Loading experiment and deflection detection tool for wings of unmanned aerial vehicle

Abstract

The utility model relates to the technical field of deflection detection, and discloses a loading experiment and deflection detection tool for wings of an unmanned aerial vehicle, which comprises a main body mechanism and an auxiliary mechanism positioned on the outer side of the main body mechanism. The main body mechanism comprises a deflection detection supporting column, a deflection detection mounting seat, a deflection detection base, a deflection detection supporting platform, a connecting block and a first wing connecting frame, and the deflection detection mounting seat is fixedly mounted at the lower end of the deflection detection supporting column. According to the loading experiment and deflection detection tool for the wings of the unmanned aerial vehicle, the first wing connecting frame and the second wing connecting frame are fixed through the first fixing bolts and the second fixing bolts, and the wing main body is fixed to the lower ends of the first wing connecting frame and the second wing connecting frame through the fixing belts; the device can be used for placing the sandbag with the loading force corresponding to the strength requirement, the load and the loading method are simplified, and the deflection requirements of the front beam and the rear beam of the wing can be bidirectionally measured at the same time.

Description

Technical Field

[0001] The utility model relates to the technical field of deflection detection, in particular to a loading experiment and deflection detection tool for a wing of a drone. Background Art

[0002] Aircraft structural strength test usually refers to structural static test, which is to load a certain level of static load on the aircraft surface, measure the deformation and strain state of the structure, and test the aircraft's load-bearing capacity under the design load, so as to provide protection for the aircraft's flight safety and structural safety. The wing is the main lifting surface of the aircraft and the most important load-bearing component of the entire aircraft. It is crucial to the structural safety of the aircraft. For small drones, due to their relatively large span-wise dimensions and relatively "slender" structures, and the wings are their main load-bearing components, the strength of the wings is the most prominent compared to other components such as the fuselage and tail.

[0003] At present, when people perform loading and deflection testing on UAV wings, the loading method is relatively cumbersome, and it is impossible to measure the deflection requirements of the front and rear rafters of the wing in both directions at the same time. Utility Model Content

[0004] The purpose of the utility model is to provide a loading test and deflection detection tool for UAV wings, so as to solve the problem that the loading method proposed in the above background technology is relatively cumbersome and the deflection requirements of the front and rear rafters of the wing cannot be measured simultaneously in both directions.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a loading test and deflection detection tooling for unmanned aerial vehicle wings, comprising a main mechanism and an auxiliary mechanism, wherein the auxiliary mechanism is located on the outside of the main mechanism, and the main mechanism comprises a deflection detection support column, a deflection detection mounting seat, a deflection detection base, a deflection detection support platform, a connecting block and a first wing connecting frame, wherein the deflection detection mounting seat is fixedly mounted on the lower end of the deflection detection support column, the deflection detection base is fixedly mounted on the lower end of the deflection detection mounting seat, the deflection detection support platform is fixedly mounted on the upper end of the deflection detection support column, the connecting block is fixedly mounted on the front end of the deflection detection support platform, and the first wing connecting frame is movably mounted on the front end of the connecting block.

[0006] Preferably, the main body structure also includes a first connecting groove, a first fixing bolt, a second wing connecting frame, a second connecting groove, a second fixing bolt, a wing connecting double rod, a wing connecting single rod, a wing body, a fixing belt, a first mounting groove, a first screw, a second mounting groove and a second screw, and the first connecting groove is fixedly arranged at the front end of the connecting block.

[0007] Preferably, the first fixing bolt is movably mounted at the front end of the first wing connecting frame, the second wing connecting frame is movably mounted at the front end of the deflection detection support platform, the second connecting groove is fixedly arranged at the front end of the deflection detection support platform, and the second fixing bolt is movably mounted at the front end of the second wing connecting frame.

[0008] Preferably, the wing connecting double rod is fixedly installed on the right end of the first wing connecting frame, the wing connecting single rod is fixedly installed on the right end of the first wing connecting frame, the wing body is movably installed on the lower end of the first wing connecting frame, the fixing belt is movably installed on the outside of the wing body, the first mounting groove is fixedly installed on the upper end of the deflection detection base, the first screw is movably installed on the upper end of the deflection detection base, the second mounting groove is fixedly installed on the upper end of the deflection detection mounting seat, and the second screw is movably installed on the upper end of the deflection detection mounting seat.

[0009] Preferably, the auxiliary mechanism includes a first auxiliary groove, a second auxiliary groove, a first limiting column, a third mounting groove, a second limiting column, a fourth mounting groove, a first fixed groove and a second fixed groove, and the first auxiliary groove is fixedly arranged at the upper end of the deflection detection support platform.

[0010] Preferably, the second auxiliary groove is fixedly arranged at the upper end of the deflection detection support platform, the first limit column is fixedly installed at the upper end of the deflection detection support platform, and the third installation groove is fixedly arranged inside the first limit column.

[0011] Preferably, the second limit column is fixedly installed at the upper end of the deflection detection support platform, the fourth mounting groove is fixedly set inside the second limit column, the first fixing groove is fixedly set at the front end of the connecting block, and the second fixing groove is fixedly set at the front end of the deflection detection support platform.

[0012] Compared with the prior art, the beneficial effects of the utility model are:

[0013] 1. The loading test and deflection detection tooling of the UAV wing is used to fix the first wing connecting frame and the second wing connecting frame by the first fixing bolt and the second fixing bolt, and the wing body is fixed to the lower end of the first wing connecting frame and the second wing connecting frame by the fixing belt, so that the device can be placed with sandbags with loading force corresponding to the strength requirements, simplifying the load and loading method, and can measure the deflection requirements of the front and rear rafters of the wing in both directions at the same time;

[0014] 2. The loading test and deflection detection tooling of the UAV wing, the first fixing groove is fixedly set at the front end of the connecting block, and the second fixing groove is fixedly set at the front end of the deflection detection support platform, so that the first fixing bolt can be rotated into the first fixing groove, and the second fixing bolt can be rotated into the second fixing groove, so that the first wing connecting frame and the second wing connecting frame are fixed more firmly. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the three-dimensional structure of the utility model;

[0016] Figure 2 This is a schematic diagram of the structure of the first limiting column of the utility model;

[0017] Figure 3 This is a schematic diagram of the structure of the first wing connecting frame of the utility model;

[0018] Figure 4 This is a schematic diagram of the second limiting column structure of the utility model.

[0019] In the figure: 1. main body; 101. deflection detection support column; 102. deflection detection mounting seat; 103. deflection detection base; 104. deflection detection support platform; 105. connecting block; 106. first wing connecting frame; 107. first connecting groove; 108. first fixing bolt; 109. second wing connecting frame; 110. second connecting groove; 111. second fixing bolt; 112. wing connecting double rod; 113. wing connecting single rod; 114. wing body; 115. fixing belt; 116. first mounting groove; 117. first screw; 118. second mounting groove; 119. second screw; 2. auxiliary mechanism; 201. first auxiliary groove; 202. second auxiliary groove; 203. first limiting column; 204. third mounting groove; 205. second limiting column; 206. fourth mounting groove; 207. first fixing groove; 208. second fixing groove. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0021] See also Figure 1 - Figure 4The utility model provides a technical solution: a loading test and deflection detection tooling for unmanned aerial vehicle wings, comprising a main mechanism 1 and an auxiliary mechanism 2, the auxiliary mechanism 2 is located on the outside of the main mechanism 1, the main mechanism 1 comprises a deflection detection support column 101, a deflection detection mounting seat 102, a deflection detection base 103, a deflection detection support platform 104, a connecting block 105 and a first wing connecting frame 106, the deflection detection mounting seat 102 is fixedly mounted on the lower end of the deflection detection support column 101, the deflection detection base 103 is fixedly mounted on the lower end of the deflection detection mounting seat 102, the deflection detection support platform 104 is fixedly mounted on the upper end of the deflection detection support column 101, the connecting block 105 is fixedly mounted on the front end of the deflection detection support platform 104, and the first wing connecting frame 106 is movably mounted on the front end of the connecting block 105.

[0022] The main body mechanism 1 also includes a first connecting groove 107, a first fixing bolt 108, a second wing connecting frame 109, a second connecting groove 110, a second fixing bolt 111, a wing connecting double rod 112, a wing connecting single rod 113, a wing body 114, a fixing belt 115, a first installation groove 116, a first screw 117, a second installation groove 118 and a second screw 119. The first connecting groove 107 is fixedly arranged at the front end of the connecting block 105, the first fixing bolt 108 is movably installed at the front end of the first wing connecting frame 106, the second wing connecting frame 109 is movably installed at the front end of the deflection detection support platform 104, the second connecting groove 110 is fixedly arranged at the front end of the deflection detection support platform 104, the second fixing bolt 111 is movably installed at the front end of the second wing connecting frame 109, the wing connecting double rod 112 is fixedly installed at the right end of the first wing connecting frame 106, the wing connecting single rod 113 is fixedly installed at the right end of the first wing connecting frame 106, and the wing body 114 is movably installed at the first At the lower end of a wing connecting frame 106, a fixing belt 115 is movably mounted on the outer side of a wing body 114, a first mounting groove 116 is fixedly mounted on the upper end of a deflection detection base 103, a first screw 117 is movably mounted on the upper end of the deflection detection base 103, a second mounting groove 118 is fixedly mounted on the upper end of a deflection detection mounting seat 102, and a second screw 119 is movably mounted on the upper end of a deflection detection mounting seat 102. When the loading test and deflection detection tooling of the UAV wing need to be used, by The first fixing bolt 108 and the second fixing bolt 111 fix the first wing connecting frame 106 and the second wing connecting frame 109, and the wing body 114 is fixed to the lower ends of the first wing connecting frame 106 and the second wing connecting frame 109 by the fixing belt 115, so that the device can be placed with sandbags of loading force corresponding to the strength requirements, simplifying the load and loading method, and can measure the deflection requirements of the front and rear rafters of the wing in both directions at the same time. The device is made of steel, is simple to manufacture, and has extremely low cost.

[0023] The auxiliary mechanism 2 includes a first auxiliary groove 201, a second auxiliary groove 202, a first limiting column 203, a third mounting groove 204, a second limiting column 205, a fourth mounting groove 206, a first fixed groove 207 and a second fixed groove 208. The first auxiliary groove 201 is fixedly arranged at the upper end of the deflection detection support platform 104, the second auxiliary groove 202 is fixedly arranged at the upper end of the deflection detection support platform 104, the first limiting column 203 is fixedly arranged at the upper end of the deflection detection support platform 104, the third mounting groove 204 is fixedly arranged inside the first limiting column 203, and the second limiting column 205 is fixedly arranged inside the deflection detection support platform 104. At the upper end, the fourth mounting groove 206 is fixedly arranged inside the second limiting column 205, the first fixing groove 207 is fixedly arranged at the front end of the connecting block 105, and the second fixing groove 208 is fixedly arranged at the front end of the deflection detection support platform 104. The first fixing groove 207 is fixedly arranged at the front end of the connecting block 105, and the second fixing groove 208 is fixedly arranged at the front end of the deflection detection support platform 104, so that the first fixing bolt 108 can be rotated into the first fixing groove 207, and the second fixing bolt 111 is rotated into the second fixing groove 208, so that the first wing connecting frame 106 and the second wing connecting frame 109 are fixed more firmly.

[0024] Working principle: When it is necessary to use the loading test and deflection detection tooling of the drone wing, the first wing connecting frame 106 and the second wing connecting frame 109 are fixed by the first fixing bolt 108 and the second fixing bolt 111, and the wing body 114 is fixed to the lower end of the first wing connecting frame 106 and the second wing connecting frame 109 by the fixing belt 115, so that the device can place sandbags with loading force corresponding to the strength requirements, simplify the load and loading method, and can measure the deflection requirements of the front and rear wing of the wing in both directions at the same time. The device is made of steel, simple to make, and extremely low in cost. The first fixing groove 207 is fixedly set at the front end of the connecting block 105, and the second fixing groove 208 is fixedly set at the front end of the deflection detection support platform 104, so that the first fixing bolt 108 can be rotated into the first fixing groove 207, and the second fixing bolt 111 is rotated into the second fixing groove 208, so that the first wing connecting frame 106 and the second wing connecting frame 109 are fixed more firmly.

[0025] Finally, it should be noted that the above content is only used to illustrate the technical solution of the utility model, rather than to limit the protection scope of the utility model. Simple modifications or equivalent substitutions of the technical solution of the utility model by ordinary technicians in this field do not deviate from the essence and scope of the technical solution of the utility model.

Claims

1. A loading test and deflection detection tool for a wing of an unmanned aerial vehicle, comprising a main mechanism (1) and an auxiliary mechanism (2), characterized in that: The auxiliary mechanism (2) is located outside the main mechanism (1); the main mechanism (1) comprises a deflection detection support column (101), a deflection detection mounting seat (102), a deflection detection base (103), a deflection detection support platform (104), a connecting block (105) and a first wing connecting frame (106); the deflection detection mounting seat (102) is fixedly mounted on the lower end of the deflection detection support column (101); the deflection detection base (103) is fixedly mounted on the lower end of the deflection detection mounting seat (102); the deflection detection support platform (104) is fixedly mounted on the upper end of the deflection detection support column (101); the connecting block (105) is fixedly mounted on the front end of the deflection detection support platform (104); and the first wing connecting frame (106) is movably mounted on the front end of the connecting block (105).

2. The loading test and deflection detection tool for the wing of an unmanned aerial vehicle according to claim 1, characterized in that: The main body structure (1) further comprises a first connecting groove (107), a first fixing bolt (108), a second wing connecting frame (109), a second connecting groove (110), a second fixing bolt (111), a wing connecting double rod (112), a wing connecting single rod (113), a wing body (114), a fixing belt (115), a first installation groove (116), a first screw (117), a second installation groove (118) and a second screw (119), wherein the first connecting groove (107) is fixedly arranged at the front end of the connecting block (105).

3. The loading test and deflection detection tool for the wing of an unmanned aerial vehicle according to claim 2, characterized in that: The first fixing bolt (108) is movably mounted on the front end of the first wing connecting frame (106), the second wing connecting frame (109) is movably mounted on the front end of the deflection detection support platform (104), the second connecting groove (110) is fixedly arranged on the front end of the deflection detection support platform (104), and the second fixing bolt (111) is movably mounted on the front end of the second wing connecting frame (109).

4. The loading test and deflection detection tool for the wing of an unmanned aerial vehicle according to claim 3, characterized in that: The wing connection double rod (112) is fixedly mounted on the right end of the first wing connection frame (106), the wing connection single rod (113) is fixedly mounted on the right end of the first wing connection frame (106), the wing body (114) is movably mounted on the lower end of the first wing connection frame (106), the fixing belt (115) is movably mounted on the outer side of the wing body (114), the first mounting groove (116) is fixedly mounted on the upper end of the deflection detection base (103), the first screw (117) is movably mounted on the upper end of the deflection detection base (103), the second mounting groove (118) is fixedly mounted on the upper end of the deflection detection mounting seat (102), and the second screw (119) is movably mounted on the upper end of the deflection detection mounting seat (102).

5. The loading test and deflection detection tool for the wing of an unmanned aerial vehicle according to claim 4, characterized in that: The auxiliary mechanism (2) comprises a first auxiliary groove (201), a second auxiliary groove (202), a first limiting column (203), a third installation groove (204), a second limiting column (205), a fourth installation groove (206), a first fixed groove (207) and a second fixed groove (208); the first auxiliary groove (201) is fixedly arranged at the upper end of the deflection detection support platform (104).

6. The loading test and deflection detection tool for the wing of an unmanned aerial vehicle according to claim 5, characterized in that: The second auxiliary groove (202) is fixedly arranged at the upper end of the deflection detection support platform (104), the first limit column (203) is fixedly arranged at the upper end of the deflection detection support platform (104), and the third installation groove (204) is fixedly arranged inside the first limit column (203).

7. The loading test and deflection detection tool for the wing of an unmanned aerial vehicle according to claim 6, characterized in that: The second limiting column (205) is fixedly mounted on the upper end of the deflection detection support platform (104), the fourth mounting groove (206) is fixedly arranged inside the second limiting column (205), the first fixing groove (207) is fixedly arranged at the front end of the connecting block (105), and the second fixing groove (208) is fixedly arranged at the front end of the deflection detection support platform (104).

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