CN215436916U

CN215436916U - Multi-rotor unmanned aerial vehicle

Info

Publication number: CN215436916U
Application number: CN202120373627.7U
Authority: CN
Inventors: 郄新越
Original assignee: Beijing Jingdong Qianshi Technology Co Ltd
Current assignee: Beijing Jingdong Qianshi Technology Co Ltd
Priority date: 2021-02-10
Filing date: 2021-02-10
Publication date: 2022-01-07
Anticipated expiration: 2031-02-10

Abstract

The utility model provides a multi-rotor unmanned aerial vehicle, which comprises an unmanned aerial vehicle main body, rotors, a rotating part, a transmission mechanism and an air injection device, wherein the unmanned aerial vehicle main body comprises a vehicle body and a support structure positioned on the peripheral side of the vehicle body; the rotor wing is connected with the fuselage through a supporting structure and used for providing lift force for the multi-rotor unmanned aerial vehicle; the rotating part is connected with the machine body; the transmission mechanism is connected with the rotating part and the rotor wing so as to drive the rotor wing to rotate through the transmission mechanism when the rotating part rotates; the air injection device is used for injecting compressed air, and the air injection device is configured to inject the compressed air to drive the rotating part to rotate and drive the rotor wing to rotate.

Description

Multi-rotor unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned vehicles technical field, more specifically relates to a many rotor unmanned aerial vehicle.

Background

Unmanned aerial vehicle's application in daily life is more and more common, and unmanned aerial vehicle in the existing market mostly all is the unmanned aerial vehicle through battery charging drive or other fuel drive's rotor structure, and battery drive's unmanned aerial vehicle adopts the lithium cell to supply power mostly, and it charges and need consume the longer time, but battery duration is shorter relatively, and this type of unmanned aerial vehicle's carrying capacity is more weak simultaneously. Unmanned aerial vehicle of other fuel drive consumes fuel in the flight process, produces a large amount of greenhouse gases or other harmful gases to the environment, causes environmental pollution easily.

In implementing the disclosed concept, the inventors found that there are at least the following problems in the related art:

through electric power or fuel drive unmanned aerial vehicle flight among the prior art, and current electric drive's unmanned aerial vehicle has the time of endurance short, the weak problem of carrying capacity, and current fuel drive's unmanned aerial vehicle produces harmful substance to the environment easily, causes environmental pollution's problem.

SUMMERY OF THE UTILITY MODEL

In view of this, the present disclosure provides a many rotor unmanned aerial vehicle, includes: the unmanned aerial vehicle comprises an unmanned aerial vehicle main body, a control system and a control system, wherein the unmanned aerial vehicle main body comprises a body and a support structure positioned on the periphery of the body; the rotor wing is connected with the fuselage through the supporting structure and is used for providing lift force for the multi-rotor unmanned aerial vehicle; a rotating member connected with the body; the transmission mechanism is connected with the rotating component and the rotor wing so as to drive the rotor wing to rotate through the transmission mechanism when the rotating component rotates; and the air injection device is used for injecting compressed air and is configured to inject the compressed air to drive the rotating part to rotate and drive the rotor wing to rotate.

According to an embodiment of the present disclosure, the gas injection device includes: a nozzle provided in a region of an orthogonal projection of a rotation circular surface of the rotating member, the nozzle being disposed so as to face the rotating member and configured to eject the compressed gas to rotationally drive the rotating member; a pressure vessel adapted to contain the compressed gas, the pressure vessel in communication with the nozzle; and the electric control gas injection valve is configured to control the opening of the nozzle so as to control the flow and the speed of the compressed gas.

According to an embodiment of the present disclosure, rotary part sets up in the bottom of unmanned aerial vehicle main part and is close to the nozzle tip, rotary part has a plurality of blades.

According to the embodiment of the present disclosure, the nozzle is disposed in a region of the bottom of the main body of the drone opposite to the rotating part.

According to this disclosed embodiment, rotary part pass through the main rotating shaft rotationally install in unmanned aerial vehicle main part bottom, rotary part drives when rotating main rotating shaft rotates.

According to the embodiment of the present disclosure, one end of the transmission mechanism is connected with the main rotating shaft, the other end of the transmission mechanism is connected with the rotor wing, and the main rotating shaft drives the rotor wing to rotate through the transmission mechanism when rotating.

According to an embodiment of the present disclosure, the transmission mechanism includes at least one of a transmission shaft, a transmission chain, and a transmission belt.

According to an embodiment of the present disclosure, the multi-rotor drone further comprises: a pitch device configured to control a pitch of the rotor.

According to the embodiment of the disclosure, the pitch-variable device is provided with a steering engine, and the steering engine is connected with the blades of the rotor wing through a connecting rod; the steering engine is configured to control an angle of attack of the blade via a linkage to adjust a pitch of the rotor.

According to an embodiment of the present disclosure, the multi-rotor drone further comprises: an air compression device configured to communicate with the pressure vessel for charging the air jet device with compressed air.

According to an embodiment of the present disclosure, the multi-rotor drone further comprises: control module, its with jet-propelled device, rotor, rotary part, displacement means communication connection, control module receives control command and is based on control command control many rotor unmanned aerial vehicle's flight status.

According to this disclosed embodiment, through setting up pressure vessel and with the nozzle of pressure vessel intercommunication to through following nozzle spun compressed gas drive part is rotatory, and rotary part passes through drive mechanism and drives the rotor is rotatory, thereby does many rotor unmanned aerial vehicle provide lift. Based on this scheme, unmanned aerial vehicle's power derives from the nozzle spun compressed air from air jet system, can provide bigger lift for unmanned aerial vehicle, avoids producing the problem of waste gas through nozzle spun compressed air simultaneously, consequently can realize improving unmanned aerial vehicle's carrying capacity and avoid environmental pollution's technological effect.

Drawings

The above and other objects, features and advantages of the present disclosure will become more apparent from the following description of embodiments of the present disclosure with reference to the accompanying drawings, in which:

fig. 1 schematically illustrates an exemplary application scenario in which a multi-rotor drone may be applied in accordance with an embodiment of the present disclosure;

fig. 2 schematically illustrates a bottom view structural schematic of a multi-rotor drone according to an embodiment of the present disclosure;

fig. 3 schematically illustrates a side view structural schematic of a multi-rotor drone according to an embodiment of the present disclosure.

Detailed Description

Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. It should be understood that the description is illustrative only and is not intended to limit the scope of the present disclosure. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present disclosure.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.

All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.

Where a convention analogous to "A, B or at least one of C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B or C" would include but not be limited to systems that have a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.).

The embodiment of the disclosure provides a multi-rotor unmanned aerial vehicle, which comprises an unmanned aerial vehicle main body and an air injection device, wherein a plurality of rotors are arranged on the periphery of the unmanned aerial vehicle main body. The air injection device is used for injecting compressed air and is configured to inject the compressed air to drive the plurality of rotary wings to rotate. Wherein, for many rotor unmanned aerial vehicle provide lift when jet system blowout compressed gas and/or rotor rotate.

Fig. 1 schematically illustrates an exemplary application scenario in which a multi-rotor drone may be applied according to an embodiment of the present disclosure. It should be noted that fig. 1 is only an example of an application scenario in which the embodiments of the present disclosure may be applied to help those skilled in the art understand the technical content of the present disclosure, but does not mean that the embodiments of the present disclosure may not be used in other environments or scenarios.

As shown in fig. 1 (a), the multi-rotor drone of the embodiment of the present disclosure may be applied to, for example, logistics transportation, i.e., as a multi-rotor drone for transportation. The multi-rotor unmanned aerial vehicle for transportation can transport the articles at one delivery point to other places according to a set route, for example, the articles at the place A are respectively transported to the place B by a plurality of logistics unmanned aerial vehicles, and the logistics unmanned aerial vehicles can transport one or more articles at a time.

As shown in fig. 1 (b), the multi-rotor drone of the embodiment of the present disclosure may also be applied to data monitoring, i.e., a multi-rotor drone for monitoring, for example. The multi-rotor unmanned aerial vehicle for monitoring can take off from the starting point C, fly to the target site D, collect and monitor data of the target site D, and feed back the collected or monitored data to a collector.

Fig. 2 and 3 schematically illustrate a multi-rotor drone according to an embodiment of the present disclosure, it should be noted that fig. 1 is only an example of a multi-rotor drone to which the embodiment of the present disclosure may be applied to help those skilled in the art understand the technical content of the present disclosure, but it is not meant that the embodiment of the present disclosure defines a specific shape of the multi-rotor drone.

With reference to fig. 2 and 3, a multi-rotor drone according to an embodiment of the present disclosure includes: unmanned aerial vehicle main part 11, rotor 12, rotary part 14, drive mechanism 15 and jet system 13. The drone body 11 includes a fuselage 111 and a support structure 112 located on the periphery side of the fuselage. The rotor 12 is connected to the fuselage 111 via a support structure 112, and the rotor 12 may be provided in plurality. The rotary member 14 is connected to the body 111. The transmission mechanism 15 is connected to the rotary member 14 and the rotor 12 so that the rotor 12 is rotated by the transmission mechanism 15 when the rotary member 14 rotates. Pack compressed gas in gas jet equipment 13, drive rotary part 14 when gas jet equipment 13 blowout compressed gas rotates to transmit power to a plurality of rotors 12 by rotary part 14 via drive mechanism 15, rotate in order to drive a plurality of rotors 12, make many rotor unmanned aerial vehicle obtain lift that rises.

The rotor 12 may be, for example, a propeller having a plurality of blades mounted on a rotating shaft of the rotor that drives the blades to rotate, providing lift for a multi-rotor drone. The rotors 12 of the multi-rotor drone may be provided, for example, in 4 numbers, which are symmetrically provided on the peripheral side of the multi-rotor drone through the support structure 112. In other embodiments of the present disclosure, the number of rotors 12 may be set to 6, 8, or 10, etc., and the number may be adjusted according to the specific requirements of the user. The rotor 12 provides lift to the multi-rotor drone when driven in rotation by the jet 13.

The compressed gas ejected from the gas ejecting device 13 may be, for example, air, and after the compressed gas is ejected, no harmful gas is generated, that is, no problem of environmental pollution is caused.

According to the embodiment of this disclosure, gas jet system 13 can for example provide lift for many rotor unmanned aerial vehicle alone, and gas jet system 13 is through spouting compressed gas at a high speed to form the thrust against gas jet system 13, further promote many rotor unmanned aerial vehicle motion. Jet-propelled device 13 also can be when the compressed gas of blowout, and it is rotatory to utilize compressed gas drive rotor 12, provides partly power for many rotor unmanned aerial vehicle when rotor 12 is rotatory, forms reaction force at the compressed gas of blowout from jet-propelled device 13 simultaneously, also provides partly power for many rotor unmanned aerial vehicle, provides lift for many rotor unmanned aerial vehicle jointly.

According to the embodiment of this disclosure, it provides a many rotor unmanned aerial vehicle adopts air jet system blowout compressed gas to utilize a plurality of rotors of spun compressed gas drive to rotate, provide lift for many rotor unmanned aerial vehicle, this drive mode is a brand-new drive mode. In addition, this compressed air can use the air to compress for example and obtain, compares and uses fuel driven unmanned aerial vehicle, and this many rotor unmanned aerial vehicle of this disclosure can not produce and produce poisonous and harmful substance to the environment, therefore can avoid environmental pollution's problem.

According to an embodiment of the present disclosure, the air injection device 13 has a nozzle 131, a pressure vessel 132, and an electrically controlled air injection valve (not shown). The nozzle 131 is provided in a region of the normal projection of the rotation circular surface of the rotating member 14, and the nozzle 131 is disposed so as to face the rotating member 14, and discharges the compressed gas to rotationally drive the rotating member 14 located on the downstream side of the compressed gas flow. For example, the nozzle 131 may be disposed at the bottom of the main body 11 of the drone, and when the compressed gas is ejected from the nozzle 131, the rotating member 14 is driven to rotate by the driving force. The pressure vessel 132 may be provided, for example, at a side of the main body 11 of the drone for containing compressed gas, and the pressure vessel 132 is in communication with the nozzle 131, such as may be through an air conduit 133. The electrically controlled gas injection valve is used for controlling the opening of the nozzle 131 to control the flow rate and speed of the compressed gas sprayed from the nozzle 131.

In this disclosed optional implementation, rotary part can set up at the fuselage top of unmanned aerial vehicle main part for example to the orthographic projection area of rotary part's the rotation disc is greater than the orthographic projection of the fuselage of unmanned aerial vehicle main part, and the nozzle setting is in one side of rotary part's the fuselage of keeping away from the unmanned aerial vehicle main part, so that the rotary part that makes nozzle spun compressed gas drive the downstream side that is located the compressed gas air current rotates, and then drives a plurality of rotors rotatory, provides lift for the unmanned aerial vehicle main part.

According to the embodiment of the present disclosure, the nozzle 131 is disposed at the bottom of the main body 111 of the drone body 11, and the direction of the compressed gas ejected therefrom is vertical and toward the ground, so as to generate an upward lift force for the multi-rotor drone. In other embodiments of the present disclosure, the compressed gas ejected from the nozzle 131 has a certain angle (for example, 30 °) with the vertical direction, and the component force of the gas ejected from the nozzle 131 in the vertical direction generates an upward lift force for the multi-rotor drone and also generates a component force in the horizontal direction, so that the multi-rotor drone can move in the horizontal direction.

The pressure vessel 132 communicates with the nozzle 131 to eject the compressed gas in the pressure vessel 132 from the nozzle 131. For example, the air guide duct 133 can be used for communication, and the pressure container and the nozzle can be arranged at different positions, so that the overall arrangement structure of the multi-rotor unmanned aerial vehicle is more reasonable; for another example, the pressure vessel 132 is directly connected to the nozzle 131, that is, the nozzle 131 is provided on the pressure vessel, and the compressed gas is directly discharged through the nozzle 131.

The electronically controlled gas injection valve controls the opening of the nozzle 131 to control the flow rate and velocity of the compressed gas ejection. For example, when the multi-rotor unmanned aerial vehicle needs to generate a large lift force, the electronically controlled gas injection valve receives a command of increasing the opening degree of the nozzle 131, and the opening degree of the nozzle 131 is enlarged, so that the flow rate of compressed gas ejected from the nozzle 131 is increased, or the ejection speed of the ejected compressed gas is increased, and thus the large lift force is generated; for another example, when the multi-rotor unmanned aerial vehicle needs a smaller lift force, the electronically controlled gas injection valve receives a command to decrease the opening degree of the nozzle 131, and decreases the opening degree of the nozzle 131, so that the flow rate of the compressed gas ejected from the nozzle 131 is decreased, or the ejection speed of the ejected compressed gas is decreased, thereby generating the smaller lift force. Through configuration automatically controlled gas injection valve, be favorable to realizing the accurate control to many rotor unmanned aerial vehicle flight state.

According to the embodiment of the present disclosure, the multi-rotor unmanned aerial vehicle further includes a rotating member 14, the rotating member 14 has a plurality of blades 141, the rotating member 14 may be disposed at the bottom of the main body 11 of the unmanned aerial vehicle and near the end of the nozzle 131, the compressed gas ejected from the nozzle 131 generates a driving force on the blades 141 to drive the rotating member 14 to rotate, the rotating member 14 is connected with the rotor 12 through a transmission mechanism 15, and the transmission mechanism is configured to drive the rotor 12 to rotate when the rotating member 14 rotates.

According to the embodiment of the present disclosure, for example, 4 blades 141 of the rotating member 14 may be provided, and the blades 141 are close to the end of the nozzle 131, after the compressed gas is ejected from the nozzle 131, the air around the blades 141 is disturbed, so as to promote the airflow around the blades 141 to flow, and the flowing airflow generates a force on the blades 141, so as to drive the rotating member 14 to rotate, and when the blades 141 move to a position where the end of the nozzle 131 is opposite, the ejected compressed gas further drives the rotating member to rotate at an accelerated speed. In the embodiment of the present disclosure, when the vane 141 of the rotating component 14 is installed or disposed, the surface of the vane 141 has a certain inclination with the flow direction of the gas flow ejected from the nozzle 131, so that the gas flow of the compressed gas ejected from the nozzle exerts a force on the vane, thereby driving the vane 141 to rotate. For example, when the air flow ejected from the nozzle 131 is in the vertical direction and directed toward the ground, and the vane 141 is driven by the turbulent air flow and rotated to the end of the nozzle 131, the air flow blowing on the vane 141 generates a horizontal component force to the vane 141, and the component force accelerates the vane 141, so that the rotating member 14 is accelerated by the vane 141 every time the vane 141 passes the end of the nozzle 131.

In other embodiments of the present disclosure, the number of the blades 141 of the rotating component 14 may be set to 6, 8, etc., and a larger number of the blades may increase the number of times that the blades are driven by the compressed gas when the blades rotate to the end of the nozzle, thereby effectively increasing the driving efficiency.

According to the embodiment of the present disclosure, the transmission mechanism 15 connects the rotor 12 and the rotary member 14, and after the rotary member 14 is driven to rotate by the compressed gas ejected from the nozzle 131, the transmission mechanism 15 transmits the rotation of the rotary member 14 to the rotor 12, thereby rotating the rotor 12. Also, the rotational speed of the rotor 12 can be adjusted by adjusting the rotational speed of the rotary member 14.

According to the embodiment of this disclosure, through utilizing drive mechanism 15 to transmit rotary part's power to the rotor, it can simplify many rotor unmanned aerial vehicle structure, improves power transmission efficiency. For example, rotary part 14 sets up to one, and four rotors that set up week side in unmanned aerial vehicle main part select for use same drive mechanism 15 to be connected with same rotary part 14 simultaneously, and rotary part 14 can drive four rotors simultaneously when rotating rotatory, adopts the same connected mode at rotary part 14 and drive mechanism junction, makes many rotor unmanned aerial vehicle's structure become simple, through adopting single connected mode, reduces the loss of power in transmission process, improves power transmission efficiency.

According to the embodiment of the present disclosure, the nozzle 131 is disposed in the area of the bottom of the drone body 11 that is opposite to the rotation circular surface of the rotating member 14. The blade 141 of the rotating member 14 constitutes a rotating circular surface of the rotating member 14 when rotating, and the nozzle 131 is disposed in a region of the bottom of the main body 11 of the drone that faces the rotating circular surface, and with this arrangement, the compressed gas discharged from the nozzle 131 can directly form a large driving force to the blade 141 of the rotating member 14, and further drive efficiency to the blade 141 is higher.

According to the embodiment of this disclosure, rotary part 14 rotationally installs in the bottom of unmanned aerial vehicle main part 11 through main rotation axis 16, and when rotary part 14 rotated, drive main rotation axis 16 and rotate.

For example, in order to facilitate the rotation of the rotating member 14, the main rotating shaft 16 and the main body 11 may be mounted via a bearing, so as to reduce the friction between the main rotating shaft 16 and the main body, and the main rotating shaft 16 may freely rotate relative to the main body. The rotary member 14 is fixedly connected to the main rotary shaft 16, and therefore, when the rotary member 14 is rotated by the compressed gas, the main rotary shaft 16 is rotated at the same time.

According to the embodiment of the present disclosure, the transmission mechanism 15 is configured such that one end is connected to the main rotating shaft 16 and the other end is connected to the rotor 12, and the main rotating shaft 16 rotates to drive the rotor 12 to rotate through the transmission mechanism. The transmission mechanism 15 is used to transmit the rotation of the main rotating shaft 16 to the rotor 12, thereby driving the rotation of the rotor 12. The rotational speed of the rotor 12 can be adjusted by adjusting the rotational speed of the main rotating shaft 16. By providing the transmission mechanism 15, the power transmission efficiency of the main rotating shaft 16 to the rotor 12 is improved.

According to an embodiment of the present disclosure, the transmission mechanism may include, for example, at least one of a transmission shaft, a transmission chain, and a transmission belt, among others. For example, when the transmission mechanism is set as a transmission shaft, two ends of the transmission shaft include first bevel gears, second bevel gears matched with the first bevel gears are respectively arranged on the main rotating shaft 16 and the rotor 12, the first bevel gears on the transmission shaft are driven to rotate when the second bevel gears on the main rotating shaft 16 rotate, the second bevel gears on the rotor 12 are further driven to rotate, the number of teeth of the second bevel gears on the main rotating shaft 16 and the second bevel gears on the rotor 12 can be adjusted according to actual rotating speed requirements, and the number of teeth can be the same or can be set to be different. For another example, when the transmission mechanism is a transmission chain, the main rotating shaft 16 is provided with a first sprocket, the rotor 12 is provided with a second sprocket, the transmission chain is respectively sleeved on the first sprocket and the second sprocket, and when the main rotating shaft 16 rotates, the first sprocket drives the second sprocket to rotate, and further drives the rotor 12 to rotate. For another example, when the transmission mechanism is set as a transmission belt, the main rotating shaft 16 is provided with a first belt pulley, the rotor 12 is provided with a second belt pulley, the transmission belt is sleeved on the first belt pulley and the second belt pulley, when the main rotating shaft 16 rotates, the first belt pulley drives the second belt pulley to rotate, the rotor 12 is further driven to rotate, and the diameters of the first belt pulley and the second belt pulley can be adjusted according to actual rotating speed requirements. Any one of the drive shaft, the drive chain and the drive belt may be used alone, or any two or three thereof may be used together.

According to the embodiment of this disclosure, many rotor unmanned aerial vehicle's drive mechanism can adjust and select according to the design demand of reality, satisfies the design demand of different functions and technique.

According to an embodiment of the present disclosure, the multi-rotor drone is further provided with a pitch device 17, the pitch device 17 being configured to control the pitch of the rotor 12.

According to an embodiment of the present disclosure, the rotors 12 are rotors with variable pitch, the pitch devices 17 are configured to directly control the variation of the pitch of the rotors, and each rotor 12 is provided with a pitch device 17 that individually controls the variation of the pitch of the rotor 12. Carry out pitch control to different rotors 12 through displacement device 17 to change the lift size of the rotor 12 of different positions, thereby adjust many rotor unmanned aerial vehicle's flight gesture, guarantee that many rotor unmanned aerial vehicle can be in aerial safe and stable's flight.

In the disclosed embodiment, the rotor 12 is configured as a pitchable rotor, i.e., by controlling the pitch of the blades of the rotor 12 relative to the plane of rotation to control the distance the blades of the rotor 12 theoretically travel up or forward in one revolution about the plane of rotation. Under the circumstances that the rotational speed of rotor remains unchanged, the pitch when the rotor is big more, and it can be for many rotor unmanned aerial vehicle provide lift also big more, and the pitch when the rotor is little, and it can be for many rotor unmanned aerial vehicle provide lift also little. Therefore, the variable pitch of rotor 12 can make the user adjust the lift size of many rotor unmanned aerial vehicle's every rotor in a flexible way, realizes the accurate adjustment to many rotor unmanned aerial vehicle flight state.

According to the embodiment of the disclosure, the pitch-variable device is provided with a steering engine, the steering engine is connected with the blades of the rotor wing through a connecting rod, and the steering engine is configured to control the attack angle of the blades through the connecting rod so as to adjust the pitch of the rotor wing.

For example, the pitch-varying device may be a steering engine, and the pitch of the rotor 12 is controlled by changing the angle of the steering engine, and the lift force of the rotor 12 can be adjusted by changing the pitch, so that the lift force of the rotor 12 is changed by adjusting the pitch when the rotation speed of the rotor 12 is not changed. Specifically, the blades of the rotor 12 may be controlled by a steering engine to vary the angle of attack of the blades, thereby enabling control of the pitch of the rotor 12. The pitch-variable device is, for example, a structure in which a connecting rod connects a variable-attack-angle paddle with a movable part of a steering engine, and when the movable part of the steering engine moves, the connecting rod drives the paddle to change the attack angle of the paddle, thereby adjusting the pitch of a rotor. Other means for adjusting the pitch of the rotor may be used.

According to the embodiment of the disclosure, the connecting rod is driven by the steering engine to change the attack angle of the blade and realize the control of the propeller pitch of the rotor. Under the condition that the rotation speed of the rotor wing is not changed, the angle of attack of the paddle is continuously adjusted through the steering engine driving connecting rod, accurate control over the lift force of the rotor wing can be achieved, and accurate control over the flight postures of the multi-rotor wing unmanned aerial vehicle is achieved.

According to an embodiment of the present disclosure, the multi-rotor drone is further provided with an air compression device 18 configured to communicate with the pressure vessel 132 for charging the pressure vessel 132 of the air jet device 13 with compressed air.

For example, the air compressor 18 is used to compress air and pump the air into the pressure vessel 132, and the air compressor 18 may be driven by electricity or fuel such as fuel. The air compressing device 18 charges the pressure vessel 132 with the compressed air when it detects that the pressure inside the pressure vessel is insufficient or the compressed air needs to be charged, and stops the charging when the pressure inside the pressure vessel 132 exceeds a set value.

In other embodiments of the present disclosure, the air compressing device may compress other gases (non-air), may generate other compressed gases (e.g., inert gases, etc.), and may charge the generated compressed gases into the pressure vessel for storage.

According to the embodiment of this disclosure, air compression device can provide power for many rotor unmanned aerial vehicle flight, and it starts promptly when detecting pressure vessel's internal pressure is not enough, is favorable to improving many rotor unmanned aerial vehicle's voyage.

According to the embodiment of this disclosure, many rotor unmanned aerial vehicle still is provided with control module 19, and control module 19 and jet-propelled device 13, rotor 12, rotary part 14, displacement device 17 communication connection, and control module 19 receives control command and controls many rotor unmanned aerial vehicle's flight state based on this control command.

The control module 19 may include, but is not limited to, a processing chip, a controller, etc., and the control instructions received by the control module 19 may include electrical signal instructions, sound signal instructions, etc.

Control module 19 can control gas jet system 13 for example, specifically, can control the operating condition of the automatically controlled gas injection valve of gas jet system 13, adjusts the aperture of nozzle 131 to the realization is to the control of the flow and the speed of the gas of blowout in nozzle 131, realizes adjusting the power of many rotor unmanned aerial vehicle flights.

Control module 19 can control the speed of rotation of rotor 12, for example, and when different rotors 12 have different speeds of rotation, the lift that each rotor 12 of multi-rotor drone produced is different, through control module 19 to the adjustment of rotor 12 rotational speed, realizes controlling and adjusting multi-rotor drone's flight action.

The control module 19 may control the pitch control device 17, for example, so that the pitch control device 17 adjusts the pitch of the blades of the rotor 12, and the rotor 12 may still adjust the lift when the rotation speed is unchanged, thereby controlling and adjusting the flight status of the multi-rotor drone.

The control module 19 may, for example, control the rotational speed of the rotary part 14, thereby indirectly adjusting the rotational speed of the rotor 12, enabling adjustment of the flight state of the multi-rotor drone.

According to the embodiment of this disclosure, many rotor unmanned aerial vehicle is through setting up control module 19, and control module 19 can carry out accurate control to a plurality of parts of many rotor unmanned aerial vehicle, effectively improves unmanned aerial vehicle's the ability of controlling.

According to the embodiment of the present disclosure, the principle that multi-rotor unmanned aerial vehicle realizes flight is as follows:

many rotor unmanned aerial vehicle's air compression device compresses the air to go into the pressure vessel with the air after compressing through the gas piping pump and save in, pressure vessel and nozzle intercommunication, the aperture of nozzle is controlled through automatically controlled gas injection valve. After many rotor unmanned aerial vehicle received the flight instruction, control module sends control command and makes automatically controlled gas injection valve adjust the aperture of nozzle, and the compressed gas who stores in pressure vessel spouts in the nozzle from, produces the thrust towards the nozzle opposite direction to many rotor unmanned aerial vehicle.

Unmanned aerial vehicle main part bottom just is close to the rotary part of nozzle tip setting and rotates under compressed gas's drive, and rotary part passes through drive mechanism and drives the rotor and rotate, and the rotor provides lift to many rotor unmanned aerial vehicle rotating the in-process. The control module adjusts the rotating speed or the propeller pitch of the rotor wing through controlling the pitch changing device, the rotating part, the air injection device and other parts, and the adjustment of the flight attitude of the unmanned aerial vehicle is realized.

According to the embodiment of this disclosure, through setting up air compressor arrangement for unmanned aerial vehicle, can fill compressed air into pressure vessel in succession, guarantee the gaseous replenishment and the supply of the compressed gas in the air pressure vessel on the one hand, on the other hand can improve unmanned aerial vehicle's duration, and then reach the effect that increases unmanned aerial vehicle's voyage.

The terms "front," "back," "upper," "lower," "upward," "downward," and other orientation descriptions used in this disclosure are for the purpose of describing exemplary embodiments of the disclosure, and are not intended to limit the structure of exemplary embodiments of the disclosure to any particular position or orientation. Terms of degree such as "substantially" or "approximately" are understood by those skilled in the art to refer to a reasonable range outside of the given value, e.g., the usual tolerances associated with the manufacture, assembly, and use of the described embodiments. The use of "first," "second," and similar terms in the present disclosure does not denote any order, quantity, or importance, but rather the terms are used to distinguish one element from another. Also, the use of the terms "a" or "an" and the like do not necessarily denote a limitation of quantity.

Those skilled in the art will appreciate that various combinations and/or combinations of features recited in the various embodiments and/or claims of the present disclosure can be made, even if such combinations or combinations are not expressly recited in the present disclosure. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present disclosure may be made without departing from the spirit or teaching of the present disclosure. All such combinations and/or associations are within the scope of the present disclosure.

The embodiments of the present disclosure have been described above. However, these examples are for illustrative purposes only and are not intended to limit the scope of the present disclosure. Although the embodiments are described separately above, this does not mean that the measures in the embodiments cannot be used in advantageous combination. The scope of the disclosure is defined by the appended claims and equivalents thereof. Various alternatives and modifications can be devised by those skilled in the art without departing from the scope of the present disclosure, and such alternatives and modifications are intended to be within the scope of the present disclosure.

Claims

1. A multi-rotor unmanned aerial vehicle, comprising:

the unmanned aerial vehicle main body comprises a main body and a support structure positioned on the periphery of the main body;

the rotor wing is connected with the fuselage through the supporting structure and is used for providing lift force for the multi-rotor unmanned aerial vehicle;

a rotating member connected with the body;

the transmission mechanism is connected with the rotating component and the rotor wing so as to drive the rotor wing to rotate through the transmission mechanism when the rotating component rotates;

and the air injection device is used for injecting compressed air and is configured to inject the compressed air to drive the rotating part to rotate and drive the rotor wing to rotate.

2. A multi-rotor drone according to claim 1, wherein the air jet means comprises:

a nozzle provided in a region of an orthogonal projection of a rotation circular surface of the rotating member, the nozzle being disposed so as to face the rotating member and configured to eject the compressed gas to rotationally drive the rotating member;

a pressure vessel adapted to contain the compressed gas, the pressure vessel in communication with the nozzle;

and the electric control gas injection valve is configured to control the opening of the nozzle so as to control the flow and the speed of the compressed gas.

3. A multi-rotor drone according to claim 2,

the rotary part sets up the bottom of unmanned aerial vehicle main part just is close to the nozzle tip, rotary part has a plurality of blades.

4. A multi-rotor drone according to claim 3, wherein the nozzles are arranged in the area of the bottom of the drone body opposite the circular plane of rotation of the rotating member.

5. The multi-rotor drone of claim 3, wherein the rotating member is rotatably mounted to the bottom of the drone body by a main axis of rotation that rotates with the main axis of rotation.

6. A multi-rotor unmanned aerial vehicle as claimed in claim 5, wherein the transmission mechanism has one end connected to the main shaft and the other end connected to the rotor, and the main shaft rotates to drive the rotor to rotate through the transmission mechanism.

7. The multi-rotor drone of claim 6, wherein the drive mechanism includes at least one of a drive shaft, a drive chain, and a drive belt.

8. A multi-rotor drone according to any one of claims 2 to 7, further comprising:

a pitch device configured to control a pitch of the rotor.

9. The multi-rotor drone of claim 8,

the pitch-variable device is provided with a steering engine, and the steering engine is connected with the blades of the rotor wing through a connecting rod;

the steering engine is configured to control an angle of attack of the blade via a linkage to adjust a pitch of the rotor.

10. The multi-rotor drone of claim 9, further comprising:

an air compression device configured to communicate with the pressure vessel for charging the pressure vessel of the air jet device with compressed air.

11. The multi-rotor drone of claim 10, further comprising:

control module, its with jet-propelled device, rotor, rotary part, displacement means communication connection, control module receives control command and is based on control command control many rotor unmanned aerial vehicle's flight status.