WO2019127565A1 - Lanceur d'aéronef - Google Patents

Lanceur d'aéronef Download PDF

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Publication number
WO2019127565A1
WO2019127565A1 PCT/CN2017/120386 CN2017120386W WO2019127565A1 WO 2019127565 A1 WO2019127565 A1 WO 2019127565A1 CN 2017120386 W CN2017120386 W CN 2017120386W WO 2019127565 A1 WO2019127565 A1 WO 2019127565A1
Authority
WO
WIPO (PCT)
Prior art keywords
base
support frame
aircraft
telescopic structure
support
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/CN2017/120386
Other languages
English (en)
Chinese (zh)
Inventor
王凤太
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.)
Flysky Technology Co Ltd
Original Assignee
Flysky Technology Co Ltd
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 Flysky Technology Co Ltd filed Critical Flysky Technology Co Ltd
Priority to PCT/CN2017/120386 priority Critical patent/WO2019127565A1/fr
Priority to CN201780005123.6A priority patent/CN108513569B/zh
Publication of WO2019127565A1 publication Critical patent/WO2019127565A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft

Definitions

  • the present disclosure relates to the field of aircraft launching device technology, and in particular to an aircraft launcher.
  • Aircraft are widely used in the current society.
  • the prospects for aerial photography, forest fire inspection, geological survey, high-voltage transmission line inspection, oil field pipeline inspection, highway management, emergency rescue and rescue are extremely broad.
  • the aircraft Before the aircraft is maneuvered, it is placed on the ground. When taking off, the aircraft needs to fly a certain distance vertically from the ground before starting to fly back and forth, which takes a long time to take off. Alternatively, simply tilt the aircraft against a stone at an angle to the ground so that it can take off faster than the ground, but this method does not easily adjust the angle of the aircraft to the ground.
  • the present disclosure provides an aircraft launcher to address deficiencies in the related art.
  • the present disclosure provides an aircraft launcher comprising a base and a support frame rotatably coupled to the base, the base for placing an aircraft, the support frame being rotated to support one end of the base such that the base is grounded Certain angle
  • the support frame includes a support portion disposed on one side of the base, and a positioning portion disposed on the other side of the base and connected to the support portion, the positioning portion is configured to fix the aircraft in the a base, wherein the support portion and the positioning portion are connected along a length direction of the support frame.
  • the support frame further includes a pivoting portion connecting the support portion and the positioning portion, and the pivoting portion is rotatably connected to the base.
  • the base is provided with a receiving portion for receiving the support frame, and the receiving portion is formed in the base, and rotating the support frame can accommodate the support frame in the base.
  • the base is provided with a fixing portion for fixing the support frame
  • the support frame is provided with a matching portion that cooperates with the fixing portion, and when the support frame is received in the base, the support frame is The fixing portion is in contact with the fitting portion.
  • one of the fixing portion and the engaging portion is a card slot, and the other is a buckle, and the fixing portion is engaged with the engaging portion.
  • a first limiting portion is disposed at a position of the base adjacent to the positioning portion; and after the supporting frame is rotated to a preset angle, the first limiting portion may be in contact with the positioning portion. The support frame is prevented from continuing to rotate.
  • one end of the base in the longitudinal direction is provided with a telescopic structure, and the telescopic structure can expand and contract along the length direction of the base.
  • the base includes a receiving portion for receiving the telescopic structure, and the telescopic structure is slidable within the receiving portion.
  • the receiving portion is a sliding slot formed in the base
  • the telescopic structure is a U-shaped rod having a preset width.
  • an end of the telescopic structure is provided with an elastic member, and the elastic member is disposed in the receiving portion.
  • the telescopic structure is provided with a second limiting portion
  • the supporting frame is provided with a nip portion that cooperates with the second limiting portion.
  • the nip portion cooperates with the second limiting portion to fix the telescopic structure in the accommodating portion.
  • the base is provided with a fixed card position
  • the second limiting portion is movable to the fixed card position, and when the support frame is received in the base, the pressing portion is pressed
  • the telescopic structure housed in the accommodating portion is fixed to the second limiting portion.
  • the present disclosure can adjust the tilt angle of the base to meet the take-off requirements of the aircraft by rotating the connected support frame to the base. Rotating the support frame can easily adjust the angle between the aircraft and the ground, which changes the problem that the conventional launcher aircraft is difficult to adjust after being placed on the shelf.
  • FIG. 1 is an exploded view of an aircraft launcher according to an embodiment of the present disclosure
  • Figure 2 is a view of the first direction of the aircraft launcher of Figure 1;
  • Figure 3 is a view of the second direction of the aircraft launcher of Figure 1;
  • Figure 4 is a schematic view of the aircraft launcher mating with the aircraft.
  • first, second, third, etc. may be used in the present disclosure to describe various information, such information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other.
  • first information may also be referred to as second information without departing from the scope of the present disclosure.
  • second information may also be referred to as first information.
  • word "if” as used herein may be interpreted as "when” or “when” or “in response to a determination.”
  • FIG. 1 is an exploded view of an aircraft launcher according to an embodiment of the present disclosure
  • FIG. 2 is a first direction view of the aircraft launcher of FIG. 1
  • FIG. 3 is a second direction view of the aircraft launcher of FIG.
  • the first direction and the second direction are respectively a front side and a back side of the aircraft launcher.
  • the aircraft launching frame includes a base 1 and a support frame 2, and the base 1 is rotatably coupled to the support frame 2.
  • the base 1 is used for placing an aircraft, and the support frame 2 is rotated to support one end of the base 1 such that the base 1 is at an angle to the ground (for example, 30°-150°), and one end of the base 1 is One end of the support frame 2 is a fulcrum, and one end of the support frame 2 as a fulcrum is away from the base 1.
  • the base 1 is composed of a plurality of rod-shaped cylinders and has a support area with a certain supporting area, and the area thereof may be slightly larger than the support area of the aircraft.
  • the support frame 2 includes a support portion 22, a positioning portion 21, and a pivot portion.
  • the support portion 22 is disposed on the side of the base 1
  • the positioning portion 21 is disposed on the other side of the base 1 and connected to the support portion 22
  • the support portion 22 and the positioning portion 21 are along The longitudinal direction of the support frame 2 is connected.
  • the pivoting portion (not shown) is rotatably coupled to the base 1 , and the pivoting portion connects the support portion 22 and the positioning portion 21 .
  • the support frame 2 is composed of two columnar structures and a connecting rod connected between the two columnar structures.
  • the pivoting portion is a through hole (formed on two columnar structures) disposed on the support frame 2, and correspondingly, the base 1 is also provided with a through hole 16 through which the rotating shaft passes through the two through holes.
  • the support frame 2 is rotatably coupled to the base 1.
  • the pivoting portion divides the two columnar structures into two parts, namely the support portion 22 and the positioning portion 21. Since the pivoting portion is located between the supporting portion 22 and the positioning portion 21, when the supporting frame 2 is rotated about the rotating shaft, the supporting portion 22 is opposite to the rotating direction of the positioning portion 21.
  • the positioning portion 21 can fix the aircraft to the base 1, for example, the positioning portion 21 cooperates with a shelter of the aircraft to fix the aircraft, preventing the aircraft from sliding down on the base 1.
  • the base 1 is provided with a receiving portion 13 for receiving the support frame 2 , and the receiving portion 13 is formed in the base 1 , and rotating the support frame 2 can The support frame 2 is received in the base 1 .
  • the accommodating portion 13 is a strip-shaped slot, and is disposed adjacent to both sides of the base 1 respectively.
  • the free end of the support portion 22 is rotated toward the base 1 , and when the plane of the support frame 2 coincides with the plane of the base 1 , the support frame 2 is received in the receiving portion 13 .
  • the base 1 is provided with a fixing portion 14 for fixing the support frame 2, and the support frame 2 is provided with a fitting portion 23 that cooperates with the fixing portion 14, and the support frame 2 is received in the base
  • the fixing portion 14 is in contact with the engaging portion 23.
  • the fixing portion 14 is a card slot disposed near the bottom end of the base 1;
  • the engaging portion 23 is a buckle, disposed near the bottom end of the support frame 2 (located at the lower end of the support frame 2) On the support bar).
  • the fixing portion 14 is rotated, and when the support frame 2 is received in the receiving portion 13, the fixing portion 14 is engaged with the engaging portion 23, and the support frame is realized. 2 fixed.
  • the lower end of the support frame 2 and the lower end of the base 1 are directly separated from the engaged fixing portion 14 and the engaging portion 23.
  • the fixing portion 14 is a buckle
  • the engaging portion 23 is a card slot.
  • a first limiting portion 12 is further disposed on the base 1 , and a position of the first limiting portion 12 on the base 1 is disposed adjacent to the positioning portion 21 .
  • the first limiting portion 12 is disposed in the receiving portion 13 and located below the rotating shaft. After the support frame 2 is rotated to a preset angle, the first limiting portion 12 can be in contact with the positioning portion 21 to prevent the support frame 2 from continuing to rotate.
  • the first limiting portion 12 includes a slot having a specific depth. The positioning portion 21 rotates from the plane of the base 1 until it contacts the first limiting portion 12, and the depth of the slot is The angle at which the positioning portion 21 is rotatable is related.
  • a telescopic structure 3 is provided, and the telescopic structure 3 can be expanded and contracted along the longitudinal direction of the base 1.
  • the telescopic structure 3 is arranged to increase the length of the aircraft launcher to accommodate different lengths of the aircraft 5 (see FIG. 4), and the effect of stable placement of different aircraft can be achieved.
  • the telescopic structure 3 is a U-shaped bar having a preset width.
  • the telescopic structure 3 is expanded and contracted with respect to the base 1 , and the accommodating portion 11 is disposed on the base 1 , and the accommodating portion 11 can accommodate the telescopic structure 3 .
  • the telescopic structure 3 is slidable within the accommodating portion 11.
  • the accommodating portion 11 is a chute formed in the base 1 .
  • it may also be a chute structure formed on the surface of the base 1.
  • the end of the telescopic structure 3 is provided with an elastic member 4, and the elastic member 4 is placed in the accommodating portion 11.
  • the telescopic structure 3 is slid into the accommodating portion 11 to compress the elastic member 4.
  • the elastic member 4 can assist in ejecting the telescopic structure 3.
  • the elastic member 4 can be connected to the base 1 at one end and the telescopic structure 3 at the other end.
  • the elastic member 4 is a spring.
  • the telescopic structure 3 is provided with a second limiting portion 12, and the supporting frame 2 is provided with a pressing portion 24 that cooperates with the second limiting portion 12.
  • the second limiting portion 12 is a groove formed on the telescopic structure 3, and the pressing portion 24 is a connecting rod disposed on the support frame 2.
  • the base 1 is provided with a fixed latching position 15 .
  • the fixed latching position 15 is a strip-shaped slot formed on the base 1 , and the nip portion 24 can be received in the strip-shaped slot (the support frame 2 is received In the base 1).
  • the second limiting portion 12 can be moved to the fixed latching portion 15 and exposed from the accommodating portion 13 .
  • the pressing portion 24 is pressed against the second limiting portion 12 to fix the telescopic structure 3 received in the receiving portion 11 .
  • the elastic member 4 can eject a part of the telescopic structure 3 from the receiving portion 11.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)

Abstract

L'invention concerne un lanceur d'aéronef, comprenant une base (1) et un cadre de support (2) relié rotatif à la base (1), la base (1) étant utilisée pour placer un aéronef, le cadre de support (2) étant tourné afin de maintenir une extrémité de la base (1) de telle sorte qu'un certain angle est formé entre la base (1) et le sol ; et le cadre de support (2) comprenant une partie de support (22) agencée sur un côté de la base (1), et une partie de positionnement (21) agencée de l'autre côté de la base (1) et reliée à la partie de support (22), la partie de positionnement (21) étant utilisée pour fixer l'aéronef à la base (1), et la partie de support (22) et la partie de positionnement (21) étant en liaison le long d'une direction de longueur du cadre de support (2).
PCT/CN2017/120386 2017-12-30 2017-12-30 Lanceur d'aéronef Ceased WO2019127565A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/CN2017/120386 WO2019127565A1 (fr) 2017-12-30 2017-12-30 Lanceur d'aéronef
CN201780005123.6A CN108513569B (zh) 2017-12-30 2017-12-30 飞行器发射架

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2017/120386 WO2019127565A1 (fr) 2017-12-30 2017-12-30 Lanceur d'aéronef

Publications (1)

Publication Number Publication Date
WO2019127565A1 true WO2019127565A1 (fr) 2019-07-04

Family

ID=63375246

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2017/120386 Ceased WO2019127565A1 (fr) 2017-12-30 2017-12-30 Lanceur d'aéronef

Country Status (2)

Country Link
CN (1) CN108513569B (fr)
WO (1) WO2019127565A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070252034A1 (en) * 2003-01-17 2007-11-01 The Insitu Group, Inc. Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and braking subsequent grip motion
US20130313357A1 (en) * 2010-07-14 2013-11-28 Arcturus UAV LLC UAV Launch Attachment Assembly and Launch System
WO2015073091A1 (fr) * 2013-08-27 2015-05-21 Engineered Arresting Systems Corporation Lanceur électrique de véhicule aérien sans pilote
CN204956949U (zh) * 2015-09-22 2016-01-13 上海南迅航空科技有限公司 轻便折叠式无人机发射架
CN106043731A (zh) * 2016-06-22 2016-10-26 浙江大学 改进型飞行器发射架
CN107176310A (zh) * 2017-06-27 2017-09-19 武汉华伍航空科技有限公司 一种无人机发射架
CN108039165A (zh) * 2017-10-31 2018-05-15 广西带路科技有限公司 一种支撑架

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8662441B2 (en) * 2011-02-16 2014-03-04 Sparton Corporation Unmanned aerial vehicle launch system
CN203094463U (zh) * 2013-01-09 2013-07-31 碳基科技股份有限公司 折叠式弹射架
CN104608937B (zh) * 2015-02-03 2017-03-01 河南省汇隆精密设备制造股份有限公司 一种多机型无人机液压蓄能弹射装置
CN205872508U (zh) * 2016-05-26 2017-01-11 江西洪都国际机电有限责任公司 一种可调节且自动回避式的发射装置剪切机构
CN206238747U (zh) * 2016-08-31 2017-06-13 杭州利帆实业有限公司 一种桌子

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070252034A1 (en) * 2003-01-17 2007-11-01 The Insitu Group, Inc. Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and braking subsequent grip motion
US20130313357A1 (en) * 2010-07-14 2013-11-28 Arcturus UAV LLC UAV Launch Attachment Assembly and Launch System
WO2015073091A1 (fr) * 2013-08-27 2015-05-21 Engineered Arresting Systems Corporation Lanceur électrique de véhicule aérien sans pilote
CN204956949U (zh) * 2015-09-22 2016-01-13 上海南迅航空科技有限公司 轻便折叠式无人机发射架
CN106043731A (zh) * 2016-06-22 2016-10-26 浙江大学 改进型飞行器发射架
CN107176310A (zh) * 2017-06-27 2017-09-19 武汉华伍航空科技有限公司 一种无人机发射架
CN108039165A (zh) * 2017-10-31 2018-05-15 广西带路科技有限公司 一种支撑架

Also Published As

Publication number Publication date
CN108513569B (zh) 2021-06-18
CN108513569A (zh) 2018-09-07

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