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WO2018188053A1 - Dispositif de poussée destiné à introduire un tuyau de gaz dans un véhicule aérien sans pilote - Google Patents

Dispositif de poussée destiné à introduire un tuyau de gaz dans un véhicule aérien sans pilote Download PDF

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Publication number
WO2018188053A1
WO2018188053A1 PCT/CN2017/080530 CN2017080530W WO2018188053A1 WO 2018188053 A1 WO2018188053 A1 WO 2018188053A1 CN 2017080530 W CN2017080530 W CN 2017080530W WO 2018188053 A1 WO2018188053 A1 WO 2018188053A1
Authority
WO
WIPO (PCT)
Prior art keywords
pin
hole
shaft pin
shaft
fixed
Prior art date
Application number
PCT/CN2017/080530
Other languages
English (en)
Chinese (zh)
Inventor
肖丽芳
Original Assignee
深圳市方鹏科技有限公司
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 深圳市方鹏科技有限公司 filed Critical 深圳市方鹏科技有限公司
Priority to PCT/CN2017/080530 priority Critical patent/WO2018188053A1/fr
Publication of WO2018188053A1 publication Critical patent/WO2018188053A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs

Definitions

  • the present invention relates to a push device for an air intake pipe of a UAV aircraft.
  • the drone is referred to as "UAV”, abbreviated as “UAV”, and is a non-manned aircraft operated by radio remote control equipment and self-contained program control devices. From the technical point of view, it can be divided into: unmanned fixed-wing aircraft, unmanned vertical take-off and landing machines [1], unmanned airships, unmanned helicopters, unmanned multi-rotor aircraft, unmanned umbrellas, etc. UAVs can be divided into military and civilian applications according to the application field. In military terms, drones are divided into reconnaissance planes and drones.
  • Civilian, drone + industry application is the real need for drones; currently in aerial photography, agriculture, plant protection, micro-self-timer, express delivery, disaster relief, observation of wildlife, surveillance of infectious diseases, mapping, news reports, power patrol
  • the application of inspection, disaster relief, film and television shooting, manufacturing romance, etc. has greatly expanded the use of the drone itself, and developed countries are also actively expanding the application and development of drone technology.
  • CA Civil Aviation Administration of China
  • CA Civil Aviation Administration of China
  • the China AOPA Association is responsible for the management of civil drones.
  • the operation of UAVs in China can be divided into 11 cases according to the size of the aircraft and the flight space. Among them, only 116 kg or more and 4,600 m above are flying in the converged airspace. In other cases, other flights, including the increasingly popular micro-aviation aircraft, are managed by industry associations or by the operator.
  • a push device for an air intake pipe of a drone aircraft is provided.
  • a push device for an air intake pipe of a UAV aircraft the main structures thereof are: a servo motor, a reversing gear set, a steel frame plate, and a long Strip hole, circular hole, mounting hole, cover, trache hole, track, track groove, driven wheel, pin a, drive wheel, pin b, bushing, fixing block, pull pin, pin rod ,
  • the steel frame plate has a long strip at one end
  • the hole groove has a circular hole groove in the middle position and a mounting hole groove at the other end.
  • the circular hole groove has a sleeve embedded therein, and the shaft sleeve penetrates the shaft pin b.
  • One end of the shaft pin b is fixed with a driving wheel, and the other end is inserted into the reversing gear set, and the other end of the reversing gear set is inserted.
  • the shaft end of the servo motor. a shaft pin a is fixed in the driven wheel, and the shaft pin a penetrates into the elongated hole; the top end of the shaft pin a has a hole in a lateral position, and the hole is internally threaded; the steel frame plate
  • a fixing block is fixed at the end end, and a pulling pin is screwed in the fixing block, and the pulling pin is matched with the thread in the hole of the shaft pin a .
  • a crawler belt is arranged between the driven wheel and the driving wheel, and a crawler groove is arranged in the concave portion in the middle position of the crawler belt;
  • the crawler outer cover has a cover, and the end of the cover has a tracheal hole at each end.
  • a bearing is sleeved between the driven wheel and the axle pin a.
  • a bearing is sleeved between the driving wheel and the axle pin b.
  • the mounting hole is fixed to the drone device.
  • the crawler belt is covered with a layer of fireproof cotton. Further, the cover is inserted and fixed to the steel frame by a pin.
  • the crawler belt is arranged between the driven wheel and the driving wheel, and the crawler groove is arranged in the concave portion in the middle position of the crawler belt, and the technical means of the air pipe hole are respectively arranged at both ends of the cover, thereby realizing the use of the servo pipe through the servo.
  • the motor speed control so that the process of the gas pipe access is completely controlled by the electronic device, how much is introduced, how much is pulled out, and the device of the drone is completely controlled.
  • FIG. 1 is an overall structural view of a push device for an air intake pipe of a UAV aircraft according to the present invention.
  • 2 is an exploded structural view of a push device for a gas pipe of a UAV aircraft according to the present invention.
  • Figure 1- Servo motor, 11- reversing gear set, 2-steel frame, 21-long slot, 22-round slot, 23-mounting slot, 3-cover, 31-pipe hole , 4-track, 41-track groove, 5-driven wheel, 51-axis pin a, 6-drive wheel, 61-axis pin b, 7- bushing, 8-fixing block, 81-pull pin, 9-pin Rod.
  • a push device for an air intake pipe of a UAV aircraft the main structures thereof are: a servo motor 1, a reversing gear set 11.
  • Steel frame plate 2 elongated hole groove 21, circular hole groove 22, mounting hole groove 23, cover 3, gas pipe hole 31, crawler belt 4, track groove 41, driven wheel 5, shaft pin a51, driving wheel 6.
  • the steel frame plate 2 has an elongated hole 21 in the end, and a circular hole 22 in the middle position.
  • the other end is provided with a mounting hole groove 23.
  • the circular hole groove 22 has a sleeve 7 built therein, and the shaft sleeve 7 has a through-shaft pin b61.
  • the driving pin 6 is fixed at one end of the shaft pin b61, and the other end is inserted into the reversing gear set 11, the reversing gear The other end of the group 11 is inserted with the shaft end of the servo motor 1.
  • a shaft pin a5 1 is fixed in the driven wheel 5, and a shaft pin a51 passes through the elongated hole 21; the shaft pin a51 has a hole in a lateral position at the top end, and the hole is internally threaded; the steel
  • the fixing plate 8 is fixed to the end plate 2, and the pulling pin 81 is screwed in the fixing block 8.
  • the pulling pin 81 is matched with the thread in the hole of the shaft pin a51.
  • a crawler belt 4 is disposed between the driven wheel 5 and the driving wheel 6, and a crawler groove 41 is disposed in a concave portion at an intermediate position of the crawler belt 4; the crawler belt 4 has a cover 3 on the outer cover, and the cover 3 has two ends at the ends There is a tracheal hole 31.
  • a bearing is sleeved between the driven wheel 5 and the axle pin a51.
  • a bearing is sleeved between the driving wheel 6 and the shaft pin b61.
  • the mounting hole 23 is fixed to the drone device.
  • the crawler belt 4 is covered with a layer of fireproof cotton.
  • the cover 3 is inserted and fixed to the steel frame plate 2 by a pin rod 9.
  • the use process of the present invention is: firstly, the ventilating tube requiring surgery is inserted from the tracheal hole 31 at the end of the cover and is pierced by the tracheal hole 31 at the other end, and the end of the vent tube which is worn out is inserted into the air inlet device, and this is The port goes to the ventilation room of the drone.
  • the servo motor 1 is started to perform a smooth needle operation. Since the crawler groove 41 of the crawler belt 4 is wrapped with the vent pipe, when the crawler belt 4 is rotated, the crawler belt 4 can drive the vent pipe to move to one side.
  • the pull pin 81 disposed in the fixing block 8 at the end of the steel frame plate 2 is screwed or loosened to adjust the distance between the track 4 and the driving wheel 6 to adjust the distance between the moving wheel 5 and the driving wheel 6.
  • the tracked track 4 is tight. Due to the good numerical control performance of the servo motor 1, the number of revolutions is converted by the computer information, and the effective control of the track 4 pushes the precise distance of the snorkel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un dispositif de poussée destiné à introduire un tuyau de gaz dans un véhicule aérien sans pilote. Un trou allongé (21) est formé au niveau d'une extrémité d'une plaque de cadre en acier (2), un trou circulaire (22) est formé au niveau de la position centrale, et un tube de montage (23) est situé au niveau de l'autre extrémité. Une douille (7) est disposée dans le trou circulaire (22); une broche d'arbre b (61) pénètre dans la douille; et une roue d'entraînement (6) est fixée au niveau d'une extrémité de la broche d'arbre b, et l'autre extrémité pénètre dans un ensemble d'engrenages d'inversion (11); une extrémité d'arbre rotatif d'un servomoteur (1) est insérée dans l'autre extrémité de l'ensemble d'engrenages d'inversion; une courroie (4) est disposée entre une roue entraînée et la roue d'entraînement; et une rainure de courroie (41) est formée au niveau d'un évidement au niveau de la position centrale de la courroie; les deux extrémités d'un couvercle (3) sont respectivement pourvues de trous de tuyau de gaz (31). Sur la base du dispositif de poussée, l'introduction du tuyau de gaz est complètement commandée par la vitesse de rotation du servomoteur, de telle sorte que le processus d'introduction du tuyau de gaz est complètement commandé par un dispositif électronique, et les étendues d'introduction et de retrait sont complètement commandées par un dispositif du véhicule aérien sans pilote.
PCT/CN2017/080530 2017-04-14 2017-04-14 Dispositif de poussée destiné à introduire un tuyau de gaz dans un véhicule aérien sans pilote WO2018188053A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2017/080530 WO2018188053A1 (fr) 2017-04-14 2017-04-14 Dispositif de poussée destiné à introduire un tuyau de gaz dans un véhicule aérien sans pilote

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2017/080530 WO2018188053A1 (fr) 2017-04-14 2017-04-14 Dispositif de poussée destiné à introduire un tuyau de gaz dans un véhicule aérien sans pilote

Publications (1)

Publication Number Publication Date
WO2018188053A1 true WO2018188053A1 (fr) 2018-10-18

Family

ID=63792177

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2017/080530 WO2018188053A1 (fr) 2017-04-14 2017-04-14 Dispositif de poussée destiné à introduire un tuyau de gaz dans un véhicule aérien sans pilote

Country Status (1)

Country Link
WO (1) WO2018188053A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102785778A (zh) * 2012-07-17 2012-11-21 王�华 一种管式发射灭火无人机及灭火控制方法
US8439301B1 (en) * 2011-07-18 2013-05-14 Systems Engineering Associates Corporation Systems and methods for deployment and operation of unmanned aerial vehicles
US20160137312A1 (en) * 2014-05-06 2016-05-19 Osterhout Group, Inc. Unmanned aerial vehicle launch system
CN105620780A (zh) * 2016-02-20 2016-06-01 周栋 可水下启动侦查无人飞机的推进器

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8439301B1 (en) * 2011-07-18 2013-05-14 Systems Engineering Associates Corporation Systems and methods for deployment and operation of unmanned aerial vehicles
CN102785778A (zh) * 2012-07-17 2012-11-21 王�华 一种管式发射灭火无人机及灭火控制方法
US20160137312A1 (en) * 2014-05-06 2016-05-19 Osterhout Group, Inc. Unmanned aerial vehicle launch system
CN105620780A (zh) * 2016-02-20 2016-06-01 周栋 可水下启动侦查无人飞机的推进器

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