CN212022962U

CN212022962U - Unmanned aerial vehicle driving system and unmanned aerial vehicle

Info

Publication number: CN212022962U
Application number: CN202020300538.5U
Authority: CN
Inventors: 肖川; 姜林弟
Original assignee: Shenyang Woozoom Technology Co ltd
Current assignee: Shenyang Woozoom Technology Co ltd
Priority date: 2020-03-11
Filing date: 2020-03-11
Publication date: 2020-11-27
Anticipated expiration: 2030-03-11

Abstract

The utility model relates to an unmanned aerial vehicle driving system and unmanned aerial vehicle, unmanned aerial vehicle driving system include a plurality of ducts (1) that hold the rotor, the bottom of every duct is connected with air current pipe (2) respectively, every the air current pipe includes main line (21), is used for carminative first branch road (22) and towards other second branch road (23) that the air current pipe extends, wherein the end opening of first branch road is down, is provided with open and close valve (231) in the second branch road, and a plurality of second branch roads pass through valve selectivity intercommunication, and unmanned aerial vehicle driving system still includes the controlling means who is used for the control flap to open or close. Under the normal working state, all the valves are in the closed state; when arbitrary duct broke down, each valve of controlling means control was opened to the air current equipartition that makes the duct that does not break down produced to each airflow pipe in, make the unmanned aerial vehicle gesture stable until safe descending, avoid leading to unmanned aerial vehicle flight unstability, can not descend safely because of the trouble of any rotor department.

Description

Unmanned aerial vehicle driving system and unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically relates to an unmanned aerial vehicle driving system and unmanned aerial vehicle.

Background

The unmanned aerial vehicle can be divided into a fixed wing unmanned aerial vehicle and a rotor unmanned aerial vehicle according to the power supply form. Wherein, to many rotor unmanned aerial vehicle, the lift and the gesture of its motion are realized by the cooperation of a plurality of rotors, when one of them rotor broke down, can seriously destroy flight stability, produced the potential safety hazard. Therefore, the design of the unmanned aerial vehicle power system which can be regulated and controlled emergently when a fault occurs so that the unmanned aerial vehicle is stable in posture until safe landing has important significance.

SUMMERY OF THE UTILITY MODEL

The first purpose of this disclosure is to provide an unmanned aerial vehicle driving system, this unmanned aerial vehicle driving system can solve the problem that leads to unmanned aerial vehicle flight unstability, can not descend safely because of the trouble of any one rotor department.

A second object of the present disclosure is to provide a drone including the drone power system provided by the present disclosure.

In order to achieve the above object, the present disclosure provides an unmanned aerial vehicle power system, including a plurality of ducts containing rotors, a gas flow pipe is connected to a bottom end of each duct, each gas flow pipe includes a main pipe, a first branch for exhausting gas, and a second branch extending toward the other gas flow pipes, wherein a terminal opening of the first branch is downward, an openable valve is disposed in the second branch, and a plurality of the second branches are selectively communicated through the valve, and the unmanned aerial vehicle power system further includes a control device for controlling the opening or closing of the valve.

Optionally, the first branch comprises a first straight tube extending horizontally away from the duct and a second straight tube communicably connected to an end of the first straight tube and extending downwardly.

Optionally, the second straight tube extends obliquely downwards towards a direction away from the duct.

Optionally, an elbow is connected between the first straight pipe and the second straight pipe, and the elbow is configured to drive the second straight pipe to rotate around the first straight pipe.

Optionally, the elbow comprises a first part fixed with the first straight pipe and a second part fixed with the second straight pipe, the first part and the second part are rotatably connected through a universal joint, and a driver for controlling the universal joint is arranged on the airflow pipe and is connected with a flight control system of the unmanned aerial vehicle in a communication mode.

Optionally, the number of the ducts and the number of the airflow pipes are four respectively, and the ducts and the airflow pipes are evenly distributed along the circumferential direction of the unmanned aerial vehicle power system.

Optionally, the duct is butted with the gas flow pipe, and a sealing ring is arranged at the joint of the duct and the gas flow pipe.

Optionally, a base is further included, the duct and the gas flow tube being mounted on the base, respectively.

Optionally, the main pipeline vertically penetrates through the base, and the duct is arranged above the main pipeline and fixed on the base through a bracket.

According to a second aspect of the present disclosure, there is also provided a drone including the drone power system as described above.

Through above-mentioned technical scheme, the unmanned aerial vehicle driving system that this disclosure provided passes through controlling means to the control of each valve, so that the second branch road selectively communicates, rotor or other structures in a certain or a plurality of ducts break down and lead to the air current not smooth when, controlling means control each valve open, so that the air current equipartition that the rotor produced in the duct that does not break down to each airflow pipe in, make the unmanned aerial vehicle gesture stable until safe landing, guaranteed unmanned aerial vehicle flight's stability and security.

Additional features and advantages of the disclosure will be set forth in the detailed description which follows.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description serve to explain the disclosure without limiting the disclosure. In the drawings:

FIG. 1 is a schematic block diagram of an unmanned aerial vehicle power system provided in an exemplary embodiment of the present disclosure;

fig. 2 is a bottom view of an unmanned aerial vehicle power system provided by an exemplary embodiment of the present disclosure;

fig. 3 is a schematic view of an unmanned aerial vehicle power system provided in an exemplary embodiment of the present disclosure with ducts and airflow pipes disassembled.

Description of the reference numerals

1 duct 11 first flange

2 airflow pipe 21 main pipeline

211 second flange 22 first branch

221 first straight pipe 222 second straight pipe

223 elbow 23 second branch

231 valve 3 driver

4 base 41 support

Detailed Description

The following detailed description of specific embodiments of the present disclosure is provided in connection with the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present disclosure, are given by way of illustration and explanation only, not limitation.

In this disclosure, unless stated to the contrary, use of directional words such as "upper and lower" generally means defined with the unmanned aerial vehicle power system provided by the present disclosure operating normally, and "inner and outer" means inner and outer of the respective component profiles. Furthermore, the terms "first," "second," and the like, as used in this disclosure, are intended to distinguish one element from another, and not necessarily for order or importance. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated.

Referring to fig. 1 to 3, the present embodiment provides an unmanned aerial vehicle power system that provides power to an unmanned aerial vehicle by rotating a rotor via an engine to generate thrust. The unmanned aerial vehicle power system comprises a plurality of ducts 1 containing rotors, wherein the ducts 1 form passages for airflow generated by the rotors, can generate larger thrust compared with a single rotor, and have certain protection effect on the rotors. Referring to fig. 1 and 2, a gas flow tube 2 is connected to a bottom end of each duct 1, respectively, and each gas flow tube 2 includes a main branch 21 interfacing with the duct 1, a first branch 22 for exhaust gas, and a second branch 23 extending toward the other gas flow tubes 2. Wherein the end of the first branch 22 is open downwards, that is, the thrust gas exhausted from the end of the first branch 22 flows downwards, which helps to control the hovering or lifting action of the drone, it should be noted that the end of the first branch 22 is open downwards refers to its general direction, and does not require a vertical arrangement, that is, may form an angle with the vertical plane. The second branch passage 23 is provided with an openable and closable valve 231, and the plurality of second branch passages 23 are selectively communicated through the valve 231. The unmanned aerial vehicle power system further comprises a control device for controlling the opening or closing of the valve 231 and a flight control system for controlling the flight attitude, and the control device and the flight control system are connected in a communication mode.

Through the above-mentioned arrangement, a plurality of second branches 23 pass through valve 231 selectively intercommunication, under the normal operating condition, each valve 231 all is the closed condition, rotor or other structures in a certain or a plurality of ducts 1 break down and lead to the air current not smooth when, each valve 231 of controlling means control is opened, make thrust air current evenly distributed that the rotor produced in duct 1 that does not break down in each air current pipe 2, make the unmanned aerial vehicle gesture stable until safe descending, the stability and the security of flying under the normal operating condition of unmanned aerial vehicle have been increased.

In addition, the configuration of the valve 231 and the second branch 23 is not limited in the embodiment of the present disclosure. According to one embodiment, as shown in fig. 2, a valve 231 is provided on each second branch 23; according to another embodiment, an N-way valve may be further disposed at a position where the plurality of second branches 23 converge, and the number of the valves 231 and the direction of the second branches 23 may be adaptively adjusted according to the number of the second branches 23.

As shown in fig. 1 and 3, the first branch 22 may comprise a first straight tube 221 extending horizontally from the ductus 1 away from the ductus 1 and a second straight tube 222 communicably connected to the end of the first straight tube 221. The air current gets into air current pipe 2 by duct 1, at the terminal blowout of the second straight tube 222 of air current pipe 2, arranges second straight tube 222 in the position far away from unmanned aerial vehicle power system's focus, has strengthened the stability of unmanned aerial vehicle flight under normal operating condition.

Further, as shown in fig. 1 and 3, the second straight pipe 222 may be configured to extend obliquely downward toward a direction away from the duct 1, so as to prevent the airflow from being sprayed to the central position of the unmanned aerial vehicle, thereby ensuring the stability of the unmanned aerial vehicle in flight.

In addition, as shown in fig. 1, an elbow 223 may be connected between the first straight pipe 221 and the second straight pipe 222, and the elbow 223 is configured to drive the second straight pipe 222 to rotate around the first straight pipe 221. The airflow pipe 2 may further be provided with a driver 3 for driving the second straight pipe 222 to rotate, and the driver 3 is communicably connected to the flight control system described above. Thus, by adjusting the angle of the second branch pipe 222, the direction of the jet can be adjusted, and the attitude of the aircraft can be controlled more stably. However, it should be noted here that the second straight pipe 222 is not rotated in any direction by any angle, but always keeps the exhaust direction thereof substantially downward.

According to one embodiment, the curved tube 223 may include a first portion fixed to the first straight tube 221 and a second portion fixed to the second straight tube 222, the first and second portions being rotatably connected by a universal joint. The driver 3 is used for controlling the universal joint to adjust the rotation direction and the angle of the second straight pipe 222, so that the air injection direction is controlled, and the aircraft attitude can be controlled stably.

According to another embodiment, the bent pipe 223 can be rotatably connected to one of the first straight pipe 221 and the second straight pipe 222 and fixedly connected to the other, for example, a universal joint can be provided between the bent pipe 223 and the first straight pipe 221 or the second straight pipe 222, and the relative rotation between the first straight pipe 221 and the second straight pipe 222 can be realized by controlling the universal joint through the driver 3.

According to another embodiment, the bent pipe 223 can be a flexible pipe, and both ends of the flexible pipe are respectively fixed on the first straight pipe 221 and the second straight pipe 222. In this case, the driver 3 may directly drive the first straight pipe 221 or the second straight pipe 222, for example, the driver 3 may include a telescopic member connected between the first straight pipe 221 and the second straight pipe 222, and the rotation of the second straight pipe 222 with respect to the first straight pipe 221 may be controlled by the action of the telescopic member.

In order to improve the stability of the power system, as shown in fig. 1 to 3, the number of the ducts 1 and the number of the air flow pipes 2 may be four respectively, and the ducts and the air flow pipes are uniformly distributed along the circumferential direction of the unmanned power system, that is, the ducts and the air flow pipes sequentially have 90 ° turning angles. It should be noted that, the number and the distribution situation of duct 1 and airflow pipe 2 can make corresponding adjustment according to actual conditions, and in each embodiment, duct 1 and airflow pipe 2 are all evenly arranged to ensure that unmanned aerial vehicle's gesture is stable.

In order to prevent the air current from leaking, the connecting part of the duct 1 and the air current pipe 2 is provided with a sealing ring, and the sealing ring can be selected as a sealing rubber gasket, so that the air leakage is avoided, and the working efficiency is improved. In particular, with reference to figure 3, the duct 1 can comprise a tubular body and a first flange 11, the main conduit 21 can comprise a tubular body and a second flange 211 at the end, the first flange 11 and the second flange 211 being in face contact, the sealing ring being clamped between the first flange 11 and the second flange 211.

In an exemplary embodiment of the present disclosure, the unmanned aerial vehicle power system further includes a base 4, and the duct 1 and the airflow duct 2 are respectively installed on the base 4, that is, the duct 1 and the airflow duct 2 may be integrated into a whole. In particular, according to some embodiments, as shown in figure 3, the main conduit 21 extends vertically through the basement 4, the duct 1 being arranged above the main conduit 21 and being fixed to the basement 4 by means of a bracket 41. Referring to fig. 1 and 3, in the present embodiment, the outer circumferential surface of the duct 1 is provided with mounting lugs, and the bracket 41 is configured in a strip shape, one end of which is fixed to the base 4, and the other end of which is detachably mounted on the lugs by means of bolting or the like.

In another aspect of the present disclosure, there is also provided an unmanned aerial vehicle including the unmanned aerial vehicle power system as described above. Compared with the prior art, the unmanned aerial vehicle has the same advantages as the unmanned aerial vehicle power system, and the description is omitted.

The preferred embodiments of the present disclosure are described in detail with reference to the accompanying drawings, however, the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solution of the present disclosure within the technical idea of the present disclosure, and these simple modifications all belong to the protection scope of the present disclosure.

It should be noted that, in the foregoing embodiments, various features described in the above embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, various combinations that are possible in the present disclosure are not described again.

In addition, any combination of various embodiments of the present disclosure may be made, and the same should be considered as the disclosure of the present disclosure, as long as it does not depart from the spirit of the present disclosure.

Claims

1. An unmanned aerial vehicle power system is characterized by comprising a plurality of ducts (1) containing rotors, wherein the bottom end of each duct (1) is connected with an air flow pipe (2), each air flow pipe (2) comprises a main pipeline (21), a first branch (22) for exhausting and a second branch (23) extending towards other air flow pipes (2), the tail end of the first branch (22) is opened downwards, an openable and closable valve (231) is arranged in the second branch (23), the second branches (23) are selectively communicated through the valve (231), and the unmanned aerial vehicle power system further comprises a control device for controlling the opening or closing of the valve (231).

2. An unmanned aerial vehicle power system according to claim 1, wherein the first branch (22) comprises a first straight pipe (221) extending horizontally away from the duct (1) and a second straight pipe (222) communicably connected to a distal end of the first straight pipe (221) and extending downward.

3. An unmanned aerial vehicle power system according to claim 2, wherein the second straight pipe (222) extends obliquely downwards towards a direction away from the duct (1).

4. An unmanned aerial vehicle power system according to claim 2, wherein an elbow (223) is connected between the first straight pipe (221) and the second straight pipe (222), and the elbow (223) is configured to drive the second straight pipe (222) to rotate around the first straight pipe (221).

5. The unmanned aerial vehicle power system according to claim 4, wherein the elbow (223) comprises a first part fixed with the first straight pipe (221) and a second part fixed with the second straight pipe (222), the first part and the second part are rotatably connected through a universal joint, a driver (3) for controlling the universal joint is arranged on the air flow pipe (2), and the driver (3) is connected with an unmanned aerial vehicle flight control system in a communication mode.

6. The unmanned aerial vehicle power system of claim 1, wherein the number of the ducts (1) and the airflow pipes (2) is four, and the ducts and the airflow pipes are evenly distributed along the circumferential direction of the unmanned aerial vehicle power system.

7. The unmanned aerial vehicle power system of claim 1, wherein the duct (1) is butted with the air flow pipe (2) and a sealing ring is arranged at the joint of the duct and the air flow pipe.

8. The unmanned aerial vehicle power system of any of claims 1-7, further comprising a base (4), the duct (1) and the gas flow tube (2) being mounted on the base (4), respectively.

9. An unmanned aerial vehicle power system according to claim 8, wherein the main pipeline (21) vertically penetrates the base (4), and the duct (1) is arranged above the main pipeline (21) and fixed on the base (4) through a bracket (41).

10. An unmanned aerial vehicle comprising the unmanned aerial vehicle power system of any of claims 1-9.