CN102602529A - Folding full-motion horizontal tail mechanism - Google Patents

Folding full-motion horizontal tail mechanism Download PDF

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Publication number
CN102602529A
CN102602529A CN2011104565479A CN201110456547A CN102602529A CN 102602529 A CN102602529 A CN 102602529A CN 2011104565479 A CN2011104565479 A CN 2011104565479A CN 201110456547 A CN201110456547 A CN 201110456547A CN 102602529 A CN102602529 A CN 102602529A
Authority
CN
China
Prior art keywords
horizontal tail
rotating shaft
horizontal
hand rotation
rotation platform
Prior art date
Application number
CN2011104565479A
Other languages
Chinese (zh)
Inventor
申强
刘学庆
李兵
邓宏彬
贺伟
余国斌
邹燕梅
张忠伟
李�杰
Original Assignee
北京理工大学
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 北京理工大学 filed Critical 北京理工大学
Priority to CN2011104565479A priority Critical patent/CN102602529A/en
Publication of CN102602529A publication Critical patent/CN102602529A/en

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Abstract

The invention provides a folding full-motion horizontal tail mechanism, and belongs to the technical field of folding-wing unmanned aircrafts. The mechanism comprises a left horizontal tail, a left turntable, a horizontal tail connection body, a right turntable, a right horizontal tail, torsional spring covers, a pressing screw, torsional springs, horizontal tail rotating shafts and a locking mechanism, wherein two rotating shaft mounting holes which are symmetric in the transverse direction are formed in the horizontal tail connection body; an included angle between the axis of each mounting hole and the horizontal plane is 55.5 degrees; after the horizontal tail connection body is fixedly connected with the left turntable and the right turntable, the rear end face of the horizontal tail connection body and the rear end face of a machine body form a 45-degree angle; rotating shaft mounting sleeves matched with the horizontal tail rotating shafts are arranged on the left horizontal tail and the right horizontal tail; included angles between the central axis of each rotating shaft mounting sleeve and the wing plane as well as between the central axis of each rotating shaft mounting sleeve and the wing chord direction are 45 degrees; the torsional springs are arranged on the horizontal tail rotating shafts; and the locking mechanism makes the horizontal tail rotating shafts rotate by 105 degrees and locks the horizontal tail rotating shafts, so that the horizontal tails rotate to a position vertical to the side face of the machine body from the position close to the side face of the machine body. The mechanism is connected reliably, has a simple structure, and is unfolded quickly and operated easily.

Description

Collapsible flying tail mechanism
Technical field
The present invention relates to the folding wings of unmanned vehicle, be specifically related to a kind of collapsible flying tail mechanism, belong to folding wings unmanned vehicle technical field of structures.
Background technology
Unmanned vehicle is the not manned craft of controlling through radio robot or airborne computer stored program controlled.Unmanned vehicle is simple in structure, use cost is low, not only can accomplish the task that manned aircraft is carried out, and more is applicable to the task that people's aircraft should not be carried out, like scouting, air rescue commander and the remote sensing monitoring of hazardous location.
Mainly on the market now use following three kinds: fixedly aerofoil profile unmanned plane, pilotless helicopter and driverless operation dirigible; Compare with these ripe unmanned planes, the largest benefit of folding wings unmanned vehicle is saved the space exactly, and is easy to carry and transport; Improved the convenience of unmanned vehicle greatly; But because evening is wanted in its research starting, and technology is comparatively complicated, hereat in use present commercial market, also is in space state basically.
Summary of the invention
In view of this, the invention provides a kind of collapsible flying tail mechanism, can realize that empennage moves to horizontal development from vertical folded state in the folding wings unmanned vehicle through once rotating release motion.
A kind of collapsible flying tail mechanism; Comprise fuselage, left horizontal tail, left-hand rotation platform, horizontal tail connector, right-hand rotation platform, right horizontal tail, torsion spring lid, press spiral shell, torsion spring, horizontal tail rotating shaft and catch gear; Wherein, Be processed with two symmetrical rotating shaft mounting holes on the horizontal tail connector, the axis of mounting hole and the angle of horizontal surface are 55.5 °, also are processed with locking pin-and-hole and horizontal tail rotating shaft mounting hole on the horizontal tail connector and connect; Catch gear comprises compression spring, locking key seat and locking pin; Be processed with the rotating shaft installation sleeve that cooperates with the horizontal tail rotating shaft on left side horizontal tail and the right horizontal tail, the angle of rotating shaft installation sleeve central axis and wing plane and chordwise is 45,
Its connection and assembly relation are following: the medial surface of left-hand rotation platform and right-hand rotation platform is captiveed joint with the left and right sides of horizontal tail connector respectively, and the horizontal tail rotating shaft mounting hole position of horizontal tail connector extends outward the end face of left-hand rotation platform and right-hand rotation platform; The horizontal tail connector is installed in fuselage interior through left-hand rotation platform and right-hand rotation platform, and the aft end face of horizontal tail connector becomes 45 with the aft end face of fuselage; Two horizontal tail rotating shafts are installed in respectively in the rotating shaft mounting hole on the horizontal tail connector; The horizontal tail connector is stretched out in the lower end of horizontal tail rotating shaft; Fixed by torsion spring lid and pressure spiral shell behind the suit torsion spring of upper end, torsion spring one end is fixed in the horizontal tail rotating shaft, and the other end is fixed on the horizontal tail connector; A locking key seat is respectively installed in the inboard of left-hand rotation platform and right-hand rotation platform, and locking pin is installed on the locking key seat through compression spring and is positioned at the locking pin-and-hole of horizontal tail connector; Weld behind left side horizontal tail and the lower end suit of right horizontal tail through rotating shaft installation sleeve on it and horizontal tail rotating shaft.
Principle of work: under the folded state; The aerofoil of left side horizontal tail and right horizontal tail is close to the fuselage side and spanwise is parallel to the aircraft central axis direction; After removing the constraint of left horizontal tail and right horizontal tail; The horizontal tail rotating shaft makes the mounting hole axis rotation around the shaft of left horizontal tail and right horizontal tail and launches under the effect of torsion spring, behind 103 ° of angles of horizontal tail rotating shaft rotation, locking pin inserts in the spacing hole in the horizontal tail rotating shaft horizontal tail rotating shaft is locked; The left horizontal tail in horizontal tail rotating shaft this moment and the aerofoil of right horizontal tail are parallel to the aircraft central axis direction perpendicular to fuselage side and chordwise, thereby when aircraft need be controlled, enough big pitch control subsystem moment are provided.
In addition, in fuselage interior driver train is set, drive mechanism left-hand rotation platform and right-hand rotation platform rotate around the central axis of himself, and then realize the adjustment of left horizontal tail and right horizontal tail attitude.
Beneficial effect: the present invention can guarantee fin through the design of horizontal tail connector and setting angle thereof, and it moves to horizontal development from vertical folded state through the releasing action realization, has simplified the actuating mechanism of folding wings; The present invention simultaneously is simple in structure, and connection is reliable, launches rapidly, and locking is firm, and in light weight, volume is little, is easy to handle; The present invention has accumulated technical foundation for the development of folding wings unmanned vehicle.
Description of drawings
Fig. 1 is a folded state scheme drawing of the present invention;
Fig. 2 is a deployed condition scheme drawing of the present invention;
Fig. 3 is expansion of the present invention and lockout mechanism assembly relation scheme drawing;
Fig. 4 is a horizontal tail connector structural representation of the present invention;
Fig. 5 is the structural front view of the present invention's left side horizontal tail or right horizontal tail;
Fig. 6 is the structure left view of the present invention's left side horizontal tail or right horizontal tail.
Wherein, 1-fuselage, 2-left side horizontal tail, 3-left-hand rotation platform, 4-horizontal tail connector, 5-right-hand rotation platform, the right horizontal tail of 6-, 7-torsion spring lid, 8-press spiral shell, 10-torsion spring, the rotating shaft of 11-horizontal tail, 12-compression spring, 13-locking key seat, 14-locking pin.
The specific embodiment
Describe the present invention below in conjunction with accompanying drawing.
Collapsible flying tail of the present invention mechanism; Comprise fuselage 1, left horizontal tail 2, left-hand rotation platform 3, horizontal tail connector 4, right-hand rotation platform 5, right horizontal tail 6, torsion spring lid 7, press spiral shell 8, torsion spring 10, horizontal tail rotating shaft 11 and catch gear; Wherein, like accompanying drawing 4, be processed with two symmetrical rotating shaft mounting holes on the horizontal tail connector 4; The axis of mounting hole and the angle of horizontal surface are 55.5 °, also are processed with locking pin-and-hole and horizontal tail rotating shaft 11 mounting holes on the horizontal tail connector 4 and connect; Catch gear comprises compression spring 12, locking key seat 13 and locking pin 14; Shown in accompanying drawing 5 and 6, be processed with the rotating shaft installation sleeve that cooperates with horizontal tail rotating shaft 11 on left horizontal tail 2 and the right horizontal tail 6, the angle of rotating shaft installation sleeve central axis and wing plane and chordwise is 45,
Its connection and assembly relation are following: shown in accompanying drawing 3; The medial surface of left-hand rotation platform 3 and right-hand rotation platform 5 is captiveed joint with the left and right sides of horizontal tail connector 4 respectively, and the horizontal tail rotating shaft 11 mounting hole positions of horizontal tail connector 4 extend outward the end face of left-hand rotation platform 3 and right-hand rotation platform 5; Horizontal tail connector 4 is installed in fuselage 1 inside through left-hand rotation platform 3 and right-hand rotation platform 5, and the aft end face of horizontal tail connector 4 becomes 45 with the aft end face of fuselage 1; Two horizontal tail rotating shafts 11 are installed in respectively in the rotating shaft mounting hole on the horizontal tail connector 4; Horizontal tail connector 4 is stretched out in the lower end of horizontal tail rotating shaft 11; Suit torsion spring 10 backs in upper end are fixing with pressure spiral shell 8 by torsion spring lid 7, and torsion spring 10 1 ends are fixed in the horizontal tail rotating shaft 11, and the other end is fixed on the horizontal tail connector 4; A locking key seat 13 is respectively installed in the inboard of left-hand rotation platform 3 and right-hand rotation platform 5, and locking pin 14 is installed on the locking key seat 13 through compression spring and is positioned at the locking pin-and-hole of horizontal tail connector 4; Weld behind left side horizontal tail 2 and the lower end suit of right horizontal tail 6 through rotating shaft installation sleeve on it and horizontal tail rotating shaft 11.
Principle of work: shown in accompanying drawing 1; Under the folded state; The aerofoil of left side horizontal tail 2 and right horizontal tail 6 is close to the fuselage side and spanwise is parallel to the aircraft central axis direction; After removing the constraint of left horizontal tail 2 and right horizontal tail 6, horizontal tail rotating shaft 11 makes left horizontal tail 2 and mounting hole axis rotation around the shaft of right horizontal tail 6 and expansion under the effect of torsion spring 10, behind 103 ° of angles of horizontal tail rotating shaft 11 rotations; In the spacing hole that locking pin 14 inserts in the horizontal tail rotating shaft 11 horizontal tail rotating shaft 11 is locked; The left horizontal tail 2 in horizontal tail rotating shaft this moment 11 and the aerofoil of right horizontal tail 6 are parallel to the aircraft central axis direction perpendicular to fuselage side and chordwise, thereby when aircraft need be controlled, enough big pitch control subsystem moment are provided, shown in accompanying drawing 2.
In addition, at fuselage 1 set inside driver train, drive mechanism left-hand rotation platform 3 rotates with the central axis of right-hand rotation platform 5 around himself, and then realizes the adjustment of left horizontal tail 2 and right horizontal tail 6 attitudes.
In sum, more than being merely preferred embodiment of the present invention, is not to be used to limit protection scope of the present invention.All within spirit of the present invention and principle, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.

Claims (3)

1. collapsible flying tail mechanism; Comprise fuselage (1), left horizontal tail (2), left-hand rotation platform (3), horizontal tail connector (4), right-hand rotation platform (5), right horizontal tail (6), torsion spring lid (7), press spiral shell (8), torsion spring (10), horizontal tail rotating shaft (11) and catch gear; It is characterized in that being processed with on the said horizontal tail connector (4) two symmetrical rotating shaft mounting holes; The axis of mounting hole and the angle of horizontal surface are 55.5 °, also are processed with locking pin-and-hole and horizontal tail rotating shaft (11) mounting hole on the horizontal tail connector (4) and connect; Catch gear comprises compression spring (12), locking key seat (13) and locking pin (14); Be processed with the rotating shaft installation sleeve that cooperates with horizontal tail rotating shaft (11) on left side horizontal tail (2) and the right horizontal tail (6), the angle of rotating shaft installation sleeve central axis and wing plane and chordwise is 45,
Its annexation is following: the medial surface of left-hand rotation platform (3) and right-hand rotation platform (5) is captiveed joint with the left and right sides of horizontal tail connector (4) respectively, and horizontal tail rotating shaft (11) the mounting hole position of horizontal tail connector (4) extends outward the end face of left-hand rotation platform (3) and right-hand rotation platform (5); Horizontal tail connector (4) is installed in fuselage (1) inside through left-hand rotation platform (3) and right-hand rotation platform (5), and the aft end face of horizontal tail connector (4) becomes 45 with the aft end face of fuselage (1); Two horizontal tail rotating shafts (11) are installed in respectively in the rotating shaft mounting hole on the horizontal tail connector (4); Horizontal tail connector (4) is stretched out in the lower end of horizontal tail rotating shaft (11); Upper end suit torsion spring (10) back is by torsion spring lid (7) and press spiral shell (8) fixing; Torsion spring (10) one ends are fixed in the horizontal tail rotating shaft (11), and the other end is fixed on the horizontal tail connector (4); A locking key seat (13) is respectively installed in the inboard of left-hand rotation platform (3) and right-hand rotation platform (5), and locking pin (14) is installed in the locking pin-and-hole that horizontal tail connector (4) was gone up and be positioned to locking key seat (13) through compression spring (12); Weld behind left side horizontal tail (2) and the lower end suit of right horizontal tail (6) through rotating shaft installation sleeve on it and horizontal tail rotating shaft (11).
2. collapsible flying tail as claimed in claim 1 mechanism; It is characterized in that said left horizontal tail (2) and right horizontal tail (6) are under folded state; Its aerofoil is close to the fuselage side and spanwise is parallel to the aircraft central axis direction; Behind 103 ° of angles of horizontal tail rotating shaft (11) rotation; Locking pin (14) inserts in the spacing hole in the horizontal tail rotating shaft (11) horizontal tail rotating shaft (11) is locked, and the left horizontal tail (2) in the horizontal tail rotating shaft (11) and the aerofoil of right horizontal tail (6) are parallel to the aircraft central axis direction perpendicular to fuselage side and chordwise.
3. collapsible flying tail as claimed in claim 1 mechanism is characterized in that said fuselage (1) set inside driver train, and drive mechanism left-hand rotation platform (3) and right-hand rotation platform (5) are around the central axis rotation of himself.
CN2011104565479A 2011-12-30 2011-12-30 Folding full-motion horizontal tail mechanism CN102602529A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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Application Number Priority Date Filing Date Title
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102849206A (en) * 2012-10-30 2013-01-02 河北科技大学 Wing folding-unfolding mechanism for small unmanned aerial vehicle with folding wings
CN103010453A (en) * 2012-12-27 2013-04-03 北京理工大学 Unmanned plane folded wing unfolding and locking device
CN103224021A (en) * 2013-03-19 2013-07-31 北京航空航天大学 Pneumatic folding apparatus of variable-wing sweepback angle suitable for aeronaval unmanned aerial vehicle
CN103825078A (en) * 2014-03-24 2014-05-28 上海航天电子通讯设备研究所 Automatic locking device for space-borne antenna
CN103935512A (en) * 2014-05-12 2014-07-23 马轶 High endurable multi-rotor craft
CN107651168A (en) * 2017-09-30 2018-02-02 肇庆高新区国专科技有限公司 A kind of unmanned plane wingfold mechanism and method for folding

Citations (5)

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Publication number Priority date Publication date Assignee Title
US2674422A (en) * 1949-05-12 1954-04-06 Pellarini Luigi Folding wing for roadable aircraft
US4471923A (en) * 1981-08-22 1984-09-18 Vereinigte Flugtechnische Werke Mbb Unmanned aircraft
US5829715A (en) * 1996-04-19 1998-11-03 Lockheed Martin Vought Systems Corp. Multi-axis unfolding mechanism with rate controlled synchronized movement
WO2011014106A1 (en) * 2009-07-31 2011-02-03 Общество С Ограниченной Ответственностью "Научно-Производственная Фирма "Сигма-Тс" Airplane with folding wings and device for folding the wings of an airplane
CN201895770U (en) * 2010-09-29 2011-07-13 贵州航天控制技术有限公司 Locking and unlocking mechanism for aircraft airfoil

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2674422A (en) * 1949-05-12 1954-04-06 Pellarini Luigi Folding wing for roadable aircraft
US4471923A (en) * 1981-08-22 1984-09-18 Vereinigte Flugtechnische Werke Mbb Unmanned aircraft
US5829715A (en) * 1996-04-19 1998-11-03 Lockheed Martin Vought Systems Corp. Multi-axis unfolding mechanism with rate controlled synchronized movement
WO2011014106A1 (en) * 2009-07-31 2011-02-03 Общество С Ограниченной Ответственностью "Научно-Производственная Фирма "Сигма-Тс" Airplane with folding wings and device for folding the wings of an airplane
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Title
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102849206A (en) * 2012-10-30 2013-01-02 河北科技大学 Wing folding-unfolding mechanism for small unmanned aerial vehicle with folding wings
CN102849206B (en) * 2012-10-30 2014-09-03 河北科技大学 Wing folding-unfolding mechanism for small unmanned aerial vehicle with folding wings
CN103010453A (en) * 2012-12-27 2013-04-03 北京理工大学 Unmanned plane folded wing unfolding and locking device
CN103224021A (en) * 2013-03-19 2013-07-31 北京航空航天大学 Pneumatic folding apparatus of variable-wing sweepback angle suitable for aeronaval unmanned aerial vehicle
CN103224021B (en) * 2013-03-19 2015-03-11 北京航空航天大学 Pneumatic folding apparatus of variable-wing sweepback angle suitable for aeronaval unmanned aerial vehicle
CN103825078A (en) * 2014-03-24 2014-05-28 上海航天电子通讯设备研究所 Automatic locking device for space-borne antenna
CN103825078B (en) * 2014-03-24 2016-06-08 上海航天电子通讯设备研究所 A kind of satellite antenna forced locking device
CN103935512A (en) * 2014-05-12 2014-07-23 马轶 High endurable multi-rotor craft
CN107651168A (en) * 2017-09-30 2018-02-02 肇庆高新区国专科技有限公司 A kind of unmanned plane wingfold mechanism and method for folding

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Application publication date: 20120725