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WO2018161193A1 - Véhicule aérien à quatre axes pourvu de lumières - Google Patents

Véhicule aérien à quatre axes pourvu de lumières Download PDF

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Publication number
WO2018161193A1
WO2018161193A1 PCT/CN2017/075672 CN2017075672W WO2018161193A1 WO 2018161193 A1 WO2018161193 A1 WO 2018161193A1 CN 2017075672 W CN2017075672 W CN 2017075672W WO 2018161193 A1 WO2018161193 A1 WO 2018161193A1
Authority
WO
WIPO (PCT)
Prior art keywords
module
fuselage
loop
spiral
control circuit
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2017/075672
Other languages
English (en)
Chinese (zh)
Inventor
肖丽芳
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to PCT/CN2017/075672 priority Critical patent/WO2018161193A1/fr
Publication of WO2018161193A1 publication Critical patent/WO2018161193A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/006Safety devices
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64UUNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00Type of UAV
    • B64U10/10Rotorcrafts
    • B64U10/13Flying platforms
    • B64U10/14Flying platforms with four distinct rotor axes, e.g. quadcopters
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64UUNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00Propulsion; Power supply
    • B64U50/10Propulsion
    • B64U50/19Propulsion using electrically powered motors
    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05DSYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/10Simultaneous control of position or course in three dimensions
    • G05D1/101Simultaneous control of position or course in three dimensions specially adapted for aircraft
    • G05D1/102Simultaneous control of position or course in three dimensions specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64UUNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2201/00UAVs characterised by their flight controls

Definitions

  • the utility model belongs to the field of machines, and in particular relates to a four-axis light aircraft.
  • the communication between the UAV and the ground terminal is mostly wirelessly transmitted, that is, the flight state of the UAV is transmitted to the ground terminal through a wireless signal.
  • the unmanned aerial vehicle flight state is not intuitive enough, and it is relatively lagging. In the user's control of the unmanned aerial vehicle flight, the unmanned aircraft can not notice the flight state of the unmanned aerial vehicle. It may cause an accident and is therefore not reliable enough. Therefore, how to get rid of a single wirelessly transmitted signal transmission method, a new device or method for knowing the flight state of an unmanned aerial vehicle has become a goal pursued by those skilled in the art.
  • a four-axis light aircraft comprising a control circuit, a wireless transceiver module, an electric motor, a battery, a fuselage and a top bumper: voltage input of the control circuit with a Bluetooth module, a test program module, a four-axis drive module and a barometric sensor module
  • the wireless transceiver module is composed of a filtering portion, a decoder, and the like, and is connected to an antenna and a power source; the motor is symmetrically distributed under the spiral spiral wing in front, rear, and left and right directions of the body; the battery is embedded in the body.
  • the control circuit is composed of a control loop, a power loop, a main loop, and an auxiliary loop; wherein the control loop is composed of a power loop, a button switch, a protection switch, a relay coil, and an auxiliary thereof.
  • the power supply circuit is composed of a photoresistor R, a magnetron switch L, a fixed value resistor R0, a power source Ul, and the like.
  • the wireless transceiver The module and the receiving module are directly connected to the decoder; the decoder is further connected to the single chip by the encoding module and the high frequency transmitting module; and the receiving portion is composed of the high frequency frequency selecting module and the demodulating module.
  • a four-axis light aircraft wherein: the motor is composed of a stationary locating and a rotatable rotor; the stator is mainly composed of a stator core The stator winding resistance and the base are composed of three parts; the rotor is connected to the spiral wing by a shaft, and the spiral wings are symmetrically distributed in the front, rear, and left and right directions of the body; the spiral wings are at the same height plane and the structure is The radii are all the same, the motor is symmetrically mounted on the bracket end of the aircraft; the intermediate space of the bracket end houses the flight control computer and external equipment.
  • the utility model has the advantages of dexterous structure and low energy consumption, and the monitoring personnel of the monitoring room can realize wireless remote control of the aircraft through Bluetooth, etc., when the aircraft flies to the scene after the disaster. In the sky, the image data can be wirelessly transmitted to the monitoring room through the carried camera, which provides convenience for on-site decision-making.
  • 1 is a front view showing the structure of the present invention.
  • the top anti-collision bar 2, charging interface; 3, U SB interface; 4, control circuit; 5, wireless transceiver module; 6, base; 7, laser transmitter; 8, laser; 9, battery; 10, the fuselage; 11, the motor; 12, the spiral wing.
  • a four-axis light aircraft includes a control circuit (4), a wireless transceiver module (5), an electric motor (11), a battery (9), a fuselage (10) and a top bumper (1).
  • the control circuit (4) is connected to a voltage input end of the Bluetooth module, the test program module, the four-axis drive module, and the air pressure sensor module;
  • the wireless transceiver module (5) is composed of a filter part, a decoder, and the like, and an antenna and a power supply.
  • the control circuit (4) is controlled
  • the circuit, the power circuit, the main circuit and the auxiliary circuit are composed of: the control circuit is composed of a power circuit, a button switch, a protection switch, a relay coil and an auxiliary contact thereof; the power circuit is composed of a photoresistor R and a magnetic control
  • the switch module (5) and the receiving module are directly connected to the decoder; the decoder is connected to the single chip microcomputer and is composed of an encoding module and a high frequency transmitting module; The receiving portion is composed of a high frequency frequency selective module and a demodulation module; the motor (11) is composed of a stationary locating and a rotatable rotor; the stat
  • the rotor is connected to the spiral helix (12) through a shaft, and the spiral wing (12) is symmetrically distributed in the front, rear, and left and right directions of the body; the spiral wing (12) is in the same A height plane, and the same structure and radius, the motor (11) has four symmetrical mountings on the support end of the aircraft, and the flight control computer and external equipment are placed in the middle space of the bracket.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)

Abstract

L'invention concerne un véhicule aérien à quatre axes pourvu de lumières ayant un circuit de commande (4), un module émetteur-récepteur sans fil (5), des moteurs (11), une pile (9), un fuselage (10) et une tige anti-collision supérieure (1). Le circuit de commande (4) est connecté à des extrémités d'entrée de tension d'un module Bluetooth, d'un module de programme d'essai, d'un module d'entraînement à quatre axes et d'un module de capteur de pression d'air. Le module émetteur-récepteur sans fil (5) est composé d'une partie filtre, d'un décodeur et autres, et est connecté à une antenne et à une alimentation. Les moteurs (11) sont situés sous une hélice (12) et sont répartis symétriquement dans les directions avant, arrière, gauche et droite. Le véhicule aérien possède une structure ingénieuse et une faible consommation d'énergie.
PCT/CN2017/075672 2017-03-05 2017-03-05 Véhicule aérien à quatre axes pourvu de lumières Ceased WO2018161193A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2017/075672 WO2018161193A1 (fr) 2017-03-05 2017-03-05 Véhicule aérien à quatre axes pourvu de lumières

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2017/075672 WO2018161193A1 (fr) 2017-03-05 2017-03-05 Véhicule aérien à quatre axes pourvu de lumières

Publications (1)

Publication Number Publication Date
WO2018161193A1 true WO2018161193A1 (fr) 2018-09-13

Family

ID=63447693

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2017/075672 Ceased WO2018161193A1 (fr) 2017-03-05 2017-03-05 Véhicule aérien à quatre axes pourvu de lumières

Country Status (1)

Country Link
WO (1) WO2018161193A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112121205A (zh) * 2020-10-27 2020-12-25 常州市疾病预防控制中心 一种大空间场所环境及空气消毒装置和系统

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102442424A (zh) * 2011-10-21 2012-05-09 北京工业大学 一种固定翼无人机的定高飞行控制系统与方法
CN103365295A (zh) * 2013-06-29 2013-10-23 天津大学 基于dsp的四旋翼无人飞行器自主悬停控制系统及方法
CN105700540A (zh) * 2016-03-09 2016-06-22 哈尔滨工业大学深圳研究生院 基于fpga的无人机飞行控制电路
CN205787908U (zh) * 2016-05-23 2016-12-07 湖北省超能超高压电力科技开发有限公司 一种基于输变电设备无人机载场强仪避障系统
JP6051327B1 (ja) * 2016-05-26 2016-12-27 株式会社プロドローン 無人航空機
US20170015412A1 (en) * 2015-07-17 2017-01-19 iDrone LLC Thrust vectoring on a rotor-based remote vehicle

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102442424A (zh) * 2011-10-21 2012-05-09 北京工业大学 一种固定翼无人机的定高飞行控制系统与方法
CN103365295A (zh) * 2013-06-29 2013-10-23 天津大学 基于dsp的四旋翼无人飞行器自主悬停控制系统及方法
US20170015412A1 (en) * 2015-07-17 2017-01-19 iDrone LLC Thrust vectoring on a rotor-based remote vehicle
CN105700540A (zh) * 2016-03-09 2016-06-22 哈尔滨工业大学深圳研究生院 基于fpga的无人机飞行控制电路
CN205787908U (zh) * 2016-05-23 2016-12-07 湖北省超能超高压电力科技开发有限公司 一种基于输变电设备无人机载场强仪避障系统
JP6051327B1 (ja) * 2016-05-26 2016-12-27 株式会社プロドローン 無人航空機

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112121205A (zh) * 2020-10-27 2020-12-25 常州市疾病预防控制中心 一种大空间场所环境及空气消毒装置和系统

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