CN115649500A - folding multi-rotor drone - Google Patents

Abstract

The invention discloses a folding multi-rotor unmanned aerial vehicle, which comprises: the multi-rotor unmanned aerial vehicle is characterized in that the arms of the multi-rotor unmanned aerial vehicle are in an opening state and a folding state; launch section, it includes the barrel, when this many rotor unmanned aerial vehicle do not take off, this many rotor unmanned aerial vehicle are folding to draw in this barrel, still be provided with piston and gas generator in this barrel, the top of this piston and the contact of this many rotor unmanned aerial vehicle, the bottom of this piston is provided with this gas generator, produce gas after this gas generator electricity is igniteed, this gas promotes this piston and upwards moves, thereby launch away this many rotor unmanned aerial vehicle from this barrel, make this many rotor unmanned aerial vehicle take off. According to the invention, the multi-rotor unmanned aerial vehicle is accommodated in the barrel, when the multi-rotor unmanned aerial vehicle needs to be used, the gas generator is started to electrically ignite to generate gas to push the piston to move upwards, so that the unmanned aerial vehicle is launched out of the barrel, and the technical problem that the multi-rotor unmanned aerial vehicle is inconvenient to carry in the prior art is solved.

Description

Folding multi-rotor UAV

technical field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a folding multi-rotor unmanned aerial vehicle.

Background technique

With the further development of science and technology, unmanned operations based on informatization and intelligence have become the mainstream of the world today, and unmanned operations have also become the main trend of future warfare. With the development of drone technology, people are more and more inclined to use drones in future warfare.

A multi-rotor UAV is a UAV with three or more rotor shafts. It drives the rotors through the rotation of the motor on each shaft to generate thrust. The collective distance of the rotors is fixed. By changing the distance between different rotors The relative speed can change the size of the single-axis propulsion, thereby controlling the trajectory of the aircraft. The multi-rotor UAV has strong controllability, can take off and land vertically and hover, and is mainly suitable for low-altitude, low-speed, vertical take-off and landing and hovering. Stop the requested task type. At present, multi-rotor UAVs have been widely used in battlefield operations. How to make multi-rotor UAVs portable during combat is an urgent technical problem that needs to be solved.

Contents of the invention

The present invention aims to solve one of the technical problems in the related art at least to a certain extent. For this reason, an object of the present invention is to provide a folding multi-rotor UAV, which is easy to carry and can be widely used in battlefield operations.

The technical scheme adopted in the present invention is:

In a first aspect, the present invention provides a folding multi-rotor UAV, comprising: a multi-rotor UAV, the arms of the multi-rotor UAV have two states: open and folded; a launcher, the launcher includes a barrel , when the multi-rotor UAV is not taking off, the multi-rotor UAV is folded and folded in the cylinder, the cylinder is also provided with a piston and a gas generator, and the top of the piston is in contact with the multi-rotor UAV, The bottom of the piston is provided with the gas generator, which generates gas after electric ignition, and the gas pushes the piston to move upwards, thereby launching the multi-rotor UAV from the cylinder, making the multi-rotor unmanned The plane takes off.

Wherein, the multi-rotor UAV includes: a warhead, which forms the lower part of the multi-rotor UAV; an arm mounting seat, which forms the middle part of the multi-rotor UAV, and the arm mount The base is provided with a plurality of arms, and each arm is provided with a motor and a propeller; the fuselage forms the upper part of the multi-rotor UAV, and the fuselage is provided with positioning antennas, dual Fold the communication antenna, circuit board, and battery.

Wherein, the warhead is a warhead formed by self-forging fragments.

Among them, the circuit board includes: a flight control board, a communication board, a mission computer, a power board, and an electric adjustment board.

Wherein, the top of the piston is provided with a USB pin, and the combat part is provided with a slot matching the USB pin, and the combat part is electrically connected and installed on the piston through the USB pin.

Wherein, the lower part of the warhead is provided with a plurality of sensors, and the types of the sensors include at least one of the following: radar, optical camera or laser range finder.

Wherein, the cylinder is provided with a base, the bottom is arranged on the bottom of the cylinder, the base is provided with a limit guide post, and the piston is arranged on the base through the limit guide post.

Wherein, a wire rope is arranged between the base and the piston, one end of the wire rope is arranged on the base, and the other end of the wire rope is arranged on the piston, and the wire rope is used to pull the piston when it pushes upwards in the barrel. The piston prevents the piston from being ejected from the barrel.

Among them, it also includes: a remote control device, which is used to control the flight of the multi-rotor UAV and start the explosion of the warhead.

The beneficial effects of the present invention are:

In the present invention, the multi-rotor UAV is accommodated in the barrel, and when the multi-rotor UAV needs to be used, the electric ignition of the gas generator is started to generate gas to push the piston upward, so that the multi-rotor UAV is launched from the barrel To overcome the technical problem of inconvenient carrying multi-rotor UAV in the prior art.

In addition, the multi-rotor drone of the present invention has a warhead, and there are multiple sensors below the warhead. When the multi-rotor drone arrives at the destination, it will decide whether to start The warhead explodes to hit the target.

Description of drawings

Fig. 1 is a structural schematic diagram of the folded multi-rotor UAV of an embodiment of the multi-rotor UAV in an unexposed state;

Fig. 2 is a structural schematic diagram of an embodiment of the folding multi-rotor UAV in which the multi-rotor UAV has been released but the arms are not opened;

Fig. 3 is a structural schematic diagram of an embodiment of the folding multi-rotor UAV of the present invention, in which the multi-rotor UAV has been released and the arm is in an opened state;

FIG. 4 is a schematic diagram of an exploded structure of an embodiment of the launch unit 11 in FIG. 3;

FIG. 5 is a schematic structural diagram of an embodiment of the multi-rotor UAV 12 shown in FIG. 3 .

Detailed ways

It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.

In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Orientation or position indicated by "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" The relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, therefore It should not be construed as a limitation of the application. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be interpreted as indicating or implying relative importance or implicitly specifying the quantity of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of said features. In the description of the present application, "plurality" means two or more, unless otherwise specifically defined.

In the description of this application, it should be noted that unless otherwise specified and limited, the terms "installation", "connection", and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it can be mechanically connected, or electrically connected, or can communicate with each other; it can be directly connected, or indirectly connected through an intermediary, and it can be the internal communication of two components or the interaction of two components relation. Those of ordinary skill in the art can understand the specific meanings of the above terms in this application according to specific situations.

In this application, unless otherwise expressly specified and limited, a first feature being "on" or "under" a second feature may include direct contact between the first and second features, and may also include the first and second features Not in direct contact but through another characteristic contact between them. Moreover, "above", "above" and "above" the first feature on the second feature include that the first feature is directly above and obliquely above the second feature, or simply means that the first feature is horizontally higher than the second feature. "Below", "beneath" and "under" the first feature to the second feature include that the first feature is directly below and obliquely below the second feature, or simply means that the first feature has a lower level than the second feature.

Please refer to Figure 1 to Figure 3 together. As shown in FIGS. 1 to 3 , the folding multi-rotor UAV includes a launcher 11 and a multi-rotor UAV 12 . FIG. 1 to FIG. 3 show the state change diagrams of the multi-rotor UAV 12 from stationary to flying in the launching part 11 . As shown in FIG. 1 , the multi-rotor UAV 12 is initially set statically in the launching part 11 . After the multi-rotor UAV 12 receives the take-off command, as shown in FIG. 2 , the multi-rotor UAV 12 flies out from the launching part 11, but the arms are not opened yet. As the multi-rotor UAV 12 continues to fly, as shown in FIG. 3 , the multi-rotor UAV 12 opens a plurality of arms and keeps flying stably.

Please refer to FIG. 4 . FIG. 4 is a schematic diagram of an exploded structure of an embodiment of the emitting unit 11 in FIG. 3 . As shown in FIG. 4 , the launching part 11 includes a barrel 111 , a base (not shown), a piston 112 and a gas generator 113 .

The base is disposed at the bottom of the barrel 111 . Preferably, a limiting guide post 114 is arranged on the base, and the piston 112 is arranged on the base through the limiting guide post 114 .

When the multi-rotor drone 12 is not taking off, the multi-rotor drone 12 is folded and folded in the barrel 111, the top of the piston 112 is in contact with the multi-rotor drone 12, and the bottom of the piston 112 is provided with the gas Generator 113. The gas generator 113 generates gas after being electrically ignited, and the gas pushes the piston 112 to move upward, thereby giving the multi-rotor UAV 12 an upward momentum, and launching the multi-rotor UAV 12 from the cylinder 111, Make this multi-rotor UAV 12 take off.

Preferably, a wire rope (not shown) is arranged between the base and the piston 112, one end of the wire rope is arranged on the base, the other end of the wire rope is arranged on the piston 112, and the wire rope is used for the piston 112 to When the cylinder 111 is pushed upwards, the piston 112 is pulled so that the piston 112 will not be ejected from the cylinder 111 .

Please refer to FIG. 5 . FIG. 5 is a schematic structural diagram of an embodiment of the multi-rotor UAV 12 in FIG. 3 . As shown in FIG. 5 , the multi-rotor UAV 12 includes a fuselage 121 , an arm mount 122 and a warhead 123 .

The fuselage 121 forms the upper part of the multi-rotor drone 12, and the fuselage 121 is provided with a positioning antenna 1211, a double-fold communication antenna 1212, a circuit board (not shown) and a battery (not shown). The circuit board includes: flight control board, communication board, mission computer, power board and ESC board. Understandably, the battery is a rechargeable battery. The positioning antenna 1211 is an RTK antenna.

The arm mount 122 forms the middle part of the multi-rotor UAV, and the arm mount is provided with a plurality of arms 1221 , and each arm is provided with a motor 1222 and a propeller 1223 .

The warhead 123 forms the lower part of the multi-rotor drone. Preferably, the combat part 123 is a self-forging fragment forming combat part.

Wherein, the lower part of the warhead 123 is provided with a plurality of sensors, and the types of the plurality of sensors include: radar, optical camera and laser range finder. When a preset target is detected by the multiple sensors, the warhead 123 is activated to explode and strike the target. Specifically, the images collected by the multiple sensors are transmitted to the background of the ground station through the wireless communication module, and the background of the ground station analyzes the collected images to determine whether to start the explosion of the warhead 123 .

It should be noted here that, as shown in Figure 4, the top of the piston 112 is provided with a USB pin 1121, and the combat part 123 is provided with a slot (not shown) matching the USB pin 1121, and the combat part 123 passes through The USB pin is electrically connected to the piston 112 . Understandably, the gas generator 113 is powered through the USB pin.

In addition, the folding multi-rotor UAV also includes a remote control device (not shown in the figure), which is used to control the flight of the multi-rotor UAV 12 and start the explosion of the warhead 123 .

The working process of the folding multi-rotor UAV of the present invention is:

Operate the remote control device to issue a take-off command, start the gas generator 113 to generate gas, and the gas pushes the piston 112 to move upward, so that the multi-rotor UAV 12 is launched from the barrel 111 . After the multi-rotor UAV 12 is launched from the barrel 111, multiple arms are opened to officially take off. Continue to operate the remote control device to make the remote control device fly to the preset combat position. After arriving at the destination, multiple sensors under the warhead 123 work to collect target images, and the target images are transmitted to the background of the ground station through the wireless communication module, and the background of the ground station analyzes the target images to determine whether the destination is a strike target When it is confirmed that it is the strike target, the remote control device is operated to send a combat command, and the warhead 123 is started to explode to strike the target. Of course, in other embodiments, it can also be set that after the multi-rotor UAV 12 arrives at the destination, the warhead 123 is activated to explode.

Finally, it should be noted that the folding multi-rotor UAV of the present invention is a one-time-use equipment, and after the multi-rotor UAV 112 is launched from the barrel 111, the barrel 111 is discarded. After the warhead 123 explodes, the multi-rotor UAV 112 is also destroyed.

The above is a specific description of the preferred implementation of the present invention, but the invention is not limited to the described embodiments, those skilled in the art can also make various equivalent deformations or replacements without violating the spirit of the present invention , these equivalent modifications or replacements are all within the scope defined by the claims of the present application.

Claims (9)

1. A folding multi-rotor unmanned aerial vehicle, is characterized in that, comprises: A multi-rotor drone, the arms of the multi-rotor drone have two states: open and folded; Launching part, the launching part includes a cylinder, when the multi-rotor UAV is not taking off, the multi-rotor UAV is folded and folded in the cylinder, and a piston and a gas generator are also arranged in the cylinder , the top of the piston is in contact with the multi-rotor UAV, the bottom of the piston is provided with the gas generator, and the gas generator generates gas after electric ignition, and the gas pushes the piston to move upward, Thus, the multi-rotor UAV is launched from the cylinder, and the multi-rotor UAV is taken off. 2. The folding multi-rotor UAV according to claim 1, wherein the multi-rotor UAV comprises: a warhead forming the lower portion of the multi-rotor UAV; Machine arm mount, described machine arm mount forms the middle part of described multi-rotor UAV, and described machine arm mount is provided with a plurality of described machine arms, and each described machine arm is all provided with a motor and a propeller; A fuselage, the fuselage forms the upper part of the multi-rotor UAV, and the fuselage is provided with a positioning antenna, a double-folding communication antenna, a circuit board and a battery. 3. The folding multi-rotor UAV according to claim 2, wherein the warhead is a warhead formed from self-forging fragments. 4. The folding multi-rotor UAV according to claim 2, wherein the circuit board comprises: a flight control board, a communication board, a mission computer, a power board and an electric regulator board. 5. The folding multi-rotor drone according to claim 2, wherein the top of the piston is provided with a USB pin, and the warhead is provided with a slot matching the USB pin, and the The warhead is electrically connected and installed on the piston through the USB pin. 6. The folding multi-rotor UAV according to claim 2, wherein the bottom of the warhead is provided with a plurality of sensors, and the type of the sensors includes at least one of the following: radar, optical camera or laser measuring Tachymeter. 7. The folding multi-rotor UAV according to claim 1, wherein the cylinder is provided with a base, the base is arranged on the bottom of the cylinder, the base is provided with a limit guide post, the The piston is arranged on the base through the limit guide post. 8. The folding multi-rotor UAV according to claim 7, wherein a wire rope is arranged between the base and the piston, one end of the wire rope is arranged on the base, and the other end of the wire rope One end is arranged on the piston, and the steel wire rope is used for pulling the piston when the piston is pushed upwards in the cylinder so that the piston cannot be ejected from the cylinder. 9. The folding multi-rotor UAV according to any one of claims 1 to 8, further comprising: A remote control device, the remote control device is used to control the flight of the multi-rotor UAV and start the explosion of the warhead.

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