A horizontal loading test adjusting device for unmanned aerial vehicle control surface

Abstract

The application provides a horizontal loading test adjusting device for a rudder surface of a UAV, and belongs to the technical field of UAV test.The device comprises a fixed rack, a rudder surface base and an adjusting assembly and a rudder surface movement assembly.The rudder surface base is hingedly connected to the fixed rack and can rotate up and down.The adjusting assembly is connected to the rudder surface base and can drive the rudder surface base to rotate.The rudder surface movement assembly is installed on the rudder surface base and is used for controlling the action of the rudder surface.The device can adjust the angle of the rudder surface base through the adjusting assembly, so that the rudder surface always maintains a horizontal state, which facilitates the loading test through gravity in the later stage, and can measure the stress of the rudder surface without wind tunnel test.In addition, different rudder surface movement assemblies can be replaced to adapt to different rudder surface gravity loading tests, and the device has good versatility.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) testing technology, and more specifically, relates to a UAV control surface horizontal loading test adjustment device. Background Technology

[0002] Before the control surfaces of a UAV are officially installed, static loading tests are required to test them, as well as the accessibility of their movement, to ensure that their performance meets the relevant technical requirements of the aircraft. Control surface testing is a key technical means of evaluating the success of control surface design and is an indispensable step in ensuring normal flight and maneuverability.

[0003] Currently, the structure of transmission control surface test equipment is relatively fixed, and the angles of the control surface and the test fixture cannot be adjusted simultaneously. It is impossible to use the same test equipment to simulate various working conditions of the control surface during flight. Summary of the Invention

[0004] The purpose of this invention is to provide a test adjustment device for horizontal loading of UAV control surfaces, which solves the problem that existing test devices and control surfaces cannot be adjusted at the same time.

[0005] To achieve the above objectives, the present invention provides a horizontal loading test adjustment device for unmanned aerial vehicle (UAV) control surfaces, comprising:

[0006] Fixed platform;

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

[0008] An adjustment assembly, which is connected to the rudder base and is capable of driving the rudder base to rotate;

[0009] A control surface motion assembly, which is mounted on the control surface base, is used to control the movement of the control surface.

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

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

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

[0013] Optionally, the fixed platform includes:

[0014] Fixture;

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

[0016] A lead screw support lug connecting base is fixedly connected to the fixed frame, and the lead screw support lug connecting base is provided with a pair of lead screw hinge mounting lugs.

[0017] Optionally, the adjustment component includes:

[0018] Lead screw;

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

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

[0021] A tapered roller bearing having a first rotating portion and a second rotating portion capable of rotating relative to each other, the first rotating portion being mounted on the bearing mounting block;

[0022] A pair of lead screw nut connecting lugs are provided on the second rotating part, and the pair of lead screw nut connecting lugs are hinged to a pair of lead screw hinge mounting lugs;

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

[0024] Optionally, the rudder base includes:

[0025] A base fixing bracket has 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 away from the fixing frame;

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

[0027] Multiple gooseneck ear plate bases are provided on the upper part of the side of the base fixing plate opposite to the fixing frame.

[0028] Servo hinge base, the servo hinge base is disposed on the side of the base fixing plate opposite to the fixing frame and is lower than the gooseneck lug base;

[0029] A lower connecting rod base is disposed near the edge of the crossbar;

[0030] A lead screw connecting pin and nut assembly is provided at the lower part of the cross frame;

[0031] A pair of rudder base moving lugs are provided on the other side of the base fixed plate facing the fixed platform, and the pair of rudder base moving lugs are rotatably connected to a pair of lug hinge mounting lugs.

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

[0033] Rudder surface;

[0034] Multiple rudder surface gooseneck assemblies, wherein the multiple gooseneck assemblies are disposed at one end of the rudder surface and rotatably connected to the multiple gooseneck ear plate bases;

[0035] The upper connecting rod is connected to the lug, which is located on the lower surface of the rudder surface;

[0036] A drive assembly, which is connected to the upper connecting rod connecting lug, is used to drive the movement of the control surface.

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

[0038] Optionally, the driving component includes:

[0039] A servo motor housing, wherein the fixed end of the servo motor housing is rotatably connected to the servo motor hinge base;

[0040] A linkage assembly connects the servo motor body and the control surface, and is used to convert the extension and retraction motion of the servo motor body into the rotational motion of the control surface.

[0041] Optionally, a servo push rod is rotatably connected to the telescopic end of the servo motor body, and the servo push rod is arranged perpendicular to the servo motor body;

[0042] The linkage assembly includes:

[0043] The upper connecting rod has one end rotatably connected to the servo push rod and the other end rotatably connected to the upper connecting rod connecting lug.

[0044] The lower connecting rod has one end rotatably connected to the servo push rod and the other end rotatably connected to the lower connecting rod base.

[0045] The beneficial effects of this invention are as follows: It provides an adjustment device for horizontal loading test of UAV control surfaces, comprising: a fixed platform, a control surface base, and an adjustment component and a control surface motion component. The control surface base is hinged to the fixed platform and can rotate up and down; the adjustment component is connected to the control surface base and can drive the control surface base to rotate; the control surface motion component is installed on the control surface base and is used to control the control surface movement. This device can adjust the angle of the control surface base through the adjustment component, thereby keeping the control surface in a horizontal state at all times, which facilitates subsequent loading tests under gravity and allows for force measurement of the control surface without wind tunnel testing. Furthermore, it can adapt to different control surface gravity loading tests by replacing different control surface motion components, exhibiting good versatility.

[0046] Other features and advantages of the present invention will be described in detail in the following detailed description section. Attached Figure Description

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

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

[0049] Figure 2 The second schematic structural diagram of a UAV control surface 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 platform according to an embodiment of the present invention is shown.

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

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

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

[0057] Explanation of reference numerals in the attached figures:

[0058] 1. Fixed frame; 1-1. Fixed bracket; 1-2. Ear hinge mounting base plate; 1-3. Adjustment assembly; 1-3-1. Lead screw nut connecting lug; 1-3-2. Bearing mounting block; 1-3-3. Lead screw nut; 1-3-5. Spherical plain bearing; 1-3-6. Tapered roller bearing; 1-4. Lead screw lug connecting base; 1-5. Ear hinge mounting lug; 1-6. Lead screw hinge mounting lug;

[0059] 2. Reaction wall;

[0060] 3. Rudder surface base; 3-1. Gooseneck lug base; 3-4. Servo motor connection base; 3-5. Lower connecting rod base; 3-6. Base fixing bracket; 3-7. Base fixing plate; 3-8. Lead screw connecting pin and nut assembly; 3-9. Rudder surface base moving lug;

[0061] 4. Control surface motion assembly; 4-1. Control surface; 4-4. Control surface gooseneck assembly; 4-5. Upper linkage connecting lug; 4-6. Upper linkage; 4-7. Servo push rod; 4-8. Lower linkage; 4-9. Servo body. Detailed Implementation

[0062] Preferred embodiments of the invention will now be described in more detail. While preferred embodiments of the invention are described below, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that the invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0063] like Figure 1 and 2 As shown, the present invention provides a horizontal loading test adjustment device for unmanned aerial vehicle control surfaces, characterized in that it includes:

[0064] Fixed frame 1;

[0065] The rudder base 3 is hinged to the fixed frame 1 and can rotate up and down.

[0066] An adjustment component is connected to the rudder base 3 and can drive the rudder base 3 to rotate.

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

[0068] Specifically, the opening and closing motion of the control surface 4-1 causes an angle change. This UAV control surface horizontal loading test adjustment device can adjust the angle of the control surface base 3 through the adjustment components, thereby keeping the control surface 4-1 in a horizontal state at all times. This facilitates subsequent loading tests under gravity and allows for force measurement of the control surface 4-1 without wind tunnel testing. Furthermore, different control surface motion components 4 can be replaced to adapt to different control surface gravity loading tests, demonstrating good versatility.

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

[0070] The reaction wall 2 and the fixed platform 1 are 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 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 platform 1 includes:

[0074] Fixture 1-1;

[0075] Ear hinge mounting base plate 1-2, ear hinge mounting base plate 1-2 is set on fixed frame 1-1, and ear hinge mounting base plate 1-2 is provided with a pair of ear hinge mounting ears 1-5;

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

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

[0078] Lead screw 1-3-4;

[0079] Lead screw nut 1-3-3, lead screw nut 1-3-3 is threaded to one end of lead screw 1-3-4;

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

[0081] The tapered roller bearing 1-3-6 has a first rotating part and a second rotating part that can rotate relative to each other. The first rotating part is mounted on the bearing mounting block 1-3-2.

[0082] A pair of lead screw nut connecting lugs 1-3-1 are provided on the second rotating part, and the pair of lead screw nut connecting lugs 1-3-1 are hinged to a pair of lead screw hinge mounting lugs 1-6.

[0083] Spherical bearing 1-3-5 is located at the other end of lead screw 1-3-4 and is rotatably connected to rudder base 3.

[0084] In this embodiment, the fixing frame 1-1 is bolted to the reaction wall 2, the lug hinge mounting bracket 1-5 is fixed to the lug hinge mounting base plate 1-2 to form an integral whole, the lug hinge mounting base plate 1-2 and the screw rod bracket connecting base 1-4 are fixed to the fixing frame 1-1, and the adjusting component 1-3 is hinged to the screw rod nut connecting bracket 1-3-1 and the screw rod bracket connecting base 1-4 to form a rotating pair. The adjusting component 1-3 contains a screw pair, and the relative length between the screw rod 1-3-4 and the screw rod 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 has a vertically arranged vertical frame and a horizontally arranged horizontal frame. The horizontal frame is fixedly connected to the middle of the vertical frame and extends away from the fixing platform 1.

[0087] The base fixing plate 3-7 is vertically installed on the upper part of the vertical frame;

[0088] Multiple gooseneck ear plate bases 3-1 are disposed on the upper part of the side of the base fixing plate 3-7 facing away from the fixing frame 1.

[0089] Servo hinge base 3-4 is located on the side of the base fixing plate 3-7 that is opposite to the fixing frame 1 and is lower than the gooseneck lug base 3-1.

[0090] Lower connecting rod base 3-5 is located near the edge of the crossbar;

[0091] The lead screw connecting pin and nut assembly 3-8 is located at the lower part of the cross frame;

[0092] A pair of rudder base moving lugs 3-9 are provided on the other side of the base fixed plate 3-7 facing the fixed platform 1, and the pair of rudder base moving lugs 3-9 are rotatably connected to a pair of lug hinge mounting lugs 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 base moving lug 3-9 is located on the back of the base fixing plate 3-7 and forms a rotating pair with the lug hinge mounting lug 1-5 in the fixed frame 1 through hinge, so that the rudder base 3 can rotate relative to the fixed frame 1. The gooseneck lug base 3-1 and the rudder hinge base 3-4 are bolted and fixed on the base fixing plate 3-7. The lower connecting rod base 3-5 is bolted and fixed on the base fixing bracket 3-6 to form a hinge interface with the rudder moving component 4. The screw connecting pin nut assembly 3-8 is located at the bottom of the base fixing bracket 3-6 and cooperates with the spherical bearing 1-3-5 in the adjusting assembly 1-3 to form a rotating pair so as to adjust the angle between the rudder base 3 and the fixed frame 1.

[0094] like Figure 9 As shown, optionally, the control surface motion assembly 4 includes:

[0095] Rudder surface 4-1;

[0096] Multiple rudder surface gooseneck assemblies 4-2 are disposed at one end of the rudder surface 4-1 and rotatably connected to multiple gooseneck lug bases 3-1;

[0097] The upper connecting rod is connected to the lug 4-5, which is located on the lower surface of the rudder surface 4-1.

[0098] The drive assembly is connected to the upper connecting rod connecting lug 4-5 and is used to drive the movement of the control surface 4-1.

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

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

[0101] Optionally, the driving component includes:

[0102] Servo body 4-9, the fixed end of servo body 4-9 is rotatably connected to servo hinge base 3-4;

[0103] The linkage assembly connects the servo body 4-9 and the control surface 4-1, and is used to convert the extension and retraction of the servo body 4-9 into the rotation of the control surface 4-1.

[0104] Specifically, the linkage assembly can be configured in various forms according to experimental requirements to verify the reachability of motion of various different linkage assemblies.

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

[0106] The linkage assembly includes:

[0107] Upper link 4-6, one end of upper link 4-6 is rotatably connected to servo push rod 4-7, and the other end of upper link 4-6 is rotatably connected to upper link connecting lug 4-5;

[0108] The lower link 4-8 ​​is rotatably connected at one end to the servo push rod 4-7, and at the other end to the lower link base 3-5.

[0109] In this embodiment, the gooseneck assembly 4-2 of the rudder surface is installed at a certain distance from the relatively rotating end of the rudder surface 4-1, forming a rotating pair corresponding to the position of the gooseneck lug base 3-1 in the rudder surface base 3. The rear lug of the servo motor body 4-9 corresponds to the position of the servo motor connecting base 3-4 in the rudder surface base 3, forming a rotating pair. The upper connecting rod connecting lug 4-5 is fixed to the lower surface of the rudder surface 4-1 and forms a rotating pair with the other end of the upper connecting rod 4-6 through a hinge. The other end of the lower connecting rod 4-8 is connected to the lower connecting rod base. The seat 3-5 forms a rotating joint through a hinge. One end of the lower connecting rod 4-8 is connected to one end of the upper connecting rod 4-6 and the servo push rod 4-7 through a pin to form a three-joint rotating joint. The servo body 4-9 and the servo push rod 4-7 form a sliding joint to become a power source device. The upper connecting rod connecting lug 4-5, the upper connecting rod 4-6, the lower connecting rod 4-8, the servo push rod 4-7, and the servo body 4-9 constitute a connecting rod assembly, thereby realizing the relative rotation of the control surface 4-1 relative to the gooseneck assembly and realizing the opening and closing action of the control surface 4-1.

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

[0111] First, the control surface motion assembly 4 drives the control surface 4-1 to the required attitude angle and keeps it fixed through the servo motor body 4-9 and the linkage assembly. During this operation, the control surface 4-1 will rotate around the rotation axis formed by the gooseneck lug base 3-1 as the servo motor assembly works, that is, the control surface 4-1 rotates relative to the control surface base 3.

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

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

[0114] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A horizontal loading test adjustment device for unmanned aerial vehicle (UAV) control surfaces, characterized in that, include: Fixed frame (1); The rudder base (3) is hinged to the fixed frame (1) and can rotate up and down; Adjustment component (1-3), the adjustment component (1-3) is connected to the rudder base (3) and can drive the rudder base (3) to rotate; A control surface motion assembly (4) is mounted on the control surface base (3) and is used to control the movement of the control surface (4-1); The fixed platform (1) includes: Fixture (1-1); Ear hinge mounting base plate (1-2), the ear hinge mounting base plate (1-2) is provided on the fixed frame (1-1), and the ear hinge mounting base plate (1-2) is provided with a pair of ear hinge mounting ears (1-5); A lead screw support ear connecting base (1-4) is fixedly connected to the fixed frame (1-1), and the lead screw support ear connecting base (1-4) is provided with a pair of lead screw hinge mounting ears (1-6). The adjustment components (1-3) include: Lead screw (1-3-4); A lead screw nut (1-3-3) is threaded onto one end of the lead screw (1-3-4); A bearing mounting block (1-3-2) is 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) has a first rotating part and a second rotating part that can rotate relative to each other, and the first rotating part is mounted on the bearing mounting block (1-3-2). A pair of lead screw nut connecting lugs (1-3-1) are provided on the second rotating part, and the pair of lead screw nut connecting lugs (1-3-1) are hinged to a pair of lead screw hinge mounting lugs (1-6). A spherical bearing (1-3-5) is provided at the other end of the lead screw (1-3-4) and is rotatably connected to the rudder base (3). The rudder base (3) includes: The base fixing bracket (3-6) has a vertically arranged vertical frame and a horizontally arranged horizontal frame. The horizontal frame is fixedly connected to the middle of the vertical frame and extends away from the fixing frame (1). A base fixing plate (3-7) is vertically installed on the upper part of the vertical frame; Multiple gooseneck ear plate bases (3-1) are provided on the upper part of the side of the base fixing plate (3-7) facing away from the fixing frame (1). Servo hinge base (3-4), the servo hinge base (3-4) is disposed on the side of the base fixing plate (3-7) opposite to the fixing frame (1) and lower than the gooseneck ear plate base (3-1). The lower connecting rod base (3-5) is disposed near the edge of the crossbar; A lead screw connecting pin and nut assembly (3-8) is provided at the lower part of the cross frame; A pair of rudder base moving lugs (3-9) are provided on the other side of the base fixed plate (3-7) facing the fixed frame (1), and the pair of rudder base moving lugs (3-9) are rotatably connected to a pair of lug hinge mounting lugs (1-5). The control surface motion component (4) includes: Control surfaces (4-1); Multiple rudder surface gooseneck assemblies (4-2), the multiple gooseneck assemblies (4-2) are disposed at one end of the rudder surface (4-1) and rotatably connected to the multiple gooseneck ear plate bases (3-1); The upper connecting rod connecting lug (4-5) is located on the lower surface of the rudder surface (4-1); A drive assembly is connected to the upper connecting rod connecting lug (4-5) for driving the rudder surface (4-1) to move; The driving component includes: Servo motor body (4-9), the fixed end of which is rotatably connected to the servo motor hinge base (3-4). A linkage assembly, which connects the servo motor body (4-9) and the control surface (4-1), is used to convert the extension and retraction of the servo motor body (4-9) into the rotation of the control surface (4-1). The telescopic end of the servo motor body (4-9) is rotatably connected to a servo motor push rod (4-7), and the servo motor push rod (4-7) is set perpendicular to the servo motor body (4-9). The linkage assembly includes: Upper connecting rod (4-6), one end of which is rotatably connected to the servo push rod (4-7), and the other end of which is rotatably connected to the upper connecting rod connecting lug (4-5). The lower connecting rod (4-8) has one end rotatably connected to the servo push rod (4-7) and the other end rotatably connected to the lower connecting rod base (3-5).

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

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

4. The UAV control surface horizontal loading test adjustment device according to claim 1, characterized in that, The number of the rudder surface gooseneck assembly (4-2) and the gooseneck ear plate base (3-1) are both three.

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