CN108263603B

CN108263603B - Four rotor unmanned aerial vehicle take-off power-assisted devices

Info

Publication number: CN108263603B
Application number: CN201810070817.4A
Authority: CN
Inventors: 杨曙铭
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-01-25
Filing date: 2018-01-25
Publication date: 2020-12-01
Anticipated expiration: 2038-01-25
Also published as: CN108263603A

Abstract

The invention discloses a take-off power-assisted device of a quad-rotor unmanned aerial vehicle, which comprises a shell, wherein the top of an inner cavity of the shell is fixedly connected with a pressure box, the center of the top of the pressure box is communicated with a liquid injection pipe, the top end of the liquid injection pipe penetrates through the top of the shell and extends to the upper part of the shell, the top end of the liquid injection pipe is communicated with a liquid injection nozzle, the inside of the liquid injection nozzle is fixedly connected with a liquid leakage plate, the top of the liquid leakage plate is fixedly connected with a first spring, and the inside of the liquid injection nozzle and the top end of the first spring are movably connected with a sealing. This four rotor unmanned aerial vehicle take off power-assisted device utilizes the atmospheric pressure in the pressure case to push down the piston, and then utilizes the depression bar top to move the elastic plate center and make it sunken, and the horizontal width of elastic plate diminishes the back can't block the fixture block, and then the elasticity of usable second spring pops out first leg downwards, and then utilizes the reaction force on ground can make unmanned aerial vehicle bounce, and then reaches the effect for taking off the helping hand, makes unmanned aerial vehicle take off more easily.

Description

Four rotor unmanned aerial vehicle take-off power-assisted devices

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a take-off power assisting device of a quad-rotor unmanned aerial vehicle.

Background

An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is the real rigidity requirement of the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology. With the gradual maturity of unmanned aerial vehicle technology, manufacturing cost and entry thresholds are reduced, the consumer-grade unmanned aerial vehicle market has exploded, while the civilian unmanned aerial vehicle market is in the early night of the explosion. The related technology of the domestic and foreign unmanned aerial vehicles is rapidly developed, and the unmanned aerial vehicle has the characteristics of various types and wide application, so that the unmanned aerial vehicle has great differences in various aspects such as size, quality, range, time of flight, flight height, flight speed, tasks and the like. Due to the diversity of drones, there are different classification methods for different considerations: according to the classification of flight platform configuration, unmanned aerial vehicle can divide into fixed wing unmanned aerial vehicle, rotor unmanned aerial vehicle, unmanned dirigible, umbrella wing unmanned aerial vehicle, flapping wing unmanned aerial vehicle etc.. Categorised according to the usage, unmanned aerial vehicle can be divided into for military use unmanned aerial vehicle and civilian unmanned aerial vehicle.

The existing unmanned aerial vehicle usually takes off and is placed on the ground, but because of the height is lower, the unmanned aerial vehicle can not take off easily, and when weeds exist on the ground, the unmanned aerial vehicle takes off insecurely, and the wings are easy to hinge to the weeds to cause damage, so that the unmanned aerial vehicle takes off and is greatly influenced by the environment.

Disclosure of Invention

Technical problem to be solved

Aiming at the defects of the prior art, the invention provides a take-off assisting device for a quad-rotor unmanned aerial vehicle, which solves the problems that a man and a machine cannot take off easily due to low height, and when weeds exist on the ground, the take-off of the unmanned aerial vehicle is unsafe, and the wings are easy to hinge to the weeds to cause damage.

(II) technical scheme

In order to achieve the purpose, the invention is realized by the following technical scheme: a four-rotor unmanned aerial vehicle take-off power-assisted device comprises a shell, wherein a pressure box is fixedly connected to the top of an inner cavity of the shell, a liquid injection pipe is communicated with the center of the top of the pressure box, the top end of the liquid injection pipe penetrates through the top of the shell and extends to the upper side of the shell, a liquid injection nozzle is communicated with the top end of the liquid injection pipe, a liquid leakage plate is fixedly connected to the inside of the liquid injection nozzle, a first spring is fixedly connected to the top of the liquid leakage plate, a sealing ball is movably connected to the inside of the liquid injection nozzle and positioned at the top end of the first spring, a piston is slidably connected to the inside of the pressure box, a pressure rod is fixedly connected to the bottom of the piston, the bottom end of the pressure rod penetrates through the bottom of the pressure box and extends to the lower side of the pressure box, a first support column is fixedly connected to the bottom of the inner cavity of the shell, a second support column is, the bottom of the shell is penetrated with a first supporting leg, the first supporting leg is close to one side of the elastic plate and is located above the elastic plate, a clamping block is fixedly connected to the top end of the first supporting leg, a second spring is fixedly connected to the top end of the first supporting leg through a spring groove, the top end of the second spring is fixedly connected to the bottom of the pressure box, a guide pillar is fixedly connected to the bottom of the pressure box, and the second spring is sleeved on the surface of the guide pillar.

Preferably, one side of the first support leg close to the center of the shell is fixedly connected with an air nozzle, and the bottom of one side of the pressure box is communicated with an exhaust hose.

Preferably, the bottom end of the exhaust hose penetrates through the bottom of the housing and extends to the top of the air nozzle, and the bottom end of the exhaust hose is communicated with the top of the air nozzle.

Preferably, the bottom of first landing leg rotates and is connected with the second landing leg, and the bottom fixedly connected with supporting legs of second landing leg, one side fixedly connected with magnet that the air nozzle was kept away from to the second landing leg, the bottom fixedly connected with electro-magnet of casing.

Preferably, the top of the shell is fixedly connected with a control box, the control box is sleeved outside the liquid injection pipe, and the top of the control box is fixedly connected with a solar cell panel.

Preferably, the top of the shell is located inside the control box and is fixedly connected with the storage battery and the controller from left to right in sequence, and the center of the bottom of the shell is fixedly connected with the wireless receiver.

Preferably, the side wall of the inner cavity of the shell is fixedly connected with a power device, and a heating rod is fixedly connected between the left inner wall and the right inner wall of the pressure box and above the piston.

Preferably, the outer surface of the shell is fixedly connected with a support, and one end, far away from the shell, of the support is rotatably connected with a wing.

(III) advantageous effects

The invention provides a take-off power assisting device of a quad-rotor unmanned aerial vehicle. The method has the following beneficial effects:

(1) the four-rotor unmanned aerial vehicle take-off power-assisted device is characterized in that a piston is connected in a sliding manner in a pressure box, the bottom of the piston is fixedly connected with a pressure rod, the bottom end of the pressure rod penetrates through the bottom of the pressure box and extends to the lower part of the pressure box, the bottom of an inner cavity of a shell is fixedly connected with a first supporting column, the bottom of the pressure box is fixedly connected with a second supporting column, an elastic plate is movably connected between the first supporting column and the second supporting column, a first supporting leg penetrates through the bottom of the shell, the first supporting leg is close to one side of the elastic plate and is fixedly connected with a clamping block above the elastic plate, the top end of the first supporting leg is fixedly connected with a second spring through a spring groove, the top end of the second spring is fixedly connected with the bottom of the pressure box, the bottom of the pressure box is fixedly connected with the guide column, the second spring is sleeved on the surface of, and then utilize the depression bar to push up and move the elastic plate center and make it sunken, can't block the fixture block after the elastic plate transverse width diminishes, and then the elasticity of usable second spring pops out first leg downwards, and then utilizes the reaction force on ground can make unmanned aerial vehicle bounce, and then reaches the effect for taking off the helping hand, makes unmanned aerial vehicle take off more easily.

(2) This four rotor unmanned aerial vehicle take off and help device, top fixedly connected with heating rod through between the inner wall about the pressure cell and be located the piston, one side fixedly connected with air nozzle that first leg is close to the casing center, the bottom intercommunication of one side of pressure cell has exhaust hose, exhaust hose's bottom runs through the bottom of casing and extends to the top of air nozzle, and exhaust hose's bottom and air nozzle's top intercommunication, utilize the heating rod can make the liquid in the pressure cell volatilize rapidly, and then atmospheric pressure in the increase pressure cell, finally arrange the air nozzle through exhaust hose in to ground blowout high velocity air, the reaction force on same usable ground is unmanned aerial vehicle helping hand that takes off, can use repeatedly, it is simple high-efficient.

(3) This four rotor unmanned aerial vehicle take off and assist device, bottom through at first landing leg is rotated and is connected with the second landing leg, and the bottom fixedly connected with supporting legs of second landing leg, one side fixedly connected with magnet of air nozzle is kept away from to the second landing leg, the bottom fixedly connected with electro-magnet of casing, it is rotatable between second landing leg and the first landing leg, utilize the cooperation between magnet and the electro-magnet, can pack up the second landing leg when unmanned aerial vehicle flies, can reduce the resistance, also can avoid colluding branch electric wire etc, also can launch the second landing leg simultaneously, can use it to support, and utilize the repulsion force between electro-magnet and the electro-magnet, can cushion unmanned aerial vehicle descending, avoid damaging unmanned aerial vehicle.

(4) This four rotor unmanned aerial vehicle take off and help device, center intercommunication through at the pressure cell top has annotates the liquid pipe, the top of annotating the liquid pipe runs through the top of casing and extends to the top of casing, and the top intercommunication of annotating the liquid pipe has annotates the liquid mouth, the inside fixedly connected with weeping board of annotating the liquid mouth, the first spring of top fixedly connected with of weeping board, the inside of annotating the liquid mouth and the top swing joint who is located first spring have the ball sealer, utilize the cooperation of first spring and ball sealer, can push down the ball sealer when injecting the liquid ware, can pour into liquid smoothly, and loosen the back, the usable elasticity of first spring makes the ball sealer plug up the inlet, avoid liquid or gaseous leakage, can keep the interior sustainable increase of pressure cell, guarantee for the operation of device, and is simple in structure practical.

(5) This four rotor unmanned aerial vehicle take off power-assisted device, through the top fixedly connected with solar cell panel at the control box, the top of casing and the inside that is located the control box from left to right fixedly connected with battery and controller in proper order utilize solar cell panel to turn into solar energy the electric energy and store, and energy-concerving and environment-protective, and can improve unmanned aerial vehicle's duration.

Drawings

FIG. 1 is a schematic view of the internal structure of the present invention;

FIG. 2 is a schematic view of the internal structure of the pouring spout and the pouring nozzle of the present invention;

FIG. 3 is a top view of the appearance structure of the present invention;

in the figure, 1-shell, 2-pressure box, 3-liquid injection pipe, 4-liquid injection nozzle, 5-liquid leakage plate, 6-first spring, 7-sealing ball, 8-piston, 9-pressure rod, 10-first support column, 11-second support column, 12-elastic plate, 13-first support leg, 14-fixture block, 15-second spring, 16-guide column, 17-air nozzle, 18-exhaust hose, 19-second support leg, 20-support leg, 21-magnet, 22-electromagnet, 23-control box, 24-solar panel, 25-storage battery, 26-controller, 27-power device, 28-heating rod, 29-support and 30-wing.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1-3, an embodiment of the present invention provides a technical solution: a take-off power-assisted device of a quad-rotor unmanned aerial vehicle comprises a shell 1, wherein the top of the shell 1 is fixedly connected with a control box 23, the control box 23 is sleeved outside a liquid injection pipe 3, the top of the control box 23 is fixedly connected with a solar cell panel 24, the top of the shell 1 and the inside of the control box 23 are sequentially and fixedly connected with a storage battery 25 and a controller 26 from left to right, the solar cell panel 24 can convert solar energy into electric energy for storage, the energy is saved, the environment is protected, the cruising ability of the unmanned aerial vehicle can be improved, a wireless receiver 31 is fixedly connected to the center of the bottom of the shell 1, a power device 27 is fixedly connected to the side wall of the inner cavity of the shell 1, a heating rod 28 is fixedly connected between the left inner wall and the right inner wall of a pressure box 2 and above a piston 8, a bracket 29 is fixedly connected, the top of the inner cavity of the shell 1 is fixedly connected with a pressure box 2, the boiling point of the liquid injected into the pressure box 2 is smaller but higher than the outside temperature, so that the liquid can be volatilized rapidly, the center of the top of the pressure box 2 is communicated with a liquid injection pipe 3, the top end of the liquid injection pipe 3 penetrates through the top of the shell 1 and extends to the upper part of the shell 1, the top end of the liquid injection pipe 3 is communicated with a liquid injection nozzle 4, the inside of the liquid injection nozzle 4 is fixedly connected with a liquid leakage plate 5, the top of the liquid leakage plate 5 is fixedly connected with a first spring 6, the inside of the liquid injection nozzle 4 and the top end of the first spring 6 are movably connected with a sealing ball 7, the sealing ball 7 can be pressed down when the liquid injector is inserted by utilizing the matching of the first spring 6 and the sealing ball 7, so that the liquid can be injected smoothly, after the liquid is loosened, the sealing ball 7 can be blocked by utilizing the elasticity of the first spring, the device is simple and practical in structure, the piston 8 is connected in the pressure box 2 in a sliding manner, the bottom of the piston 8 is fixedly connected with a pressure rod 9, the bottom end of the pressure rod 9 penetrates through the bottom of the pressure box 2 and extends to the lower part of the pressure box 2, the bottom of the inner cavity of the shell 1 is fixedly connected with a first support column 10, the bottom of the pressure box 2 is fixedly connected with a second support column 11, an elastic plate 12 is movably connected between the first support column 10 and the second support column 11, a first support leg 13 penetrates through the bottom of the shell 1, an air nozzle 17 is fixedly connected to one side of the first support leg 13, which is close to the center of the shell 1, the bottom of one side of the pressure box 2 is communicated with an exhaust hose 18, when the piston 8 moves to the lowest part, air can be exhausted through the exhaust hose 18, the bottom end of the exhaust hose 18 penetrates through the bottom of the shell 1 and extends to the top of the air nozzle 17, and the bottom end of the exhaust, the liquid in the pressure box 2 can be rapidly volatilized by utilizing the heating rod 28, so that the air pressure in the pressure box 2 is increased, the liquid is finally discharged into the air nozzle 17 through the exhaust hose 18 and is sprayed to the ground, the reaction force of the ground can be used as the takeoff assisting force of the unmanned aerial vehicle, the unmanned aerial vehicle can be used repeatedly, the pressure box is simple and efficient, the bottom end of the first supporting leg 13 is rotatably connected with the second supporting leg 19, the bottom of the second supporting leg 19 is fixedly connected with the supporting leg 20, one side, far away from the air nozzle 17, of the second supporting leg 19 is fixedly connected with the magnet 21, the bottom of the shell 1 is fixedly connected with the electromagnet 22, the second supporting leg 19 and the first supporting leg 13 can rotate, the second supporting leg 19 can be folded when the unmanned aerial vehicle flies by utilizing the matching between the magnet 21 and the electromagnet 22, the resistance can be reduced, the hooking of branch electric wires and the like can be avoided, meanwhile, the second supporting, can cushion the unmanned aerial vehicle descending, avoid haring unmanned aerial vehicle, first landing leg 13 is close to one side of elastic plate 12 and is located the top fixedly connected with fixture block 14 of elastic plate 12, spring groove fixedly connected with second spring 15 is passed through on the top of first landing leg 13, and the top of second spring 15 and the bottom fixed connection of pressure cell 2, bottom fixed connection guide pillar 16 of pressure cell 2, and the surface at guide pillar 16 is established to 15 covers of second spring, utilize the atmospheric pressure in the pressure cell 2 to push down piston 8, and then utilize depression bar 9 to push up the center of elastic plate 12 and make it sunken, can't block fixture block 14 after the transverse width of elastic plate 12 diminishes, and then the elasticity of usable second spring 15 pops out first landing leg 13 downwards, and then utilize the reaction force on ground can make unmanned aerial vehicle bounce, and then reach the effect for taking off helping hand, make unmanned aerial vehicle take off easier.

When the device is used, the electromagnet 22 is electrified, the second supporting leg 19 is unfolded by utilizing the repulsive force of the electromagnet 22 and the magnet 21, the unmanned aerial vehicle is placed on the ground, the liquid injector is inserted into the liquid injection nozzle 4, the sealing ball 7 is pressed downwards, liquid is extruded into the liquid injection nozzle 4, then the liquid flows into the pressure box 2 through the liquid leakage plate 5, then the liquid injector is pulled out, the sealing ball 7 is pushed upwards by utilizing the elastic force of the first spring 6, the liquid inlet is blocked by the sealing ball 7, then the controller 26 is remotely controlled to control the heating rod 28 to heat the liquid, the liquid is rapidly volatilized, the internal pressure of the pressure box 2 is increased, the piston 8 is pushed downwards, the pressure rod 9 is driven to descend, the bottom end of the pressure rod 9 presses the center of the elastic plate 12 to enable the elastic plate 12 to be sunken, when the piston 8 moves to the bottom of the inner cavity of the pressure box 2, the transverse width of the elastic plate 12 is minimized, the fixture block 14 is separated from the elastic plate 12, first landing leg 13 pops out downwards, bounces unmanned aerial vehicle, and simultaneously pressure reaches the biggest in the pressure cell 2 to in exhausting air nozzle 17 from exhaust hose 18, again to ground blowout high velocity air, utilize thrust to make unmanned aerial vehicle rise the certain distance once more, control power device 27 simultaneously starts, wing 30 rotates and makes unmanned aerial vehicle fly up, then leads to reverse current for electro-magnet 22, electro-magnet 22 and magnet 21 adsorb each other, pack up second landing leg 19.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a four rotor unmanned aerial vehicle take-off power-assisted device, includes casing (1), its characterized in that: the top of the inner cavity of the shell (1) is fixedly connected with a pressure box (2), the center of the top of the pressure box (2) is communicated with a liquid injection pipe (3), the top end of the liquid injection pipe (3) penetrates through the top of the shell (1) and extends to the upper part of the shell (1), the top end of the liquid injection pipe (3) is communicated with a liquid injection nozzle (4), the inside of the liquid injection nozzle (4) is fixedly connected with a liquid leakage plate (5), the top of the liquid leakage plate (5) is fixedly connected with a first spring (6), the inside of the liquid injection nozzle (4) and the top end of the first spring (6) are movably connected with a sealing ball (7), the inside of the pressure box (2) is slidably connected with a piston (8), the bottom of the piston (8) is fixedly connected with a pressure rod (9), the bottom end of the pressure rod (9) penetrates through the bottom of the pressure box (2) and extends to the lower part of, the bottom fixedly connected with first support column (10) of casing (1) inner chamber, the bottom fixedly connected with second support column (11) of pressure cell (2), and swing joint has elastic plate (12) between first support column (10) and second support column (11), first landing leg (13) have been run through to the bottom of casing (1), first landing leg (13) are close to one side of elastic plate (12) and are located the top fixedly connected with fixture block (14) of elastic plate (12), the top of first landing leg (13) is through spring groove fixedly connected with second spring (15), and the top of second spring (15) and the bottom fixed connection of pressure cell (2), the bottom fixed connection guide pillar (16) of pressure cell (2), and the surface at guide pillar (16) is established to second spring (15) cover.

2. A take-off power-assisted device for a quad-rotor unmanned aerial vehicle as claimed in claim 1, wherein: an air nozzle (17) is fixedly connected to one side, close to the center of the shell (1), of the first supporting leg (13), and an exhaust hose (18) is communicated with the bottom of one side of the pressure box (2).

3. A take-off power-assisted device for a quad-rotor unmanned aerial vehicle as claimed in claim 2, wherein: the bottom end of the exhaust hose (18) penetrates through the bottom of the shell (1) and extends to the top of the air nozzle (17), and the bottom end of the exhaust hose (18) is communicated with the top of the air nozzle (17).

4. A take-off power-assisted device for a quad-rotor unmanned aerial vehicle as claimed in claim 1, wherein: the bottom of first landing leg (13) is rotated and is connected with second landing leg (19), and the bottom fixedly connected with supporting legs (20) of second landing leg (19), one side fixedly connected with magnet (21) of air nozzle (17) are kept away from in second landing leg (19), the bottom fixedly connected with electro-magnet (22) of casing (1).

5. A take-off power-assisted device for a quad-rotor unmanned aerial vehicle as claimed in claim 1, wherein: the top fixedly connected with control box (23) of casing (1), and control box (23) cover is established in the outside of annotating liquid pipe (3), the top fixedly connected with solar cell panel (24) of control box (23).

6. A take-off power-assisted device for a quad-rotor unmanned aerial vehicle as claimed in claim 1, wherein: the top of casing (1) just is located the inside of control box (23) and from left to right fixedly connected with battery (25) and controller (26) in proper order, the center fixedly connected with wireless receiver (31) of casing (1) bottom.

7. A take-off power-assisted device for a quad-rotor unmanned aerial vehicle as claimed in claim 1, wherein: the lateral wall fixed connection of casing (1) inner chamber has power device (27), between the inner wall about pressure cell (2) and be located the top fixedly connected with heating rod (28) of piston (8).

8. A take-off power-assisted device for a quad-rotor unmanned aerial vehicle as claimed in claim 1, wherein: the outer surface of the shell (1) is fixedly connected with a support (29), and one end, far away from the shell (1), of the support (29) is rotatably connected with a wing (30).