Cylindrical fixed-wing unmanned aerial vehicle

Abstract

The utility model discloses a cylindrical fixed-wing unmanned aerial vehicle and relates to the technical field of unmanned aerial vehicles. The barrel-shooting fixed-wing unmanned aerial vehicle comprises a launching part and an unmanned aerial vehicle body, the launching part comprises a launching barrel and a support fixing base used for supporting the launching barrel, and a high-pressure gas tank is arranged on the support fixing base and communicates with an inner cavity of the launching barrel through a pipeline. According to the barrel-shot fixed-wing unmanned aerial vehicle, wing parts and flaps of the unmanned aerial vehicle main body fuselage can be folded, the unmanned aerial vehicle main body can be conveniently stored in the launching barrel, after the unmanned aerial vehicle main body is launched out of the barrel, all the unmanned aerial vehicle main body is automatically unfolded, the unmanned aerial vehicle main body fuselage is in a cube shape, and the unmanned aerial vehicle main body is not prone to rotating when placed in the launching barrel; therefore, it is guaranteed that the barrel-shot fixed-wing unmanned aerial vehicle is compact in overall structure, convenient to store and easy to carry and transport, and meanwhile the requirement for rapid and high-speed launching is met.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a tube-launched fixed-wing unmanned aerial vehicle. Background Art

[0002] Fixed-wing drones are a type of drone whose wings are fixed and do not need to rotate, relying on the airflow passing over the wings to provide lift. This type of drone usually uses an engine or electric drive system to provide thrust to drive the drone forward and overcome air resistance. Its flight principle is based on aerodynamics, generating lift through the action of wing shape and airflow, while relying on thrust to provide forward power.

[0003] Traditional fixed-wing UAVs require catapult takeoff. The fixed wings of the fixed-wing UAVs in the prior art are usually fixed and not easy to fold. Therefore, it is inconvenient to transport them. Moreover, the catapult equipment, as an auxiliary equipment for launching, also takes up a lot of space. For application scenarios that require a large number of fixed-wing UAVs, traditional fixed-wing UAVs cannot meet the requirements of fast and high-speed launching. In view of the shortcomings of the prior art, the utility model provides a tube-launched fixed-wing UAV to solve the above problems. Utility Model Content

[0004] In view of the deficiencies in the prior art, the utility model provides a tube-launched fixed-wing UAV. The wing parts and flaps of the main fuselage of the UAV are foldable, and the main body of the UAV is convenient to be stored inside the launching tube. When the main body of the UAV is launched out of the tube, it is automatically unfolded. The main body of the UAV is in a cube shape, so that the main body of the UAV is not easy to rotate when placed in the launching tube, thereby ensuring a stable posture during launching. Therefore, the overall structure of the tube-launched fixed-wing UAV is compact, convenient to store, easy to carry and transport, and at the same time meets the requirements of fast and high-speed launching.

[0005] To achieve the above objectives, the utility model is implemented through the following technical solutions: a tube-launched fixed-wing UAV, comprising a launching unit and a UAV body, the launching unit comprising a launching tube and a bracket fixing seat for supporting the launching tube, a high-pressure gas tank is arranged on the bracket fixing seat, and the high-pressure gas tank is connected to the inner cavity of the launching tube through a pipeline;

[0006] The drone body includes a brushless motor and a foldable rear wing, a front wing and a flap arranged on the drone body. The drone body is provided with a plurality of sets of wing folding plates, and the wing folding plates are respectively used to fold and support the rear wing, the flap and the front wing;

[0007] A battery body is arranged inside the drone body, a foldable blade is arranged at the output end of the brushless motor, and the battery body is electrically connected to the brushless motor.

[0008] Preferably, a solenoid valve is installed on the pipeline between the high-pressure gas tank and the launching tube, and a sealing seat is provided between the launching tube and the pipeline of the high-pressure gas tank.

[0009] Preferably, the rear wing is provided with a rudder and a rudder surface control steering gear for rudder transmission.

[0010] Preferably, the wing folding disc includes a pin, a sleeve and a torsion spring, the sleeve is arranged on the rear wing, the front wing and the flap, the pin is arranged on the drone body, the pin is plugged into the sleeve, and the torsion spring is arranged between the sleeve and the drone body for fixation.

[0011] Preferably, parachutes are installed on both sides of the drone body.

[0012] Preferably, a pitot tube and a navigation camera are provided at the front end of the drone body.

[0013] Preferably, a power switch and a charging port are provided on the drone body.

[0014] The utility model discloses a tube-launched fixed-wing UAV, which has the following beneficial effects:

[0015] The wing part and flaps of the main fuselage of the tube-launched fixed-wing UAV are foldable, and the main body of the UAV is easy to store inside the launching tube. When the main body of the UAV is launched out of the tube, it is automatically unfolded. The main body of the UAV adopts a cube shape, so that the main body of the UAV is not easy to rotate when placed in the launching tube, ensuring a stable posture during launching. Therefore, the overall structure of the tube-launched fixed-wing UAV is compact, convenient to store, easy to carry and transport, and at the same time meets the needs of fast and high-speed launching. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0018] Figure 2 It is a structural schematic diagram of the transmitting part of the utility model;

[0019] Figure 3 It is a side view of the main body of the UAV of the utility model;

[0020] Figure 4 It is a schematic diagram of a half-supported UAV body of the utility model;

[0021] Figure 5 It is a schematic diagram of the fully supported main body of the UAV of the utility model.

[0022] In the figure: 1. launching unit; 101. launching tube; 102. bracket fixing seat; 103. high-pressure gas tank; 104. solenoid valve; 105. sealing seat; 2. drone body; 201. brushless motor; 2011. folding blades; 202. rear wing; 2021. rudder; 2022. rudder control servo; 203. front wing; 2031. wing folding plate; 204. flap; 205. parachute; 206. battery body; 2061. power switch; 2062. charging port; 207. pitot tube; 208. navigation camera. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solution and advantages of the embodiments of the utility model clearer, the technical solution in the embodiments of the utility model is described clearly and completely. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of 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.

[0024] The embodiment of the present application provides a tube-launched fixed-wing UAV, which solves the problem that traditional fixed-wing UAVs need to be launched by catapult, the unfolded wings are extremely inconvenient during transportation, and the catapult equipment, as an auxiliary equipment for launching, takes up a lot of space. For application scenarios that require strong maneuverability, traditional fixed-wing UAVs cannot meet the needs of fast and high-speed launching.

[0025] In order to better understand the above technical solution, the above technical solution will be described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0026] The utility model embodiment discloses a tube-launched fixed-wing UAV. Figure 1-5 As shown, it includes a launching unit 1 and a drone body 2, the launching unit 1 includes a launching tube 101 and a bracket fixing seat 102 for supporting the launching tube 101, a high-pressure gas tank 103 is provided on the bracket fixing seat 102, and the high-pressure gas tank 103 is connected to the inner cavity of the launching tube 101 through a pipeline;

[0027] The drone body 2 includes a brushless motor 201 and a foldable rear wing 202, a front wing 203 and a flap 204 arranged on the drone body 2. A plurality of sets of wing folding plates 2031 are installed on the drone body 2. The wing folding plates 2031 are used to fold and support the rear wing 202, the flap 204 and the front wing 203 respectively.

[0028] A battery body 206 is disposed inside the drone body 2 , and a foldable blade 2011 is disposed at the output end of the brushless motor 201 . The battery body 206 is electrically connected to the brushless motor 201 .

[0029] Furthermore, a solenoid valve 104 is installed on the pipeline between the high-pressure gas tank 103 and the launching tube 101, and a sealing seat 105 is provided between the launching tube 101 and the pipeline of the high-pressure gas tank 103. The design of the solenoid valve 104 facilitates the connection or disconnection of the pipeline between the high-pressure gas tank 103 and the launching tube 101, thereby facilitating the control of the drone body 2 for pneumatic ejection.

[0030] Furthermore, the rear wing 202 is provided with a rudder 2021 and a control servo 2022 for driving the rudder 2021. The rudder 2021 and the control servo 2022 facilitate the use of the rear wing 202 to control the posture of the drone body 2 and achieve steering and other actions.

[0031] Specifically disclosed, the wing folding plate 2031 includes a pin, a sleeve and a torsion spring. The sleeve is arranged on the rear wing 202, the front wing 203 and the flap 204. The pin is arranged on the drone body 2, the pin is plugged into the sleeve, and the torsion spring is arranged between the sleeve and the drone body 2 for fixation. Due to the design of the pin and the sleeve, the rear wing 202, the front wing 203 and the flap 204 can be rotated and folded along the surface of the drone body 2. Through the torsion spring design, the torsion spring is compressed after folding. When the drone body 2 is launched out of the tube, the torsion spring is reset and drives the rear wing 202, the front wing 203 and the flap 204 to automatically reset. At the same time, the bracket fixing seat 102 on the launching tube 101 also has a folding function. Therefore, the entire launching part 1 and the drone body 2 are easy to fold and store, which reduces the carrying space and is easy to carry and transport.

[0032] Furthermore, parachutes 205 are installed on both sides of the drone body 2. The parachutes 205 are automatically popped out when the drone body 2 is recovered, making the recovery of the drone body 2 convenient.

[0033] Furthermore, a pitot tube 207 and a navigation camera 208 are provided at the front end of the drone body 2. The pitot tube 207 uses the relative air flow rate to control the flight speed of the drone body 2, and the navigation camera 208 is connected to the ground control terminal through the flight control and image data link, so that the drone body 2 can automatically navigate to the preset sky or target area.

[0034] Specifically, a power switch 2061 and a charging port 2062 are provided on the drone body 2. The charging port 2062 is convenient for charging the battery body 206, and the power switch 2061 is convenient for controlling the power-on and power-off states of the battery body 206.

[0035] The fixed-wing UAV launched by the barrel has a cubic shape of the UAV body 2, so that the UAV body 2 is not easy to rotate when placed in the launch barrel 101, ensuring a stable posture during launch;

[0036] The wing part and flaps 204 of the fuselage of the drone body 2 are foldable, and when the drone body 2 is launched out of the tube, they are all automatically unfolded, which also ensures that a single person can carry more in a backpack during transportation;

[0037] The lower end of the launch tube 101 is connected with a high-pressure gas tank 103, which is inflated to 1.6 MPa by an air pump, and is equipped with a solenoid valve 104 and a start switch. The high-pressure gas tank 103 is deflated by controlling the switch of the solenoid valve 104, and the drone body 2 is instantly launched;

[0038] The front end of the drone body 2 is equipped with a pitot tube 207, which uses the relative air flow rate to control the flight speed of the drone body 2; the front end of the drone body 2 is equipped with a navigation camera 208, which is connected to the ground control terminal through the flight control and image data link, so that the drone body 2 can automatically navigate to the preset sky or target area;

[0039] The drone body 2 has a built-in battery body 206. When the battery power is exhausted, the battery body 206 does not need to be taken out for charging. The battery body 206 can be charged through the charging port 2062, the charging cable and the external power source.

[0040] The belly of the drone body 2 is equipped with a parachute 205. When the drone body 2 completes the mission, the parachute 205 can be automatically ejected for landing and recovery.

[0041] The above shows and describes the basic principle and main features of the utility model and the advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions are only for explaining the principle of the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the utility model to be protected. The scope of protection claimed by the utility model is defined by the attached claims and their equivalents.

Claims

1. A tube-launched fixed-wing UAV, comprising a launch unit (1) and a UAV body (2), characterized in that: The launching unit (1) comprises a launching tube (101) and a support fixing seat (102) for supporting the launching tube (101); a high-pressure gas tank (103) is provided on the support fixing seat (102); the high-pressure gas tank (103) is connected to the inner cavity of the launching tube (101) through a pipeline; The drone body (2) comprises a brushless motor (201) and a foldable rear wing (202), a front wing (203) and a flap (204) arranged on the drone body (2); a plurality of sets of wing folding plates (2031) are installed on the drone body (2); the wing folding plates (2031) are respectively used to fold and support the rear wing (202), the flap (204) and the front wing (203); A battery body (206) is provided inside the drone body (2), a folding blade (211) is provided at the output end of the brushless motor (201), and the battery body (206) is electrically connected to the brushless motor (201); A solenoid valve (104) is installed on the pipeline between the high-pressure gas tank (103) and the launching tube (101), and a sealing seat (105) is provided between the launching tube (101) and the pipeline of the high-pressure gas tank (103).

2. A tube-launched fixed-wing UAV according to claim 1, characterized in that: The rear wing (202) is provided with a rudder (221) and a rudder surface control steering gear (222) for driving the rudder (2021).

3. The tube-launched fixed-wing UAV according to claim 1, characterized in that: The wing folding disc (2031) comprises a pin shaft, a shaft sleeve and a torsion spring; the shaft sleeve is arranged on the rear wing (202), the front wing (203) and the flap (204); the pin shaft is arranged on the drone body (2); the pin shaft is plugged into the shaft sleeve; and the torsion spring is arranged between the shaft sleeve and the drone body (2) for fixation.

4. The tube-launched fixed-wing UAV according to claim 3, characterized in that: Parachutes (205) are installed on both sides of the drone body (2).

5. The tube-launched fixed-wing UAV according to claim 1, characterized in that: The front end of the drone body (2) is provided with a pitot tube (207) and a navigation camera (208).

6. The tube-launched fixed-wing UAV according to claim 1, characterized in that: The drone body (2) is provided with a power switch (2061) and a charging port (2062).

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