[0027] A plurality of gooseneck ear bases, wherein the plurality of gooseneck ear bases are arranged on the upper portion of a side of the base fixing plate facing away from the fixing stand;

[0028] A steering gear hinge base, the steering gear hinge base being arranged on a side of the base fixing plate away from the fixing stand and lower than the gooseneck ear base;

[0029] A lower connecting rod base, the lower connecting rod base being arranged near an edge of the cross frame;

[0030] A lead screw connecting pin shaft nut assembly, wherein the lead screw connecting pin shaft nut assembly is arranged at the lower part of the cross frame;

[0031] A pair of rudder surface base motion ears, the pair of rudder surface base motion ears are arranged on the other side of the base fixing plate facing the fixed platform, and the pair of rudder surface base motion ears are rotatably connected with a pair of ear piece hinge mounting ears.

[0032] Optionally, the rudder surface motion assembly includes:

[0033] Rudder surface;

[0034] A plurality of rudder surface gooseneck assemblies, wherein the plurality of gooseneck assemblies are arranged at one end of the rudder surface and are rotatably connected to the plurality of gooseneck ear bases;

[0035] An upper connecting rod connecting lug, wherein the upper connecting rod connecting lug is arranged on the lower surface of the rudder surface;

[0036] A driving assembly is connected to the upper connecting rod connecting lug and is used for driving the rudder surface to move.

[0037] Optionally, the number of the rudder surface gooseneck assembly and the number of the gooseneck ear bases are both three.

[0038] Optionally, the driving assembly comprises:

[0039] A steering gear body, wherein a fixed end of the steering gear body is rotatably connected to the steering gear hinge base;

[0040] A connecting rod assembly connects the servo body and the rudder surface and is used for converting the telescopic action of the servo body into the rotational action of the rudder surface.

[0041] Optionally, the telescopic end of the steering gear body is rotatably connected to a steering gear push rod, and the steering gear push rod is vertically arranged to the steering gear body;

[0042] The connecting rod assembly comprises:

[0043] An upper connecting rod, one end of which is rotatably connected to the steering gear push rod, and the other end of which is rotatably connected to the upper connecting rod connecting lug;

[0044] A lower connecting rod, one end of which is rotatably connected to the steering gear push rod, and the other end of which is rotatably connected to the lower connecting rod base.

[0045] The beneficial effects of the present invention are: providing an adjustment device for the horizontal loading test of the rudder surface of an unmanned aerial vehicle, comprising: a fixed stand, a rudder surface base and an adjustment component rudder surface motion component, the rudder surface base is hinged to the fixed stand and can rotate up and down; the adjustment component is connected to the rudder surface base and can drive the rudder surface base to rotate; the rudder surface motion component is installed on the rudder surface base to control the movement of the rudder surface. The device can adjust the angle of the rudder surface base through the adjustment component, so that the rudder surface always remains in a horizontal state, which is convenient for subsequent loading tests through gravity, and can measure the force on the rudder surface without conducting a wind tunnel test. It can also adapt to different rudder surface gravity loading tests by replacing different rudder surface motion components, and has good versatility.

[0046] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0048] Figure 1 One of the schematic structural diagrams of a UAV rudder horizontal loading test adjustment device according to an embodiment of the present invention is shown.

[0049] Figure 2 A second schematic structural diagram of a UAV rudder horizontal loading test adjustment device according to an embodiment of the present invention is shown.

[0050] Figure 3 A schematic structural diagram of a fixed stand according to an embodiment of the present invention is shown.

[0051] Figure 4 A schematic structural diagram of a screw support lug connection base according to an embodiment of the present invention is shown.

[0052] Figure 5 One of the schematic structural diagrams of an adjustment component according to an embodiment of the present invention is shown.

[0053] Figure 6 A second schematic structural diagram of an adjustment component according to an embodiment of the present invention is shown.

[0054] Figure 7 One of the schematic structural diagrams of a rudder surface base according to an embodiment of the present invention is shown.

[0055] Figure 8 The second schematic structural diagram of a rudder surface base according to an embodiment of the present invention is shown.

[0056] Fig. 9 A schematic structural diagram of a control surface motion assembly according to an embodiment of the present invention is shown.

[0057] Description of reference numerals:

[0058] 1. Fixed stand; 1-1. Fixed stand; 1-2. Ear hinge mounting base; 1-3. Adjustment assembly; 1-3-1. Screw nut connecting lug; 1-3-2. Bearing mounting block; 1-3-3. Screw nut; 1-3-5. Spherical bearing; 1-3-6. Tapered roller bearing; 1-4. Screw lug connecting base; 1-5. Ear hinge mounting lug; 1-6. Screw hinge mounting lug;

[0059] 2. Reaction wall;

[0060] 3. Rudder base; 3-1. Gooseneck ear base; 3-4. Servo connection base; 3-5. Lower connecting rod base; 3-6. Base fixing bracket; 3-7. Base fixing plate; 3-8. Screw connecting pin nut assembly; 3-9. Rudder base moving ear;

[0061] 4. Rudder surface movement assembly; 4-1. Rudder surface; 4-4. Rudder surface gooseneck assembly; 4-5. Upper connecting rod connecting lug; 4-6. Upper connecting rod; 4-7. Servo push rod; 4-8. Lower connecting rod; 4-9. Servo body. DETAILED DESCRIPTION

[0062] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0063] like Figure 1 and 2 As shown, the present invention provides a UAV rudder horizontal loading test adjustment device, which is characterized by comprising:

[0064] Fixed stand 1;

[0065] A rudder base 3, which is hinged to the fixed frame 1 and can rotate up and down;

[0066] An adjusting component, which is connected to the rudder surface base 3 and can drive the rudder surface base 3 to rotate;

[0067] The rudder surface motion component 4 is installed on the rudder surface base 3 and is used to control the movement of the rudder surface 4-1.

[0068] Specifically, the angle of the rudder surface 4-1 changes when it opens and closes. The UAV rudder surface horizontal loading test adjustment device can adjust the angle of the rudder surface base 3 through the adjustment component, so that the rudder surface 4-1 always remains horizontal, which is convenient for the subsequent loading test by gravity, and can measure the force of the rudder surface 4-1 without a wind tunnel test. It can also adapt to different rudder surface gravity loading tests by replacing different rudder surface motion components 4, and has good versatility.

[0069] Optionally, the UAV rudder horizontal loading test adjustment device further includes:

[0070] The reaction wall 2, the fixed platform 1 is fixedly installed on the reaction wall 2.

[0071] Optionally, the reaction wall 2 is L-shaped.

[0072] In this embodiment, the reaction wall 2 has a horizontal base and a longitudinal reaction wall. The fixed platform 1 is installed on the horizontal base and the longitudinal reaction wall by bolts. The horizontal base is connected to the ground and provides vertical support force for the fixed platform 1. The longitudinal reaction wall provides horizontal reaction force for the fixed platform 1.

[0073] like Figure 3 and 4 As shown, optionally, the fixed stand 1 includes:

[0074] Fixed frame 1-1;

[0075] The ear hinge mounting base plate 1-2 is arranged on the fixing frame 1-1, and the ear hinge mounting base plate 1-2 is provided with a pair of ear hinge mounting ears 1-5;

[0076] The screw support ear connection base 1-4 is fixedly connected to the fixing frame 1-1, and the screw support ear connection base 1-4 is provided with a pair of screw hinge mounting ears 1-6.

[0077] like Figure 5 and 6 As shown, optionally, the adjustment component 1-3 includes:

[0078] Lead screw 1-3-4;

[0079] A lead screw nut 1-3-3, the lead screw nut 1-3-3 is threadedly connected to one end of the lead screw 1-3-4;

[0080] The bearing mounting block 1-3-2 is movably sleeved on the outer periphery of the screw nut 1-3-3 and connected to the screw nut 1-3-3;

[0081] A tapered roller bearing 1-3-6, wherein the tapered roller bearing 1-3-6 has a first rotating portion and a second rotating portion that can rotate relative to each other, and the first rotating portion is mounted on the bearing mounting block 1-3-2;

[0082] A pair of screw nut connecting ears 1-3-1, a pair of screw nut connecting ears 1-3-1 are arranged on the second rotating part, and a pair of screw nut connecting ears 1-3-1 are hinged to a pair of screw hinge mounting ears 1-6;

[0083] The joint bearing 1-3-5 is arranged at the other end of the screw 1-3-4, and the joint bearing 1-3-5 is rotatably connected to the rudder base 3.

[0084] In this embodiment, the fixing frame 1-1 is bolted to the reaction wall 2, the ear hinge mounting ear 1-5 is fixed to the ear hinge mounting base 1-2 to form a whole, the ear hinge mounting base 1-2 and the screw ear connecting base 1-4 are fixed to the fixing frame 1-1, and the adjusting component 1-3 is hinged with the screw ear connecting base 1-4 through the screw nut connecting ear 1-3-1 to form a rotating pair, and the adjusting component 1-3 contains a spiral pair, and the relative length between the screw 1-3-4 and the screw nut 1-3-3 can be adjusted by the relative rotation of the two.

[0085] like Figure 7 and 8 As shown, optionally, the rudder base 3 includes:

[0086] The base fixing bracket 3-6 comprises a vertical frame arranged vertically and a horizontal frame arranged horizontally, wherein the horizontal frame is fixedly connected to the middle of the vertical frame and extends in a direction away from the fixing stand 1;

[0087] A base fixing plate 3-7, the base fixing plate 3-7 is vertically mounted on the upper part of the vertical frame;

[0088] A plurality of gooseneck ear bases 3-1, wherein the plurality of gooseneck ear bases 3-1 are arranged on the upper portion of a side of the base fixing plate 3-7 which faces away from the fixing stand 1;

[0089] A steering gear hinge base 3-4, the steering gear hinge base 3-4 is arranged on a side of the base fixing plate 3-7 away from the fixed platform 1 and lower than the gooseneck ear base 3-1;

[0090] A lower connecting rod base 3-5, wherein the lower connecting rod base 3-5 is arranged near the edge of the cross frame;

[0091] The lead screw is connected to the pin shaft nut assembly 3-8, and the lead screw is connected to the pin shaft nut assembly 3-8 and is arranged at the lower part of the cross frame;

[0092] A pair of rudder base moving ears 3-9 are arranged on the other side of the base fixing plate 3-7 facing the fixed platform 1, and the pair of rudder base moving ears 3-9 are rotatably connected with a pair of ear hinge mounting ears 1-5.

[0093] In this embodiment, the base fixing plate 3-7 is fixed on the base fixing bracket 3-6 to form a fixed whole, the rudder surface base movement ear 3-9 is located on the back of the base fixing plate 3-7, and is hinged with the middle ear hinge mounting ear 1-5 of the fixed platform 1 to form a rotation pair, so that the rudder surface base 3 can rotate relative to the fixed platform 1; the gooseneck ear base 3-1 and the steering gear hinge base 3-4 are bolted and fixed to the base fixing plate 3-7, the lower connecting rod base 3-5 is bolted and fixed to the base fixing bracket 3-6, forming an articulated interface with the rudder surface movement component 4, and the screw connecting pin nut component 3-8 is located at the bottom of the base fixing bracket 3-6, and cooperates with the joint bearing 1-3-5 in the adjustment component 1-3 to form a rotation pair, so as to adjust the angle between the rudder surface base 3 and the fixed platform 1.

[0094] like Fig. 9 As shown, optionally, the rudder surface motion component 4 includes:

[0095] Rudder 4-1;

[0096] A plurality of rudder surface gooseneck assemblies 4-2, wherein the plurality of gooseneck assemblies 4-2 are arranged at one end of the rudder surface 4-1 and are rotatably connected to the plurality of gooseneck ear piece bases 3-1;

[0097] The upper connecting rod connecting lug 4-5 is arranged on the lower surface of the rudder surface 4-1;

[0098] A driving assembly is connected to the upper connecting rod connecting lug 4-5 and is used to drive the rudder surface 4-1 to move.

[0099] Optionally, the number of the rudder gooseneck assembly 4-2 and the number of the gooseneck ear base 3-1 are both three.

[0100] Specifically, the three control surface gooseneck assemblies 4-2 and the three gooseneck ear bases 3-1 are evenly arranged to ensure the stable rotation of the control surface 4-1.

[0101] Optionally, the drive assembly includes:

[0102] A steering gear body 4-9, the fixed end of which is rotatably connected to the steering gear hinge base 3-4;

[0103] The connecting rod assembly connects the servo body 4-9 and the rudder surface 4-1, and is used to convert the telescopic action of the servo body 4-9 into the rotational action of the rudder surface 4-1.

[0104] Specifically, the connecting rod assembly can be set in various forms according to experimental requirements to verify the accessibility of various different connecting rod assembly movements.

[0105] Optionally, the telescopic end of the servo body 4-9 is rotatably connected to a servo push rod 4-7, and the servo push rod 4-7 is vertically arranged with the servo body 4-9;

[0106] The connecting rod assembly includes:

[0107] An upper connecting rod 4-6, one end of which is rotatably connected to the steering gear push rod 4-7, and the other end of which is rotatably connected to the upper connecting rod connecting lug 4-5;

[0108] A lower connecting rod 4-8, one end of the lower connecting rod 4-8 is rotatably connected to the steering gear push rod 4-7, and the other end of the lower connecting rod 4-8 is rotatably connected to the lower connecting rod base 3-5.

[0109] In this embodiment, the rudder surface gooseneck assembly 4-2 is installed at a relatively rotating end of the rudder surface 4-1 at a certain distance relationship, and forms a rotation pair corresponding to the position of the gooseneck ear base 3-1 in the rudder surface base 3. The rear ear of the servo body 4-9 corresponds to the position of the servo connection base 3-4 in the rudder surface base 3 to form a rotation pair. The upper connecting rod connecting ear 4-5 is fixed to the lower surface position of the rudder surface 4-1 and is hinged to form a rotation pair with the other end of the upper connecting rod 4-6. The other end of the lower connecting rod 4-8 is connected to the lower connecting rod base 3-4. The seat 3-5 is hinged to form a rotating pair, one end of the lower connecting rod 4-8 is connected to one end of the upper connecting rod 4-6 and the steering gear push rod 4-7 through a pin to form a three-joint rotating pair, and a moving pair is formed between the steering gear body 4-9 and the steering gear push rod 4-7 to become a power source device. The upper connecting rod connecting the support ear 4-5, the upper connecting rod 4-6, the lower connecting rod 4-8, the steering gear push rod 4-7, and the steering gear body 4-9 constitute a connecting rod assembly, thereby realizing the relative rotation of the rudder surface 4-1 with respect to the gooseneck assembly and realizing the opening and closing action of the rudder surface 4-1.

[0110] The working principle of the UAV rudder horizontal loading test adjustment device of this embodiment is as follows:

[0111] First, the rudder surface movement assembly 4 drives the rudder surface 4-1 to the desired attitude angle and keeps it fixed through the servo body 4-9 and the connecting rod assembly. During this operation, the rudder surface 4-1 will rotate along the rotation axis formed by the gooseneck ear base 3-1 as the servo assembly works, that is, the rudder surface 4-1 rotates relative to the rudder surface base 3.

[0112] Secondly, since the screw nut connecting ear 1-3-1 at one end of the adjusting component 1-3 is connected to the screw connecting ear base 1-4 of the fixed platform 1 to form a rotating pair, the screw 1-3-4 at the other end is connected to the screw connecting pin nut assembly 3-8 in the rudder base 3 through the joint bearing 1-3-5 to form a rotating pair. By adjusting the screw nut 1-3-3 in the adjusting component 1-3, as the screw nut 1-3-3 rotates, the spiral pair in the adjusting component 1-3 works, thereby driving the rudder base 3 connected by the screw 1-3-4 to rotate with the rotating pair composed of the ear hinge mounting ear 1-5 in the fixed platform 1. By adjusting the length of the adjusting component 1-3, the rotation of the rudder base 3 relative to the fixed platform 1 can be achieved.

[0113] Finally, by measuring the rotation angle θ of the rudder surface 4-1 relative to the rudder surface base 3, and then reversely adjusting the rotation angle -θ of the rudder surface base 3 relative to the fixed platform 1, the rudder surface 4-1 can always be kept in a horizontal position, which is convenient for later tests under different angle conditions.

[0114] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A UAV rudder horizontal loading test adjustment device, characterized in that: include: Fixed stand (1); A rudder base (3), the rudder base (3) being hinged to the fixed stand (1) and capable of rotating up and down; An adjusting component (1-3), the adjusting component (1-3) being connected to the rudder surface base (3) and capable of driving the rudder surface base (3) to rotate; A rudder surface motion component (4), the rudder surface motion component (4) is installed on the rudder surface base (3) and is used to control the movement of the rudder surface (4-1).

2. The UAV control surface horizontal loading test adjustment device according to claim 1 is characterized in that: Also includes: A reaction wall (2), wherein the fixed stand (1) is fixedly mounted on the reaction wall (2).

3. The UAV rudder horizontal loading test adjustment device according to claim 2 is characterized in that: The reaction wall (2) is L-shaped.

4. The UAV control surface horizontal loading test adjustment device according to claim 1 is characterized in that: The fixed stand (1) comprises: Fixed frame (1-1); An ear hinge mounting base plate (1-2), the ear hinge mounting base plate (1-2) being arranged on the fixing frame (1-1), and the ear hinge mounting base plate (1-2) being provided with a pair of ear hinge mounting ears (1-5); A screw support lug connection base (1-4), wherein the screw support lug connection base (1-4) is fixedly connected to the fixing frame (1-1), and the screw support lug connection base (1-4) is provided with a pair of screw hinge mounting lugs (1-6).

5. The UAV rudder horizontal loading test adjustment device according to claim 4 is characterized in that: The regulating component (1-3) comprises: Lead screw (1-3-4); A lead screw nut (1-3-3), wherein the lead screw nut (1-3-3) is threadedly connected to one end of the lead screw (1-3-4); A bearing mounting block (1-3-2), the bearing mounting block (1-3-2) being movably sleeved on the outer periphery of the lead screw nut (1-3-3) and connected to the lead screw nut (1-3-3); A tapered roller bearing (1-3-6), the tapered roller bearing (1-3-6) comprising a first rotating part and a second rotating part that can rotate relative to each other, the first rotating part being mounted on the bearing mounting block (1-3-2); A pair of screw nut connecting ears (1-3-1), the pair of screw nut connecting ears (1-3-1) are arranged on the second rotating part, and the pair of screw nut connecting ears (1-3-1) are hinged to the pair of screw hinge mounting ears (1-6); A joint bearing (1-3-5), wherein the joint bearing (1-3-5) is arranged at the other end of the lead screw (1-3-4), and the joint bearing (1-3-5) is rotatably connected to the rudder surface base (3).

6. The UAV rudder horizontal loading test adjustment device according to claim 5, characterized in that: The rudder surface base (3) comprises: A base fixing bracket (3-6), the base fixing bracket (3-6) comprising a vertically arranged vertical frame and a horizontally arranged horizontal frame, the horizontal frame being fixedly connected to the middle of the vertical frame and extending in a direction away from the fixed stand (1); A base fixing plate (3-7), wherein the base fixing plate (3-7) is vertically mounted on the upper part of the vertical frame; A plurality of gooseneck ear bases (3-1), wherein the plurality of gooseneck ear bases (3-1) are arranged on the upper portion of a side of the base fixing plate (3-7) facing away from the fixing stand (1); A steering gear hinge base (3-4), the steering gear hinge base (3-4) being arranged on a side of the base fixing plate (3-7) facing away from the fixing platform (1) and lower than the gooseneck ear base (3-1); A lower connecting rod base (3-5), wherein the lower connecting rod base (3-5) is arranged near the edge of the cross frame; A lead screw connecting pin shaft nut assembly (3-8), wherein the lead screw connecting pin shaft nut assembly (3-8) is arranged at the lower part of the cross frame; A pair of rudder surface base motion ears (3-9), the pair of rudder surface base motion ears (3-9) are arranged on the other side of the base fixing plate (3-7) facing the fixing platform (1), and the pair of rudder surface base motion ears (3-9) are rotatably connected with a pair of ear piece hinge mounting ears (1-5).

7. The UAV rudder horizontal loading test adjustment device according to claim 6, characterized in that: The rudder surface motion component (4) comprises: Rudder (4-1); A plurality of control surface gooseneck assemblies (4-2), wherein the plurality of gooseneck assemblies (4-2) are arranged at one end of the control surface (4-1) and are rotatably connected to the plurality of gooseneck ear bases (3-1); An upper connecting rod connecting lug (4-5), wherein the upper connecting rod connecting lug (4-5) is arranged on the lower surface of the rudder surface (4-1); A driving assembly is connected to the upper connecting rod connecting lug (4-5) and is used for driving the rudder surface (4-1) to move.

8. The UAV rudder horizontal loading test adjustment device according to claim 7, characterized in that: The number of the rudder surface gooseneck components (4-2) and the number of the gooseneck ear bases (3-1) are both three.

9. The UAV rudder horizontal loading test adjustment device according to claim 7, characterized in that: The drive assembly comprises: A steering gear body (4-9), wherein a fixed end of the steering gear body (4-9) is rotatably connected to the steering gear hinge base (3-4); A connecting rod assembly connects the steering gear body (4-9) and the steering surface (4-1) and is used for converting the telescopic action of the steering gear body (4-9) into the rotational action of the steering surface (4-1).

10. The UAV control surface horizontal loading test adjustment device according to claim 9, characterized in that: The telescopic end of the steering gear body (4-9) is rotatably connected to a steering gear push rod (4-7), and the steering gear push rod (4-7) is vertically arranged to the steering gear body (4-9); The connecting rod assembly comprises: An upper connecting rod (4-6), one end of the upper connecting rod (4-6) being rotatably connected to the steering gear push rod (4-7), and the other end of the upper connecting rod (4-6) being rotatably connected to the upper connecting rod connecting lug (4-5); A lower connecting rod (4-8), one end of the lower connecting rod (4-8) is rotatably connected to the steering gear push rod (4-7), and the other end of the lower connecting rod (4-8) is rotatably connected to the lower connecting rod base (3-5).

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