Pneumatic launching propeller type unmanned aerial vehicle

Abstract

The utility model discloses a pneumatic launching propeller type unmanned aerial vehicle which comprises an unmanned aerial vehicle body and a launching device. The unmanned aerial vehicle body comprises a fuselage, wings, propellers and foldable empennages, the wings are arranged on the two sides of the front portion of the fuselage, the propellers are arranged on the head of the fuselage or the front sides of the wings, and the foldable empennages are arranged at the tail of the fuselage. The launching device comprises a launching cylinder and a compressed air storage tank, one end of the launching cylinder is provided with a launching cavity for containing the rear half section of the fuselage, a sealing piston used for abutting against the rear end of the fuselage is arranged in the launching cavity in a sliding mode, the compressed air storage tank is communicated with the launching cavity through the other end of the launching cylinder, and the compressed air storage tank is provided with a pneumatic valve. Before launching, the foldable empennage is folded and put into a launching cavity of the launching cylinder, launching of the unmanned aerial vehicle is completed through compressed air, and after the unmanned aerial vehicle body leaves the launching cylinder, the foldable empennage is unfolded. Therefore, pneumatic launching can be achieved through the launching cylinder, and the device has the advantages of being small in size, free of additional structural supporting, easy to operate and transport and the like.

Description

Technical Field

[0001] The utility model relates to the field of unmanned aerial vehicles, in particular to a propeller-type unmanned aerial vehicle with pneumatic launch. Background Art

[0002] When launching a traditional oil-powered propeller-type patrol drone, the engine must be started first and then launched after it runs stably. Therefore, due to structural limitations, it is impossible to use pneumatic launch in the launch tube. Therefore, the launch of an oil-powered propeller-type patrol drone can only be launched by pushing with a launch rod, but the force applied by the launch rod is not ideal, and the aircraft state is not stable enough during launch. Utility Model Content

[0003] The utility model aims to solve at least one of the technical problems existing in the prior art. To this end, the utility model proposes a pneumatically launched propeller-type UAV, which can be pneumatically launched using a launch tube, has the advantages of small size, no need for additional structural support, and simple operation and transportation.

[0004] The technical solution adopted by the utility model to solve its technical problems is:

[0005] A pneumatically launched propeller-type UAV, comprising

[0006] The drone body comprises a fuselage, wings, propellers and a foldable tail, wherein the wings are arranged on both sides of the front part of the fuselage, the propellers are arranged on the head of the fuselage or on the front side of the wings, and the foldable tail is arranged at the tail of the fuselage;

[0007] The launching device comprises a launching tube and a compressed air storage tank. A launching chamber for accommodating the rear half of the fuselage is provided at one end of the launching tube. A sealing piston for abutting against the rear end of the fuselage is slidably provided in the launching chamber. The compressed air storage tank is connected to the launching chamber via the other end of the launching tube. The compressed air storage tank is provided with a pneumatic valve.

[0008] A propeller-type drone with pneumatic launch according to an embodiment of the utility model has at least the following beneficial effects: before launching, the foldable tail is folded and placed in the launch chamber of the launch tube, so that the lower half of the fuselage of the drone body is located in the launch chamber, and the wings and propellers are located outside the launch tube; when launching, the drone motor is started first, and the propeller rotates. After the operation is stable, the pneumatic valve is opened to release the compressed air from the compressed air storage tank, and the compressed air is used to push the drone body out of the launch tube through the sealed piston and reach the take-off speed, completing the drone launch. After the drone body leaves the launch tube, the foldable tail is unfolded. Therefore, it can be pneumatically launched using a launch tube, which has the advantages of small size, no need for additional structural support, and simple operation and transportation.

[0009] According to some embodiments of the utility model, the foldable tail includes two vertical tails and two horizontal tails, a first mounting plane is provided on both sides of the fuselage, the first mounting plane is provided with a first mounting hole, the vertical tail is installed in the first mounting hole through a fixing pin and a return spring, a mounting seat is provided on the bottom side of the fuselage, mounting columns are respectively provided on both sides of the mounting seat, and the horizontal tail is installed on the mounting columns through a return spring.

[0010] The benefit is that when installed in this way, the vertical tail and the horizontal tail can be manually folded and placed into the launch chamber of the launch tube. After the drone body leaves the launch tube, the vertical tail and the horizontal tail are free from external force and can freely return to the unfolded state under the action of the return spring.

[0011] According to some embodiments of the present utility model, the launching tube is provided with a first mounting bracket.

[0012] Advantageously, provision of a first mounting bracket facilitates fixed installation of the launch tube.

[0013] According to some embodiments of the present utility model, the compressed air storage tank is provided with a second mounting bracket.

[0014] Advantageously, the second mounting bracket is provided to facilitate fixed installation of the compressed air storage tank.

[0015] According to some embodiments of the present invention, the height of the first mounting bracket is greater than the height of the second mounting bracket.

[0016] Advantageously, the installation height of the launch tube is higher than the installation height of the compressed air storage tank, so that the launch tube is directed toward the air, which is beneficial for the launch of the UAV.

[0017] According to some embodiments of the utility model, the compressed air storage tank is connected to the launching tube via a metal pipe.

[0018] The advantage is that the use of metal pipe connection is conducive to fixing and supporting the launch tube, and the metal pipe can withstand the high pressure of compressed air.

[0019] According to some embodiments of the utility model, the compressed air storage tank is also provided with a launch switch and a solenoid valve, the launch switch is used to control the solenoid valve, and the solenoid valve is used to control the pneumatic valve.

[0020] The benefit is that the switch of the pneumatic valve can be controlled by the launch switch and the solenoid valve, which facilitates the launch.

[0021] According to some embodiments of the present invention, the propeller also includes an oil-powered engine.

[0022] The benefit is that the propeller can be driven by the oil-powered engine to rotate, thereby providing power for the main body of the drone.

[0023] According to some embodiments of the present invention, the propeller is arranged at the head of the fuselage.

[0024] Advantageously, the propeller is arranged at the head of the fuselage as a single-engine system.

[0025] According to some embodiments of the present invention, the propeller is arranged on the front side of the wing.

[0026] Advantageously, the propeller is arranged on the front side of the wing for a twin-engine system.

[0027] Additional aspects and advantages of the present invention will be given in part in the following description, and in part will become apparent from the following description, or will be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0029] Figure 1 A schematic diagram of an embodiment of the utility model;

[0030] Figure 2 for Figure 1 Schematic diagram of the installation of the fuselage and sealing piston in the middle launch tube;

[0031] Figure 3 for Figure 2 Schematic diagram of the folding of the mid-horizontal tail;

[0032] Figure 4 for Figure 1 Schematic diagram of the main body of the drone after it is launched and deployed;

[0033] Figure 5 for Figure 4 Schematic diagram of the installation of the middle vertical tail;

[0034] Figure 6 for Figure 4 Schematic diagram of the deployment of the mid-horizontal tail;

[0035] Figure 7 It is a schematic diagram of another embodiment of the utility model.

[0036] Figure numerals: fuselage 100, wing 110, propeller 120, launch tube 130, compressed air storage tank 140, sealing piston 150, pneumatic valve 160, vertical tail 170, horizontal tail 180, first mounting plane 190, first mounting hole 200, fixing pin 210, return spring 220, mounting seat 230, mounting column 240, first mounting bracket 250, second mounting bracket 260, metal tube 270, launch switch 280, solenoid valve 290, oil-driven engine 300. DETAILED DESCRIPTION

[0037] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0038] In the description of the present invention, it should be understood that descriptions involving orientation, such as up, down, front, back, left, right, etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0039] In the description of the present utility model, "several" means one or more, "more" means more than two, "greater than", "less than", "exceed" etc. are understood to exclude the number itself, and "above", "below", "within" etc. are understood to include the number itself. If there is a description of "first" or "second", it is only used for the purpose of distinguishing the technical features, and cannot be understood as indicating or implying the relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0040] In the description of the present invention, unless otherwise clearly defined, terms such as setting, installing, connecting, etc. should be understood in a broad sense, and technicians in the relevant technical field can reasonably determine the specific meanings of the above terms in the present invention based on the specific content of the technical solution.

[0041] Reference below Figure 1-Figure 7 A pneumatically launched propeller-type UAV is described in detail with two specific embodiments. It is worth noting that the following description is only an exemplary description and not a specific limitation of the utility model.

[0042] like Figure 1-Figure 6 As shown, a pneumatically launched propeller 120-type UAV includes a UAV body and a launching device.

[0043] Among them, the drone body includes a fuselage 100, wings 110, propellers 120 and a foldable tail. The wings 110 are arranged on both sides of the front of the fuselage 100, the propellers 120 are arranged at the head of the fuselage 100 or the front side of the wings 110, and the foldable tail is arranged at the tail of the fuselage 100; the launching device includes a launching tube 130 and a compressed air storage tank 140, and one end of the launching tube 130 is provided with a launching chamber for accommodating the rear half of the fuselage 100, and a sealing piston 150 for abutting against the rear end of the fuselage 100 is slidably provided in the launching chamber, and the compressed air storage tank 140 is connected to the launching chamber through the other end of the launching tube 130, and the compressed air storage tank 140 is provided with a pneumatic valve 160. Before launching, the foldable tail is folded and placed in the launch chamber of the launch tube 130, so that the lower half of the fuselage 100 of the drone body is located in the launch chamber, and the wings 110 and propellers 120 are located outside the launch tube 130; when launching, the drone motor is started first, and the propeller 120 rotates. After the operation is stable, the pneumatic valve 160 is opened to release the compressed air from the compressed air storage tank 140, and the compressed air is used to push the drone body out of the launch tube 130 through the sealing piston 150 and reach the take-off speed, completing the launch of the drone. After the drone body leaves the launch tube 130, the foldable tail is unfolded. Therefore, it can be pneumatically launched using the launch tube 130, which has the advantages of small size, no need for additional structural support, simple operation and transportation, etc.

[0044] like Figure 2-Figure 6 As shown, the foldable tail includes two vertical tails 170 and two horizontal tails 180, first mounting planes 190 are provided on both sides of the fuselage 100, first mounting holes 200 are provided on the first mounting holes 200, the vertical tail 170 is installed in the first mounting holes 200 through fixing pins 210 and return springs 220, a mounting seat 230 is provided on the bottom side of the fuselage 100, mounting posts 240 are provided on both sides of the mounting seat 230, and the horizontal tail 180 is installed on the mounting posts 240 through return springs 220. When installed in this way, the vertical tail 170 and the horizontal tail 180 can be manually folded and put into the launch chamber of the launch tube 130, and after the main body of the drone leaves the launch tube 130, the vertical tail 170 and the horizontal tail 180 are free from external force and can freely return to the unfolded state under the action of the return spring 220.

[0045] like Figure 1As shown, the launch tube 130 is provided with a first mounting bracket 250. The first mounting bracket 250 is provided to facilitate the fixed installation of the launch tube 130. In addition, the compressed air storage tank 140 is provided with a second mounting bracket 260. The second mounting bracket 260 is provided to facilitate the fixed installation of the compressed air storage tank 140. Specifically, the height of the first mounting bracket 250 is greater than the height of the second mounting bracket 260. This arrangement makes the installation height of the launch tube 130 higher than the installation height of the compressed air storage tank 140, so that the launch tube 130 is facing the air, which is conducive to the launch of the drone. Further, the compressed air storage tank 140 is connected to the launch tube 130 through a metal tube 270. The use of the metal tube 270 connection is conducive to the fixed support of the launch tube 130, and the metal tube 270 can withstand the high pressure of compressed air. It can be understood that the compressed air storage tank 140 is also provided with a launch switch 280 and a solenoid valve 290, the launch switch 280 is used to control the solenoid valve 290, and the solenoid valve 290 is used to control the pneumatic valve 160. In this way, the switch of the pneumatic valve 160 can be controlled by the launch switch 280 and the solenoid valve 290, so as to facilitate the launch.

[0046] It should be noted that the propeller 120 also includes an oil-driven engine 300. The oil-driven engine 300 can drive the propeller 120 to rotate, thereby providing power for the drone body. Specifically, the propeller 120 is arranged at the head of the fuselage 100. The propeller 120 is arranged at the head of the fuselage 100 as a single engine system.

[0047] like Figure 7 As shown, in another embodiment of the present invention, the propeller 120 is arranged on the front side of the wing 110. The propeller 120 is arranged on the front side of the wing 110 as a twin-engine system.

[0048] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments. Various changes can be made within the knowledge scope of ordinary technicians in the technical field without departing from the purpose of the present invention.

Claims

1. A propeller (120) type unmanned aerial vehicle with pneumatic launch, characterized in that: include: A drone body comprises a fuselage (100), wings (110), propellers (120) and a foldable tail wing, wherein the wings (110) are arranged on both sides of the front part of the fuselage (100), the propellers (120) are arranged at the head of the fuselage (100) or the front side of the wings (110), and the foldable tail wing is arranged at the tail of the fuselage (100); A launching device comprises a launching tube (130) and a compressed air storage tank (140); one end of the launching tube (130) is provided with a launching chamber for accommodating the rear half of the fuselage (100); a sealing piston (150) is slidably provided in the launching chamber for abutting against the rear end of the fuselage (100); the compressed air storage tank (140) is connected to the launching chamber through the other end of the launching tube (130); and the compressed air storage tank (140) is provided with a pneumatic valve (160).

2. A pneumatically launched propeller (120) type UAV according to claim 1, characterized in that: The foldable tail comprises two vertical tails (170) and two horizontal tails (180); first mounting planes (190) are provided on both sides of the fuselage (100); the first mounting planes (190) are provided with first mounting holes (200); the vertical tail (170) is installed in the first mounting holes (200) through fixing pins (210) and return springs (220); a mounting seat (230) is provided on the bottom side of the fuselage (100); mounting posts (240) are provided on both sides of the mounting seat (230); and the horizontal tail (180) is installed on the mounting posts (240) through return springs (220).

3. A pneumatically launched propeller (120) type UAV according to claim 1, characterized in that: The launching tube (130) is provided with a first mounting bracket (250).

4. A pneumatically launched propeller (120) type UAV according to claim 3, characterized in that: The compressed air storage tank (140) is provided with a second mounting bracket (260).

5. A pneumatically launched propeller (120) type UAV according to claim 4, characterized in that: The height of the first mounting bracket (250) is greater than the height of the second mounting bracket (260).

6. A pneumatically launched propeller (120) type UAV according to claim 5, characterized in that: The compressed air storage tank (140) is connected to the launching tube (130) via a metal pipe (270).

7. A pneumatically launched propeller (120) type UAV according to claim 1, characterized in that: The compressed air storage tank (140) is also provided with a transmitting switch (280) and a solenoid valve (290), wherein the transmitting switch (280) is used to control the solenoid valve (290), and the solenoid valve (290) is used to control the pneumatic valve (160).

8. A pneumatically launched propeller (120) type UAV according to claim 1, characterized in that: The propeller (120) further includes an oil-powered engine (300).

9. A pneumatically launched propeller (120) type UAV according to claim 8, characterized in that: The propeller (120) is arranged at the head of the fuselage (100).

10. A pneumatically launched propeller (120) type UAV according to claim 8, characterized in that: The propeller (120) is arranged on the front side of the wing (110).

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