Launching device of folding wing unmanned aerial vehicle

Abstract

The utility model provides a folding wing unmanned aerial vehicle launching device, which belongs to unmanned aerial vehicle launching devices and comprises a launching cylinder, one end of the launching cylinder is connected with an air chamber, and a piston is slidably mounted in the air chamber; the end, away from the launching cylinder, of the air chamber is connected with a mounting base, and a gas generator is mounted on the upper surface of the mounting base and located in a space defined by the air chamber, the piston and the mounting base. An air chamber is designed, and a piston is installed in the air chamber in a sliding mode. The end, away from the launching cylinder, of the air chamber is connected with a mounting base, a gas generator is mounted on the upper surface of the mounting base and located in a space defined by the air chamber, the piston and the mounting base, and the gas generator is powered on to instantly expand to emit gas so as to push the piston and the unmanned aerial vehicle mounted on the piston to launch. Therefore, launching of the unmanned aerial vehicle is achieved, the size of the launching device is reduced, and the launching efficiency is improved.

Description

Technical Field

[0001] This utility model relates to drone launching devices, and more particularly to a folding-wing drone launching device. Background Technology

[0002] Currently, common folding-wing drone launch devices, based on their energy source, can be categorized into compressed gas, electromagnetic catapult, gunpowder explosion, and mechanical energy storage types. These systems suffer from drawbacks such as large size, heavy weight, complex construction, and cumbersome operation.

[0003] Currently, common folding-wing drone launch devices can be categorized based on their energy source, including compressed gas, electromagnetic catapult, gunpowder explosion, and mechanical energy storage. Compressed gas launchers suffer from drawbacks such as large size, heavy weight, long charging time, and the need for external charging equipment. Electromagnetic catapult launchers are characterized by high technical barriers, complex construction, and the need for external high-power power supply equipment. Gunpowder explosion launchers are subject to control, pose high risks, and are difficult to obtain. Mechanical energy storage launchers are characterized by large size, heavy weight, and complex operation.

[0004] To address the aforementioned shortcomings, this invention provides a lightweight, simple, and portable folding-wing drone launcher that can be carried, transferred, deployed, and launched by a single person. Utility Model Content

[0005] To address the aforementioned problems, this utility model proposes a folding-wing UAV launch device, comprising a launch tube, an air chamber connected to one end of the launch tube, a piston slidably mounted in the air chamber, and a mounting base connected to the end of the air chamber away from the launch tube. A gas generator is mounted on the upper surface of the mounting base, and the gas generator is located in the space enclosed by the air chamber, the piston, and the mounting base.

[0006] Preferably, the end of the mounting base away from the gas generator is connected to a handle, and the gas chamber is detachably connected to the mounting base.

[0007] Preferably, the folding-wing UAV launcher further includes a support plate, and several of the support plates are sequentially installed at the connection between the inner surface of the launch tube and the inner surface of the air chamber.

[0008] Preferably, the piston includes a piston housing, and a groove is provided at the end of the piston housing away from the gas generator.

[0009] Preferably, a hook is provided at one end of the piston housing near the gas generator, and the hook is connected to the parachute.

[0010] Preferably, the folding-wing drone launcher further includes a support base and a support frame. The support base is installed at the corner of the air chamber near the handle, and the support frame is installed on the outer surface of the launch tube away from the handle.

[0011] Preferably, the support frame comprises a rotating shaft, a shaft sleeve and a support leg, the shaft sleeve is connected with the outer surface of the launching cylinder, the rotating shaft is rotatably installed in the shaft sleeve; the support leg is fixedly connected with the rotating shaft.

[0012] Preferably, the support frame further comprises a hoop, the hoop is sleeved on the outer surface of the launching cylinder, and the shaft sleeve is installed on the outer surface of the hoop.

[0013] Preferably, the support frame further comprises a fixing table, one end of the fixing table is fixedly installed on the end face of the rotating shaft, and the other end is fixedly connected with the support leg.

[0014] Preferably, the folding wing unmanned aerial vehicle launching device further comprises a control system, the control system comprises a battery, a manual switch, a remote control switch and a gas generator which are connected in sequence.

[0015] Beneficial effects:

[0016] 1. The utility model discloses a gas chamber is designed, and the piston is slidably installed in the gas chamber, and one end of the gas chamber is connected with the mounting base away from the launching cylinder, and the gas generator is installed on the upper surface of the mounting base, and the gas generator is located in the space surrounded by the gas chamber, the piston and the mounting base, and the gas generated by the gas generator expands in the instant of electrification and realizes the pushing of the piston and the unmanned aerial vehicle mounted on the piston, and the launching of the unmanned aerial vehicle is realized, the volume of the launching device is reduced, and the launching efficiency is improved.

[0017] 2. The utility model discloses a support base and support frame are set up, the support base is installed in the corner of the gas chamber near the handle side, and the support frame is installed on the outer surface of the launching cylinder away from the handle, and the different angles of the launching cylinder are supported, and the remote launching is supported.

[0018] 3. The utility model discloses a control system, the control system comprises a battery, a manual switch, a remote control switch and a gas generator which are connected in sequence, and the remote control switch is used to realize the remote control launching, reduces the probability of the injury of the operator, and improves the safety.

[0019] Other features and advantages of the present application will be set forth in the following description of the application, and in part will become apparent to those skilled in the art upon examination of the following specification or can be learned by practice of the application. The objects and other advantages of the present application can be realized and attained by the structure particularly pointed out in the description and the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical scheme in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0021] Figure 1 A front view of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0022] Figure 2 A three-dimensional structure diagram of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0023] Figure 3 An installation schematic diagram of the launching barrel, the air chamber and the handle of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0024] Figure 4 An explosion schematic diagram of the launching barrel and the air chamber of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0025] Figure 5 An explosion top view of the launching barrel and the air chamber of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0026] Figure 6 A three-dimensional view of the piston of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0027] Figure 7 Another angle of the three-dimensional view of the piston of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0028] Figure 8 An installation schematic diagram of the gas generator, the mounting base and the handle of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0029] Figure 9 An A partial enlarged schematic diagram of Figure 2 is shown.

[0030] Figure 10 A B partial enlarged schematic diagram of Figure 2 is shown.

[0031] Figure 11 A circuit diagram of the control system of the folding wing unmanned aerial vehicle launching device in the embodiment of the present application is shown.

[0032] In the drawings, 1, launching barrel; 2, support plate; 3, air chamber; 4, gas generator; 5, mounting base; 6, handle; 8, support base;

[0033] 7, piston; 71, piston housing; 72, clamping groove; 73, hook; 74, recess;

[0034] 9, support frame; 91, hoop; 92, rotating shaft; 93, shaft sleeve; 94, leg; 95, fixed table. DETAILED DESCRIPTION

[0035] To make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely explained in combination with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0036] Reference Figure 1 A folding wing unmanned aerial vehicle launching device, comprising a launching barrel 1, one end of the launching barrel 1 is connected with a gas chamber 3, a piston 7 is slidably installed in the gas chamber 3 (reference Figure 5 ); the gas chamber 3 is connected with a mounting base 5 away from one end of the launching barrel 1, a gas generator 4 is installed on the upper surface of the mounting base 5, and the gas generator 4 is located in the space surrounded by the gas chamber 3, the piston 7 and the mounting base 5.

[0037] Specifically, the launching barrel 1 uses a composite material rectangular tube as the main part of the launching barrel 1 to provide launching stroke support for the folding wing unmanned aerial vehicle to reach the take-off speed. The size of the composite material rectangular tube meets the requirements of loading the aircraft and the piston 7.

[0038] In the above embodiment, alternatively, another embodiment is that the launching barrel 1 can also select a common glass steel square tube, which only needs to be cut to the required length in the factory, without the need for mold opening, meeting the economic requirements.

[0039] Reference Figure 3 The mounting base 5 is connected with a handle 6 away from one end of the gas generator 4, and the gas chamber 3 and the mounting base 5 are detachably connected. Specifically, the gas chamber 3 and the mounting base 5 are connected by threads; or the gas chamber 3 and the mounting base 5 are connected by buckles.

[0040] The gas chamber 3 serves as a container for the gas to be filled rapidly after the gas generator 4 is excited, and needs to cooperate with the piston 7 to ensure that there is no gas leakage around and at the bottom, so that the rapidly filled gas pushes the piston 7 to move forward along the launching barrel 1. In order to ensure the cooperation of the piston 7, the launching barrel 1 and the gas chamber 3, the gas chamber 3 adopts a stepped design, and the inner side of the four around the gas chamber 3 is designed with a rib plate to provide support for the piston 7 in the launching barrel 1.

[0041] In the structure design of the gas chamber 3, in order to facilitate the replacement of the gas generator 4 and the adjustment of the volume of the cavity of the gas chamber 3 in the test stage, an inner threaded dismounting interface is designed, which realizes the requirements of quick dismounting, volume adjustment and air tightness through the threaded cooperation between the interface and the mounting base 5. Figure 8

[0042] The mounting base 5 is a support structure of the gas generator 4, which not only bears the connection and fixation with the gas generator 4 in this design, but also has the function of quick dismounting and replacement. Therefore, an outer metric thread is designed in the design of the mounting base 5, which cooperates with the inner thread of the gas chamber 3 to realize the purpose of quick dismounting and mounting.

[0043] Specifically, the gas generator 4 mainly consists of an igniter, sodium azide, a filter and a shell. The device borrows the principle of the automobile safety airbag and selects the gas generator as the energy source. The gas generating agent belongs to the non-explosive agent of the instantaneous type and is not a pyrotechnic product, which can be easily obtained on the market and meets the design requirements in storage, transportation and carrying.

[0044] Referring to Figure 4 , the folding wing unmanned aerial vehicle launching device further comprises a support plate 2, and a plurality of support plates 2 are sequentially installed at the connection between the inner surface of the launching barrel 1 and the inner surface of the gas chamber 3.

[0045] Specifically, due to the requirement of the depth of the gas chamber 3 and the need to bore a large size thread, if the whole aluminum rod is processed, there are problems of high processing difficulty, high processing and material costs. From the perspective of manufacturability and economy, the inner support part of the launching barrel 1 is replaced by the splicing mode of the support plate 2, which is sequentially installed at the connection between the inner surface of the launching barrel 1 and the inner surface of the gas chamber 3; the gas chamber 3 only needs to process an inner cavity with a depth of 50 mm, which can be processed without long-stroke equipment, and the overall manufacturing cost will be greatly reduced. In addition, if the volume of the gas chamber 3 needs to be adjusted greatly in the verification process, different sizes of support plates 2 can be replaced to meet the requirements of low-cost and quick adjustment.

[0046] Referring to Figure 6 and Figure 7 , the piston 7 comprises a piston shell 71, and a clamping groove 72 is arranged at the end of the piston shell 71 away from the gas generator 4. Specifically, the structure of the piston 7 is as shown in Figure 6 , in which the clamping groove 72 of the piston structure supports the force receiving part of the unmanned aerial vehicle and prevents the friction between the unmanned aerial vehicle and the wall of the launching barrel 1. The piston 7 is loaded from the mouth of the launching barrel 1, and through tolerance design, the cooperation between the piston 7 and the inner wall of the launching barrel 1 is moderate, so that the piston 7 can be easily slid into the launching barrel 1 and the air tightness of the piston 7 in the launching process can be ensured.

[0047] ​Further, the piston shell 71 is provided with a hook 73 near one end of the gas generator 4, and the hook 73 is connected with the parachute.

[0048] Specifically, the piston 7 is designed as a long cuboid heterogeneous member, the cross-sectional shape of which is square, the height is 100 mm, the clamping groove 72 avoids interference with the hub, the recess 74 is recessed by 10 mm, and the recesses 74 on both sides are designed for weight reduction to ensure overall strength. A through hole is reserved in the center of the piston 7 for assembling the hook 73, and the hook 73 is an M4 stainless steel ring bolt and a ring nut. The piston 7 is configured with a parachute, and the parachute is tied to the hook 73. During launching, the unmanned aerial vehicle is launched at the same time under the push of the piston 7. During the flight in the air, the parachute is unfolded, the wind resistance becomes large, and the piston 7 is pulled to slow down, and the unmanned aerial vehicle separates from the piston 7.

[0049] Reference Figure 2 , the folding wing unmanned aerial vehicle launching device further comprises a support base 8 (refer to Figure 10 ) and a support frame 9, the support base 8 is installed at the corner near the handle 6 on the side of the gas chamber 3, and the support frame 9 is installed on the outer surface of the launching barrel 1 away from the handle 6.

[0050] Specifically, the support base 8 serves as the tail support of the launching barrel 1 and bears the launching recoil force during the launching process, and is an important component for ensuring the stability of the launching barrel 1 during the whole launching process. Considering that the support base 8 is the main force receiving component and is in contact with various types of ground for a long time, a 2.5 mm thick 316 stainless steel plate is selected as the material, which has good tensile and yield strength. A bending reinforcing rib design is adopted to increase the Z-direction support force, and a hole is designed at the bottom to realize ground fixation in combination with ground nails during actual use. The side of the support base 8 is designed with four-stage height adjustment, the adjustment range is 24 mm, the adjustment resolution is 8 mm, which facilitates angle adjustment during actual use, and the barrel body is adjusted and fixed by hand screw bolts. The design of the support base 8 is shown in Figure 10 .

[0051] Reference Figure 9 , the support frame 9 comprises a rotating shaft 92, a shaft sleeve 93 and a supporting leg 94, the shaft sleeve 93 is connected with the outer surface of the launching barrel 1, and the rotating shaft 92 is rotatably installed in the shaft sleeve 93; the supporting leg 94 is fixedly connected with the rotating shaft 92.

[0052] Further, the support frame 9 further comprises a clamp 91, the clamp 91 is sleeved on the outer surface of the launching barrel 1, and the shaft sleeve 93 is installed on the outer surface of the clamp 91.

[0053] Specifically, the support frame 9 at the front end of the launching barrel 1 bears the functions of angle adjustment and stability of the launching barrel 1. Considering that the barrel body of the launching barrel 1 is a non-customized component and the connection is within the launching stroke range, the clamp 91 is used as an intermediate connecting component to connect and fix the support frame 9 and the launching barrel 1.

[0054] The hoop 91 is processed by bending 316 stainless steel, the material is easy to obtain, and the processing cost is low. The bottom hole of the hoop 91 and the mounting surface of the shaft sleeve 93 are connected by a flat head screw.

[0055] In actual use scenarios, there are two modes of folding and unfolding. In order to ensure stable support and rapid unfolding and folding in the unfolded mode, and considering the comprehensive economy and ease of use, the structure shown in the figure is adopted. Figure 2

[0056] The rotating shaft 92 and the shaft sleeve 93 adopt interference fit. A circular boss is designed on the rotating shaft, which can be formed by a positioning pin or direct cutting. The shaft sleeve 93 is designed and processed with an L-shaped notch. Through the cooperation of the boss and the notch, the rotating shaft can freely move within the fixed range of 0°-90°. When it is 90°, it is the support position, and when it is 0°, it is the folding position.

[0057] The supporting leg 94 and the rotating shaft 92 adopt hard connection. The fixed table 95 part is designed and processed as an intermediate part to connect the supporting leg 94 and the rotating shaft 92. The rotating shaft 92 is designed in a square shape at both ends to facilitate angle fixation during installation. The fixed table 95 and the rotating shaft 92 are connected and fastened by bolts through the threaded holes on both sides. The supporting leg 94 is directly connected with the fixed table 95 through the external threads on the supporting leg 94 and the screw holes on the fixed table 95.

[0058] The supporting leg 94 is directly purchased from the market. A single carbon fiber tripod can bear a weight of 10 kg and has a telescopic locking function, which can quickly and conveniently adjust the height and adapt to uneven ground.

[0059] Referring to Figure 11 , the folding wing unmanned aerial vehicle launching device further includes a control system, and the control system includes a battery, a manual switch, a remote control switch and a gas generator 4 connected in sequence.

[0060] Specifically, the core working principle of the system is as follows: after the battery is turned on, when the first manual switch is pressed, the system starts. The first remote controller is used to control the on-off state of the first remote control module. When the first remote controller is pressed, the circuit controlled by the first remote control module will be turned on, causing the red indicator light to turn on, indicating that the circuit has been connected. In this state, if the second remote controller is continuously pressed, the second remote control module will be activated, causing the green indicator light to turn on, at which time the power supply will be output to the downstream circuit, completing the excitation of the gas generator 4. In addition, the system design contains a first manual switch to ensure the on-off control of the entire circuit, which exists as a master switch; when the first remote control module and / or the second remote control module is damaged, the excitation function is completed through the second manual switch. The system function block Figure 11 is shown.

[0061] ​Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that the technical solutions recorded in the foregoing embodiments can still be modified, or some technical features therein can be replaced equivalently; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the utility model.

Claims

1. A folding wing UAV launcher apparatus, characterized by, The utility model relates to a folding wing unmanned plane launching device, including the launching cylinder (1), one end of the launching cylinder (1) is connected with the air chamber (3), the piston (7) is slidably installed in the air chamber (3), the air chamber (3) is connected with the installation base (5) away from the one end of launching cylinder (1), the upper surface of installation base (5) is installed with the gas generator (4), and the gas generator (4) is located in the space surrounded by the air chamber (3), the piston (7) and installation base (5).

2. The folding-wing UAV launching device according to claim 1, wherein, The one end of installation base (5) is connected with the handle (6) away from the gas generator (4), and the air chamber (3) and installation base (5) are detachably connected.

3. The folding-wing UAV launching device according to claim 1, wherein, The folding wing unmanned plane launching device further includes a plurality of support plates (2) installed in sequence at the connection between the inner surface of the launching cylinder (1) and the inner surface of the air chamber (3).

4. The folding-wing UAV launching device according to claim 1, wherein, The piston (7) includes a piston housing (71) provided with a clamping groove (72) at one end away from the gas generator (4).

5. The folding-wing UAV launching device according to claim 4, wherein, The piston housing (71) is provided with a hook (73) at one end close to the gas generator (4), and the hook (73) is connected with the parachute.

6. The folding-wing UAV launching device according to claim 2, wherein, The folding wing unmanned plane launching device further includes a support base (8) and a support frame (9), the support base (8) is installed at the corner of the air chamber (3) close to the handle (6), and the support frame (9) is installed on the outer surface of the launching cylinder (1) away from the handle (6).

7. The folding-wing UAV launching device according to claim 6, wherein, The support frame (9) includes a rotating shaft (92), a shaft sleeve (93) and a support leg (94), the shaft sleeve (93) is connected with the outer surface of the launching cylinder (1), the rotating shaft (92) is rotatably installed in the shaft sleeve (93), and the support leg (94) is fixedly connected with the rotating shaft (92).

8. The folding-wing UAV launching device according to claim 7, wherein, The support frame (9) further includes a clamp (91), the clamp (91) is sleeved on the outer surface of the launching cylinder (1), and the shaft sleeve (93) is installed on the outer surface of the clamp (91).

9. The folding-wing UAV launching device of claim 7, wherein, The support frame (9) further includes a fixing table (95), one end of the fixing table (95) is fixedly installed on the end face of the rotating shaft (92), and the other end is fixedly connected with the support leg (94).

10. The folding-wing UAV launching device of claim 1, wherein, The folding wing unmanned plane launching device further includes a control system, the control system includes a battery, a manual switch, a remote control switch and the gas generator (4) connected in sequence.

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