Launching canister of folding wing unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a folding wing unmanned aerial vehicle launch canister which comprises a mounting seat, a launch canister body, a first guide part, a second guide part, a first connecting rod and a second connecting rod. The piston block is connected into the launching cylinder in a sliding mode, an inner cavity of the launching cylinder is divided into two sections by the piston block, a second guide piece is arranged on the piston block, and the first guide piece and the second guide piece are matched to enable the piston block to only slide in the axial direction of the launching cylinder; according to the folding-wing unmanned aerial vehicle, through cooperation of the launching cylinder and the piston block, rapid sliding of the piston block in the launching cylinder in the axial direction of the launching cylinder is achieved, then the initial flight speed is provided for the folding-wing unmanned aerial vehicle, and through cooperation of the first guiding piece and the second guiding piece, the piston block cannot rotate when sliding in the launching cylinder; and therefore, the unification of the launching attitude of the folding-wing unmanned aerial vehicle is ensured, and the explosion probability of the folding-wing unmanned aerial vehicle is reduced.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a folding-wing unmanned aerial vehicle launch tube. Background Art

[0002] The folding-wing unmanned aerial vehicle is an innovative design of unmanned aerial vehicle. Its main feature is that the wings can be folded. When the folding-wing unmanned aerial vehicle is in a non-flight state, the wings can be folded to reduce the occupied space and facilitate carrying and storage. Secondly, the folding-wing unmanned aerial vehicle also performs well in terms of adaptability. For example, in reconnaissance, rescue, etc., it may be necessary for the unmanned aerial vehicle to take off and land in a narrow or complex environment.

[0003] The folding-wing unmanned aerial vehicle is launched by a launch tube and a high-voltage starting generator to give the initial speed of the unmanned aerial vehicle to replace the take-off methods of the unmanned aerial vehicle's taxiing and hand-throwing. The prior art discloses a folding-wing unmanned aerial vehicle launching device, which includes: a base, the base is provided with a first cavity, a second cavity and a channel arranged inside the base, and the first cavity and the second cavity communicate with each other through the channel; a control valve, the control valve is installed in the first cavity, the control valve is provided with an air inlet and an air outlet, and the air inlet is positioned in the channel and communicates with the second cavity; a gas storage cylinder, one end of the gas storage cylinder is fixed to the base, and the cavity of the gas storage cylinder communicates with the second cavity; a launch tube, one end of the launch tube is fixed to the base, and the cavity of the launch tube communicates with the air outlet; and a support block, the support block is placed inside the cavity of the launch tube; wherein, when the control valve is powered off, the gas storage cylinder and the launch tube are closed, and when the control valve is powered on, the gas storage cylinder and the launch tube communicate with each other.

[0004] In view of the above related technologies, it is found during the launch process that the initial postures of the unmanned aerial vehicle after being launched are not unified, and sometimes the unmanned aerial vehicle explodes. After analyzing the problem, it is found that since both the support block and the barrel body of the launch tube are circular, there will be a rotation phenomenon during the loading and launch process, making the posture of the unmanned aerial vehicle after leaving the tube uncertain and causing difficulties in control. Utility Model Content

[0005] In order to achieve the unity of the launch posture of the folding-wing unmanned aerial vehicle and reduce the probability of explosion, the present application provides a folding-wing unmanned aerial vehicle launch tube.

[0006] The folding-wing unmanned aerial vehicle launch tube provided by the present application adopts the following technical solutions:

[0007] A folding-wing unmanned aerial vehicle launch tube, comprising:

[0008] Mounting seat:

[0009] A launch tube, the launch tube is connected to the mounting base, one end of the launch tube away from the mounting base is open, and a first guiding member is arranged inside the launch tube;

[0010] A piston block, the piston block is slidably connected inside the launch tube, the piston block divides the inner cavity of the launch tube into two intervals, and a second guiding member is arranged on the piston block. The first guiding member and the second guiding member cooperate to make the piston block slide only along the axial direction of the launch tube.

[0011] By adopting the above technical solutions, the designed folding-wing UAV launch tube can facilitate providing an installation basis for the launch tube through the mounting base. Through the cooperation of the launch tube and the piston block, the piston block can be made to slide rapidly along the axial direction of the launch tube inside the launch tube by an externally connected high-pressure starting generator, thereby providing an initial flight speed for the folding-wing UAV. Through the cooperation of the first guiding member and the second guiding member, the piston block will not rotate itself when sliding inside the launch tube, thereby ensuring the unity of the launch attitude of the folding-wing UAV, and further reducing the probability of the folding-wing UAV crashing.

[0012] In a specific feasible implementation, the first guiding member is set as at least one guiding strip connected to the inner wall of the launch tube, the guiding strip is arranged along the axial direction of the launch tube, and the second guiding member is set as at least one sliding groove opened on the piston block, and the guiding strip is slidably matched with the sliding groove.

[0013] By adopting the above technical solutions, the designed first guiding member is a guiding strip and the second guiding member is a sliding groove, and the guiding of the piston block during the rapid sliding process can be realized through the cooperation of the guiding strip and the sliding groove.

[0014] In a specific feasible implementation, the first guiding member is set as at least one guiding groove opened on the inner wall of the launch tube, the guiding groove is opened along the axial direction of the launch tube, and the second guiding member is set as at least one fixing block connected to the piston block, and the fixing block is slidably connected inside the guiding groove.

[0015] By adopting the above technical solutions, the designed first guiding member is a guiding groove and the second guiding member is a fixing block, and the guiding of the piston block during the rapid sliding process can be realized through the cooperation of the guiding groove and the fixing block.

[0016] In a specific feasible implementation, a support frame is connected to the mounting base, and the support frame is connected to the end of the launch tube away from the mounting base.

[0017] By adopting the above technical solution, the designed support frame can provide physical support for the launch port at the end of the launch tube far from the mounting base, avoiding the shaking of the launch tube caused by the rapid sliding of the piston block, thereby reducing the possibility of affecting the launch angle of the folding-wing UAV.

[0018] In a specific feasible implementation, the support frame includes:

[0019] A connecting collar, which is connected to the launch tube, and the launch tube is rotatably connected to the mounting base, and the rotation plane of the launch tube is vertically arranged;

[0020] A support vertical rod, one end of which is rotatably connected to the connecting collar, and the other end is rotatably connected to an adjusting block. The adjusting block is slidably connected to the mounting base, and a fixing member is connected to the adjusting block. The fixing member is connected to the mounting base for fixing the adjusting block.

[0021] By adopting the above technical solution, the designed support frame and fixing member can adjust the inclination angle of the launch tube while completing the support of the launch tube, and further adapt to the launch inclination angle adjustment of different launch scenarios.

[0022] In a specific feasible implementation, the vertical plane where the sliding track of the adjusting block is located is parallel to the rotation plane of the launch tube.

[0023] By adopting the above technical solution, the adjusting block with the vertical plane where the sliding track is located parallel to the rotation plane of the launch tube can reduce the required width of the mounting base while realizing the adjustment of the inclination angle of the launch tube, improving portability.

[0024] In a specific feasible implementation, the fixing member includes a fixing bolt, which is threadedly connected to the adjusting block, and the fixing bolt can pass through the adjusting block and abut against the mounting base.

[0025] By adopting the above technical solution, the designed fixing member can fix the position of the adjusting block through the fixing bolt.

[0026] In a specific feasible implementation, a T-shaped adjusting groove is opened on the mounting base, the adjusting block is slidably connected in the T-shaped adjusting groove, and a rubber strip is embedded in the bottom wall of the T-shaped adjusting groove. The fixing bolt can pass through the adjusting block and abut against the rubber strip.

[0027] By adopting the above technical solution, the designed rubber strip can further improve the position stability of the adjusting block on the basis of the fixing bolt being tightened.

[0028] In summary, the present application includes at least one of the following beneficial technical effects:

[0029] 1. The designed folding-wing UAV launch tube facilitates providing an installation foundation for the launch tube through the mounting seat. Through the cooperation of the launch tube and the piston block, the piston block can be quickly slid axially along the launch tube by an externally connected high-pressure start generator, thereby providing an initial flight speed for the folding-wing UAV. Through the cooperation of the first guiding member and the second guiding member, the piston block will not rotate itself when sliding in the launch tube, thereby ensuring the uniformity of the launch posture of the folding-wing UAV and reducing the probability of the folding-wing UAV crashing.

[0030] 2. The designed folding-wing UAV launch tube can provide physical support at the launch port at one end of the launch tube away from the mounting seat through the support frame, avoiding the possibility that the launch tube shakes during the rapid sliding of the piston block, thus affecting the launch angle of the folding-wing UAV.

[0031] 3. The designed folding-wing UAV launch tube can reduce the required width of the bottom mounting seat on the basis of realizing the inclination angle adjustment of the launch tube through the adjusting block whose vertical plane where the sliding track is located is parallel to the rotation plane of the launch tube, improving the portability. Description of the Drawings

[0032] Figure 1 is a schematic structural diagram of the folding-wing UAV launch tube according to an embodiment of the present application.

[0033] Figure 2 is Figure 1 an exploded view of, aiming to illustrate the first cooperation structure of the first guiding member and the second guiding member.

[0034] Figure 3 is Figure 1 an exploded view of, aiming to illustrate the second cooperation structure of the first guiding member and the second guiding member.

[0035] Figure 4 is Figure 1 a schematic structural diagram after adding the support frame and the fixing member.

[0036] Figure 5 is Figure 4 a cross-sectional view of.

[0037] Figure 6 is Figure 5 an enlarged view of part A in.

[0038] Description of the Reference Numerals: 1, mounting seat; 11, T-shaped adjustment groove; 2, launch tube; 3, first guiding member; 31, guiding strip; 32, guiding groove; 4, piston block; 5, second guiding member; 51, sliding groove; 52, fixing block; 6, support frame; 61, connecting collar; 62, support vertical rod; 63, adjusting block; 7, fixing member; 71, fixing bolt; 8, rubber strip. DETAILED DESCRIPTION

[0039] The following is combined with Figures 1-6 This application is described in further detail.

[0040] The embodiment of the present application discloses a folding-wing UAV launch tube.

[0041] Reference Figure 1 and Figure 2 A launch tube for a folding-wing UAV comprises a mounting seat 1, a launch tube 2 and a piston block 4, wherein the launch tube 2 is connected to the mounting seat 1, and an end of the launch tube 2 away from the mounting seat 1 is opened, the piston block 4 is slidably connected to the launch tube 2, and the piston block 4 can divide the inner cavity of the launch tube 2 into two sections, and a mounting frame for supporting a folding-wing UAV is bolted to the piston block 4, and the mounting frame is staggered with the inner wall of the launch tube 2; in order to make the piston block 4 slide along the axial direction of the launch tube 2, a high-pressure starting generator is also provided on the mounting seat 1, and the high-pressure gas output interface of the high-pressure starting generator is connected to the inner cavity of the launch tube 2.

[0042] Reference Figure 2 In order to avoid relative rotation between the piston rod and the launch tube 2 while the piston block 4 slides axially along the launch tube 2, thereby ensuring the uniformity of the launching posture of the folding-wing UAV and reducing the probability of the folding-wing UAV exploding, the folding-wing UAV launch tube also includes a first guide member 3 and a second guide member 5. The first guide member 3 is connected to the launch tube 2, and the second guide member 5 is connected to the piston block 4. The first guide member 3 and the second guide member 5 cooperate to make the piston block 4 slide only along the axial direction of the launch tube 2.

[0043] Reference Figure 2 In some embodiments of the present application, the first guide member 3 is configured as at least one guide bar 31 welded or bolted to the inner wall of the launch tube 2, and the guide bar 31 is arranged along the axial direction of the launch tube 2. The second guide member 5 is configured as at least one sliding groove 51 opened on the piston block 4, and the guide bar 31 is slidably matched with the sliding groove 51. In the present application, the number of guide bars 31 can be one, two, or three, as long as it can prevent the piston block 4 from rotating during the sliding process. In the present embodiment, the number of guide bars 31 is two.

[0044] Reference Figure 3, in some other embodiments of the present application, the first guiding member 3 is provided as at least one guiding groove 32 formed on the inner wall of the launching tube 2. The guiding groove 32 is formed along the axial direction of the launching tube 2. The second guiding member 5 is provided as at least one fixing block 52 integrally connected to the piston block 4. The fixing block 52 is slidably connected in the guiding groove 32. In the present application, the number of the fixing blocks 52 can be one, two, or three, as long as the rotation of the piston block 4 during sliding can be avoided. In this embodiment, the number of the fixing blocks 52 is two.

[0045] Referring to Figure 4 , in order to provide physical support at the launch port at the end of the launching tube 2 away from the mounting base 1, and to prevent the launching tube 2 from shaking during the rapid sliding of the piston block 4, which may affect the launch angle of the folding-wing UAV, a support frame 6 is connected to the mounting base 1, and the support frame 6 is connected to the end of the launching tube 2 away from the mounting base 1.

[0046] Referring to Figure 4 , in order to adjust the inclination angle of the launching tube 2 while supporting the launching tube 2, and further adapt to the launch inclination angle adjustment in different launch scenarios, it is further disclosed that the support frame 6 includes a connecting collar 61 and a support vertical rod 62. The connecting collar 61 is tightly clamped and connected to the launching tube 2 near the launch port, and the launching tube 2 is rotatably connected to the mounting base 1. The rotation plane of the launching tube 2 is vertically arranged; one end of the support vertical rod 62 is hinged to the connecting collar 61, and the other end is hinged with an adjusting block 63. The adjusting block 63 is slidably connected to the mounting base 1.

[0047] Referring to Figure 4 , in order to reduce the width of the mounting base 1 while realizing the sliding of the adjusting block 63 to improve portability, a T-shaped adjusting groove 11 is formed on the mounting base 1. The adjusting block 63 is slidably connected in the T-shaped adjusting groove 11, and the vertical plane where the sliding track of the adjusting block 63 is located is parallel to the rotation plane of the launching tube 2.

[0048] Referring to Figure 5 and Figure 6 , in order to fix the position of the adjusting block 63 after the adjusting block 63 slides in place, a fixing member 7 is connected to the adjusting block 63. The fixing member 7 is connected to the mounting base 1 for fixing the adjusting block 63; further, the fixing member 7 includes a fixing bolt 71. The fixing bolt 71 is threadedly connected to the adjusting block 63, and the fixing bolt 71 can pass through the adjusting block 63 and abut against the mounting base 1.

[0049] Referring to Figure 5 and Figure 6 , in order to ensure the position stability of the adjusting block 63 during fixation, a rubber strip 8 is embedded in the bottom wall of the T-shaped adjusting groove 11. The fixing bolt 71 can pass through the adjusting block 63 and abut tightly against the rubber strip 8 for fixation.

[0050] The implementation principle of a folding-wing UAV launcher tube in an embodiment of this application is as follows: The high-pressure start generator applies a force to the piston block 4, causing the piston block 4 to drive the mounting frame to move to the launch port. Then, the folding-wing UAV is mounted on the mounting frame. Next, the piston block 4 slides to the bottom wall of the launcher tube 2. By applying a force to the support vertical rod 62, the adjustment block 63 slides along the opening direction of the T-shaped adjustment groove 11. While the adjustment block 63 slides, the launcher tube 2 is driven to rotate through the support vertical rod 62 until the inclination angle of the launcher tube 2 is appropriate. Then, by turning the fixing bolt 71 until the fixing bolt 71 abuts against and fixes the rubber strip 8, the position of the adjustment block 63 is fixed. Finally, the high-pressure start generator inputs high-pressure gas into the launcher tube 2, causing the piston block 4 to slide rapidly along the axis of the launcher tube 2. While the piston block 4 slides, it drives the folding-wing UAV to move through the mounting frame, thereby providing an initial velocity for the folding-wing UAV.

[0051] The above are all preferred embodiments of this application, and the protection scope of this application is not limited thereby. Therefore, all equivalent changes made according to the structure, shape, and principle of this application should be covered within the protection scope of this application.

Claims

1. A folding-wing UAV launch tube, characterized in that: include: Mounting Base (1): A launching tube (2), the launching tube (2) being connected to the mounting seat (1), the launching tube (2) being arranged with an opening at one end away from the mounting seat (1), and a first guide member (3) being arranged inside the launching tube (2); A piston block (4) is slidably connected to the launch tube (2), the piston block (4) divides the inner cavity of the launch tube (2) into two sections, and a second guide member (5) is provided on the piston block (4), and the first guide member (3) and the second guide member (5) cooperate to enable the piston block (4) to slide only along the axial direction of the launch tube (2).

2. The folding-wing UAV launch tube according to claim 1, characterized in that: The first guide member (3) is configured as at least one guide strip (31) connected to the inner wall of the launch tube (2), the guide strip (31) being arranged along the axial direction of the launch tube (2), and the second guide member (5) is configured as at least one sliding groove (51) provided on the piston block (4), the guide strip (31) being slidably matched with the sliding groove (51).

3. The folding-wing UAV launch tube according to claim 1, characterized in that: The first guide member (3) is configured as at least one guide groove (32) opened on the inner wall of the launch tube (2), the guide groove (32) being opened along the axial direction of the launch tube (2), and the second guide member (5) is configured as at least one fixed block (52) connected to the piston block (4), the fixed block (52) being slidably connected in the guide groove (32).

4. The folding-wing UAV launch tube according to any one of claims 1 to 3, characterized in that: A support frame (6) is connected to the mounting seat (1), and the support frame (6) is connected to an end of the launching tube (2) away from the mounting seat (1).

5. The folding-wing UAV launch tube according to claim 4 is characterized in that: The support frame (6) comprises: A connecting collar (61), the connecting collar (61) being connected to the launching tube (2), and the launching tube (2) being rotatably connected to the mounting seat (1), and the rotating plane of the launching tube (2) being arranged vertically; A support rod (62), one end of the support rod (62) is rotatably connected to the connecting ring (61), and the other end is rotatably connected to an adjustment block (63), the adjustment block (63) is slidably connected to the mounting seat (1), and a fixing member (7) is connected to the adjustment block (63), and the fixing member (7) is connected to the mounting seat (1) and is used to fix the adjustment block (63).

6. The folding-wing UAV launch tube according to claim 5, characterized in that: The vertical plane where the sliding track of the adjustment block (63) is located is arranged parallel to the rotation plane of the launching tube (2).

7. The folding-wing UAV launch tube according to claim 5, characterized in that: The fixing member (7) comprises a fixing bolt (71), the fixing bolt (71) is threadedly connected to the adjusting block (63), and the fixing bolt (71) can pass through the adjusting block (63) and abut against the mounting seat (1).

8. The folding-wing UAV launch tube according to claim 7, characterized in that: The mounting seat (1) is provided with a T-shaped adjustment slot (11), the adjustment block (63) is slidably connected in the T-shaped adjustment slot (11), and a rubber strip (8) is embedded on the bottom wall of the T-shaped adjustment slot (11), and the fixing bolt (71) can pass through the adjustment block (63) and abut against the rubber strip (8).

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