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CN110539877A - Rotatable flexible wing connection structure - Google Patents

Rotatable flexible wing connection structure Download PDF

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Publication number
CN110539877A
CN110539877A CN201910771425.5A CN201910771425A CN110539877A CN 110539877 A CN110539877 A CN 110539877A CN 201910771425 A CN201910771425 A CN 201910771425A CN 110539877 A CN110539877 A CN 110539877A
Authority
CN
China
Prior art keywords
inner cylinder
middle shaft
boss
limiting
hole
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.)
Pending
Application number
CN201910771425.5A
Other languages
Chinese (zh)
Inventor
杨文�
唐克兵
冯若琪
李友龙
宋嘉亮
高彬
闫蕾
肖娟
桂天才
顾汝佳
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.)
Chengdu Aircraft Industrial Group Co Ltd
Original Assignee
Chengdu Aircraft Industrial Group 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 Chengdu Aircraft Industrial Group Co Ltd filed Critical Chengdu Aircraft Industrial Group Co Ltd
Priority to CN201910771425.5A priority Critical patent/CN110539877A/en
Publication of CN110539877A publication Critical patent/CN110539877A/en
Pending legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • B64C3/56Folding or collapsing to reduce overall dimensions of aircraft

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

Abstract

The application relates to a rotatable and telescopic wing connecting structure, and belongs to the field of airplane structural design. The wing is connected with the body and the wings through the structure, so that the wings can be conveniently lifted to a certain height and rotated by a certain angle along a certain direction. When the airplane is transported or stored, the wing can be quickly lifted and rotated to be parallel to the direction of the airplane body through the structure, and the space for packaging, transporting and storing is reduced; when the airplane is used, the wings can be rapidly rotated in place through the structure, and the installation and debugging time of the airplane is saved. Meanwhile, the structure has the function of limiting the lifting height and the rotating angle, can prevent the wings from being damaged due to misoperation in the lifting or rotating process, can be quickly positioned, and is convenient to operate.

Description

Rotatable flexible wing connection structure
Technical Field
The application relates to a telescopic combined structure which is suitable for a small airplane and has the functions of connecting a wing body without separation and rotating, and belongs to the field of airplane structural design.
Background
In the existing design of the connection structure of the wings and the fuselage of the airplane, the wings and the fuselage are both of a separation structure, and the occupied space in the processes of packaging, transportation and storage is particularly large or the airplane is inconvenient to use in the transition. Particularly for small-sized airplanes, the airplanes are usually transported and transferred by automobiles, and the separation of the wings and the airplane body often causes the difficulties of inaccurate positioning, difficult re-installation, more operating and maintaining personnel and long time consumption.
disclosure of Invention
The purpose of the invention is: to above-mentioned prior art's requirement, provide a rotatable extending structure suitable for unmanned aerial vehicle for connect the wing fuselage, reduce the aircraft at activity in-process packing such as transition, transportation and storage space, save installation and debugging time, the use of the aircraft of being convenient for is maintained.
The technical scheme adopted by the invention for solving the technical problems is as follows:
A wing connecting structure capable of rotating and stretching comprises an outer barrel, an inner barrel, a middle shaft and a machine body fixing support, wherein a limiting groove is formed in an outer barrel through hole of the outer barrel, and an outer barrel limiting boss is arranged at the bottom of the outer barrel; the inner cylinder through hole of the inner cylinder is a square hole, the lower end of the inner cylinder through hole is provided with an inner cylinder lower limiting boss, the outer wall of the inner cylinder is provided with a rotary limiting boss, and the upper end of the inner cylinder is provided with an inner cylinder upper limiting platform; the middle shaft is a square shaft, and the upper end of the middle shaft is provided with a middle shaft upper limiting boss; the middle shaft is matched with the through hole of the inner cylinder, the middle shaft and the inner cylinder can slide along the inner cylinder in a sleeving manner, and the upper limiting lug boss of the middle shaft is limited at the lower limiting lug boss of the inner cylinder; the inner cylinder is sleeved in the outer cylinder in a matching way with the through hole of the outer cylinder, the inner cylinder can slide along the outer cylinder, and the upper limit platform of the inner cylinder is limited on the limit boss of the outer cylinder; the rotary limiting boss is matched with a limiting groove in the through hole of the outer barrel, and the rotary limiting boss can rotate in the limiting groove; the lower end of the middle shaft is fixedly connected with the machine body fixing support.
The lower end of the middle shaft is provided with a middle shaft lower boss, and the middle shaft is fixedly connected with the machine body fixing support through the middle shaft lower boss.
The middle shaft lower boss is provided with a pin hole, and the middle shaft is fixedly connected with the machine body through a pin shaft inserted into the pin hole.
The pin shaft is a quick-release pin.
And the upper end of the outer barrel is provided with an ejection-preventing bush for limiting the inner barrel to eject the outer barrel.
the application has the following beneficial effects:
The wing body can be telescopic and rotatable without being separated by the structure, the outer cylinder and the inner cylinder can rotate by a certain angle, the inner cylinder and the middle shaft can not rotate, and the outer cylinder and the inner cylinder as well as the inner cylinder and the middle shaft can axially extend by a certain distance, so that the connection of the wing body can not be separated, and the function of lifting the wing to a certain height and rotating to a certain angle can be realized. When the airplane is transported or stored, the wing can be quickly lifted and rotated to be parallel to the direction of the airplane body through the structure, and the space for packaging, transporting and storing is reduced; when the airplane is used, the wings can be rapidly rotated in place through the structure, and the installation and debugging time of the airplane is saved. Meanwhile, the structure has the function of limiting the lifting height and the rotating angle, can prevent the wings from being damaged due to misoperation in the lifting or rotating process, can be quickly positioned, and is convenient to operate.
drawings
the specific structure of the present invention is given by the following embodiments and the drawings thereof. But do not limit the invention to the scope of the described embodiments.
FIG. 1 is a schematic non-rotating view of an aircraft wing.
FIG. 2 is a schematic view of an aircraft wing rotation.
Fig. 3 is a view showing a state where the wing is not lifted.
Fig. 4 is a view of the wing in a raised condition.
figure 5 is a view of the wing raised and rotated 90 counter-clockwise.
Fig. 6 is an isometric view of the present application.
Fig. 7 is an exploded schematic view of the present application.
Fig. 8 is a schematic view of the outer cylinder.
FIG. 9 is a schematic view of the inner barrel.
Fig. 10 is a schematic view of the medial axis.
In the figure: 1. the novel anti-ejection mechanism comprises an outer cylinder, 2 parts of an inner cylinder, 3 parts of a center shaft, 4 parts of a machine body fixing support, 5 parts of an anti-ejection bush, 6 parts of a quick-release pin, 7 parts of an outer cylinder through hole, 8 parts of an outer cylinder limiting groove, 9 parts of an outer cylinder limiting boss, 10 parts of an inner cylinder lower limiting boss, 11 parts of an inner cylinder through hole, 12 parts of an inner cylinder rotation limiting boss, 13 parts of an inner cylinder upper limiting boss, 14 parts of a center shaft square shaft, 15 parts of a center shaft upper limiting boss, 16 parts of a pin hole and 17 parts of.
Detailed Description
Example 1
The utility model provides a wing connecting structure capable of rotating and stretching, which comprises an outer cylinder 1, an inner cylinder 2, a middle shaft 3 and a fuselage fixing support 4, wherein a limiting groove 8 is arranged in an outer cylinder through hole 7 of the outer cylinder 1, and an outer cylinder limiting boss 9 is arranged at the bottom; an inner cylinder through hole 11 of the inner cylinder 2 is a square hole, an inner cylinder lower limiting boss 10 is arranged at the lower end of the inner cylinder through hole 11, a rotation limiting boss 12 is arranged on the outer wall of the inner cylinder 2, and an inner cylinder upper limiting platform 13 is arranged at the upper end of the inner cylinder 2; the middle shaft is a square shaft, and the upper end of the middle shaft is provided with a middle shaft upper limiting boss 15; the middle shaft 3 is matched with the through hole 11 of the inner cylinder, is sleeved in the inner cylinder and can slide along the inner cylinder, and the upper limit boss 15 of the middle shaft is limited on the lower limit boss 10 of the inner cylinder; the inner cylinder is sleeved in the outer cylinder in a matching way with the through hole 7 of the outer cylinder, the inner cylinder can slide along the outer cylinder, and the upper limit platform 13 of the inner cylinder is limited on the limit boss 9 of the outer cylinder; the rotary limiting boss 12 is matched with the limiting groove 8 in the through hole 7 of the outer cylinder, and the rotary limiting boss 12 can rotate in the limiting groove 8; the lower end of the middle shaft 3 is fixedly connected with a machine body fixed support 4.
Example 2
The utility model provides a wing connecting structure capable of rotating and stretching, which comprises an outer cylinder 1, an inner cylinder 2, a middle shaft 3 and a fuselage fixing support 4, wherein a limiting groove 8 is arranged in an outer cylinder through hole 7 of the outer cylinder 1, and an outer cylinder limiting boss 9 is arranged at the bottom; an inner cylinder through hole 11 of the inner cylinder 2 is a square hole, an inner cylinder lower limiting boss 10 is arranged at the lower end of the inner cylinder through hole 11, a rotation limiting boss 12 is arranged on the outer wall of the inner cylinder 2, and an inner cylinder upper limiting platform 13 is arranged at the upper end of the inner cylinder 2; the middle shaft is a square shaft, and the upper end of the middle shaft is provided with a middle shaft upper limiting boss 15; the middle shaft 3 is matched with the through hole 11 of the inner cylinder, is sleeved in the inner cylinder and can slide along the inner cylinder, and the upper limit boss 15 of the middle shaft is limited on the lower limit boss 10 of the inner cylinder; the inner cylinder is sleeved in the outer cylinder in a matching way with the through hole 7 of the outer cylinder, the inner cylinder can slide along the outer cylinder, and the upper limit platform 13 of the inner cylinder is limited on the limit boss 9 of the outer cylinder; the rotary limiting boss 12 is matched with the limiting groove 8 in the through hole 7 of the outer cylinder, and the rotary limiting boss 12 can rotate in the limiting groove 8; the lower end of the middle shaft 3 is fixedly connected with a machine body fixed support 4. The lower end of the middle shaft 3 is provided with a middle shaft lower boss 17, and the middle shaft 3 is fixedly connected with the machine body fixing support 4 through the middle shaft lower boss 17. The middle shaft lower boss 17 is provided with a pin hole 16, and the middle shaft is fixedly connected with the machine body by inserting a quick-release pin 5 into the pin hole 16.
Example 3
The installation implementation steps of the wing-body connection non-disengagement rotatable telescopic structure are as follows:
the outer cylinder and the rib of the wing are integrally designed, the outer cylinder 1 is connected with the wing, and the outer cylinder 1 is provided with an outer cylinder through hole 7, a limiting groove 8 and an outer cylinder limiting boss 9;
The inner cylinder 2 is arranged in the outer cylinder through hole 7, then the middle shaft 3 is arranged in the inner cylinder through hole 11, and the anti-ejection bush 5 is embedded at the upper end of the outer cylinder through hole 7 and used for limiting the inner cylinder 2 to eject out of the outer cylinder and protecting the inner part of the outer cylinder;
Connecting the wings with the fuselage, simultaneously installing the lower end of the middle shaft 7 into the fuselage fixed support 4, and inserting the quick-release pin 6 into the pin hole 16, thereby completing the combination of the whole structure;
When the wings need to be selected, the wings are lifted, as the outer cylinder 1 moves upwards, the limiting boss 9 at the lower end of the outer cylinder contacts with the upper limiting boss 13 of the inner cylinder to drive the inner cylinder 2 to move upwards, and then the lower limiting boss 10 of the inner cylinder contacts with the upper limiting boss of the middle shaft, but as the middle shaft lower boss 17 is fixed on the fuselage fixed support 4 through the quick-release pin 6, the middle shaft cannot move upwards, the wings cannot be lifted continuously, the height limiting effect is achieved, and at the moment, the lower wing surfaces of the wings are higher than the rotatable wings on the upper surface of the fuselage; when the wing rotates, the inner cylinder 2 is connected with the middle shaft 3, and the middle shaft 3 is connected with the fuselage fixing support 4 through the square shaft matched with the square hole, so that the inner cylinder and the middle shaft are not rotatable. The rotary limiting boss 12 can only rotate in the limiting groove 8, and the design is that the inner cylinder rotary limiting boss 12 is tightly attached to one side of the limiting groove 8 according to the initial installation position, so that the outer cylinder can only rotate in the clockwise or anticlockwise direction, and the wing can only rotate in a certain direction due to the fact that the limiting groove 8 only occupies a certain angle in the circumference and can be designed;
The wing-body connection can be realized to be non-detachable and rotatable according to the steps. When the position of the wing needs to be restored, the wing only needs to be rotated in the opposite direction to be in place, and then the wing is put down, so that the wing can be quickly restored and installed.
The inner cylinder and the middle shaft can be connected in a triangular or polygonal shaft matching mode, and the purposes of only sliding and non-rotating are achieved. The middle shaft and the machine body can also adopt the same or other connection forms to realize the purposes of only sliding and non-rotation.

Claims (5)

1. A wing connecting structure capable of rotating and stretching is characterized by comprising an outer cylinder (1), an inner cylinder (2), a middle shaft (3) and a machine body fixing support (4), wherein a limiting groove (8) is arranged in an outer cylinder through hole (7) of the outer cylinder (1), and an outer cylinder limiting boss (9) is arranged at the bottom of the outer cylinder through hole; an inner cylinder through hole (11) of the inner cylinder (2) is a square hole, an inner cylinder lower limiting boss (10) is arranged at the lower end of the inner cylinder through hole (11), a rotary limiting boss (12) is arranged on the outer wall of the inner cylinder (2), and an inner cylinder upper limiting platform (13) is arranged at the upper end of the inner cylinder (2); the middle shaft is a square shaft, and the upper end of the middle shaft is provided with a middle shaft upper limiting boss 15; the middle shaft (3) is matched with the through hole (11) of the inner cylinder, the middle shaft and the inner cylinder can slide along the inner cylinder in a sleeving manner, and the upper limiting lug boss 15 of the middle shaft is limited on the lower limiting lug boss (10) of the inner cylinder; the inner cylinder is sleeved in the outer cylinder in a matching way with the through hole (7) of the outer cylinder, the inner cylinder can slide along the outer cylinder, and the upper limiting platform (13) of the inner cylinder is limited on the limiting boss (9) of the outer cylinder; the rotary limiting boss (12) is matched with the limiting groove (8) in the through hole (7) of the outer barrel, and the rotary limiting boss (12) can rotate in the limiting groove (8); the lower end of the middle shaft (3) is fixedly connected with a machine body fixed support (4).
2. A rotatable and retractable wing connecting structure as claimed in claim 1, wherein a middle shaft lower boss (17) is provided at the lower end of the middle shaft (3), and the middle shaft (3) is fixedly connected with the fuselage fixing support (4) through the middle shaft lower boss (17).
3. a rotatable and retractable wing connecting structure as claimed in claim 2, wherein the lower boss (17) of the central shaft is provided with a pin hole (16), and the central shaft is fixedly connected with the fuselage by inserting a pin shaft into the pin hole (16).
4. A rotationally extendable wing connection according to claim 3, characterized in that the pin is a quick release pin (5).
5. A rotatably telescopic wing connection according to claim 1, characterized in that the outer cylinder (1) is provided at its upper end with an anti-ejection bush (5) for limiting the ejection of the inner cylinder (2) from the outer cylinder (1).
CN201910771425.5A 2019-08-21 2019-08-21 Rotatable flexible wing connection structure Pending CN110539877A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910771425.5A CN110539877A (en) 2019-08-21 2019-08-21 Rotatable flexible wing connection structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910771425.5A CN110539877A (en) 2019-08-21 2019-08-21 Rotatable flexible wing connection structure

Publications (1)

Publication Number Publication Date
CN110539877A true CN110539877A (en) 2019-12-06

Family

ID=68711843

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910771425.5A Pending CN110539877A (en) 2019-08-21 2019-08-21 Rotatable flexible wing connection structure

Country Status (1)

Country Link
CN (1) CN110539877A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114715393A (en) * 2022-06-07 2022-07-08 成都睿铂科技有限责任公司 Composite wing unmanned aerial vehicle
CN115636079A (en) * 2022-12-21 2023-01-24 中国航空工业集团公司沈阳空气动力研究所 High-altitude long-endurance unmanned aerial vehicle layout with ultrahigh lift-drag ratio

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4998689A (en) * 1989-07-14 1991-03-12 Rockwell International Corporation 90 degree rotation aircraft wing
NO941502D0 (en) * 1993-04-27 1994-04-25 Hughes Aircraft Co
AU2012202580A1 (en) * 2012-04-23 2013-12-05 Roger William Ivens Improvements in wing design using natural air pressure
GB201608571D0 (en) * 2015-06-05 2016-06-29 Lockheed Corp Deployment mechanism
CN107571986A (en) * 2017-09-12 2018-01-12 歌尔科技有限公司 Foldable propeller
CN109094769A (en) * 2017-06-20 2018-12-28 成都飞机工业(集团)有限责任公司 Mini foldable unmanned plane
CN209263801U (en) * 2018-11-28 2019-08-16 成都云鼎智控科技有限公司 Slide rail type fold mechanism for folded wing

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4998689A (en) * 1989-07-14 1991-03-12 Rockwell International Corporation 90 degree rotation aircraft wing
NO941502D0 (en) * 1993-04-27 1994-04-25 Hughes Aircraft Co
AU2012202580A1 (en) * 2012-04-23 2013-12-05 Roger William Ivens Improvements in wing design using natural air pressure
GB201608571D0 (en) * 2015-06-05 2016-06-29 Lockheed Corp Deployment mechanism
US20160355250A1 (en) * 2015-06-05 2016-12-08 Lockheed Martin Corporation Deployment mechanism
CN109094769A (en) * 2017-06-20 2018-12-28 成都飞机工业(集团)有限责任公司 Mini foldable unmanned plane
CN107571986A (en) * 2017-09-12 2018-01-12 歌尔科技有限公司 Foldable propeller
WO2019051993A1 (en) * 2017-09-12 2019-03-21 歌尔科技有限公司 Foldable propeller
CN209263801U (en) * 2018-11-28 2019-08-16 成都云鼎智控科技有限公司 Slide rail type fold mechanism for folded wing

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114715393A (en) * 2022-06-07 2022-07-08 成都睿铂科技有限责任公司 Composite wing unmanned aerial vehicle
CN115636079A (en) * 2022-12-21 2023-01-24 中国航空工业集团公司沈阳空气动力研究所 High-altitude long-endurance unmanned aerial vehicle layout with ultrahigh lift-drag ratio

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Application publication date: 20191206