CN102363444B - Transverse folding mechanism for empennage - Google Patents
Transverse folding mechanism for empennage Download PDFInfo
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- CN102363444B CN102363444B CN 201110265800 CN201110265800A CN102363444B CN 102363444 B CN102363444 B CN 102363444B CN 201110265800 CN201110265800 CN 201110265800 CN 201110265800 A CN201110265800 A CN 201110265800A CN 102363444 B CN102363444 B CN 102363444B
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- empennage
- joint
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- rotation
- kinetoplast
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Abstract
The invention discloses a transverse folding mechanism for an empennage. The transverse folding mechanism which comprises an empennage joint, a rotary actuating body and a socket is characterized in that: the empennage joint is formed by an aerofoil body, a joint sleeve and a slot; one side of the aerofoil body is provided with the joint sleeve, and the other side of the aerofoil body is provided with the slot; the slot is provided with mounting holes; one end of the rotary actuating body is a tail end; the circular shaft end of a rotary joint is connected with a power source arranged in the rotary actuating body; the power source which makes the rotary joint rotate allows the empennage joint to rotate through being driven by the socket; the rotary actuating body is provided with a locking pin A and a locking pin B which are respectively and correspondingly arranged in a pinhole of a circular shaft of the rotary joint; the locking pin B is disengaged when the rotary joint rotates, the locking pin A is pushed into the pinhole to make the whole mechanism be in a locking state and prevent the past empennage rotation and the empennage oscillation movement when the rotary joint rotates to a preset angle.
Description
Technical field
The present invention relates to fold mechanism, particularly relate to the laterally folded mechanism of a kind of empennage.
Background technology
For dwindling guided missile on-hook space size and making the feedway miniaturization of guided missile, also make simultaneously transportation, store simple and conveniently, increase the storage capacity of storing and transporting equipment, the fight capability of raising armament systems, require guided missile to adopt folded surface, and can launch the back aloft and launch to put in place.Most collapsible aerofoil is longitudinal folding aerofoil at present, empennage generally need be hidden in bomb body inside, sacrificed the expensive real estate of bomb body inside, and some situation do not have space mounting, and adopt laterally folded, the folded surface rotating shaft is located at root or the middle part of aerofoil usually, because the empennage profile thickness is thinner, so generally adopt torsion spring, spring etc. as propulsion source, the moment that provides is less, after can't satisfying guided missile and aloft launching, empennage launches the requirement that puts in place.
Summary of the invention
The present invention is directed to missile tail small space and guided missile and launch the requirement that back empennage expansion puts in place in the air, adopt rotation to make kinetoplast and drive the empennage rotation, do not take too big space, in transportation, storage, carry process, empennage keeps folded state, to reduce the guided missile horizontal space; And after guided missile is launched, reach the purpose that the missile tail expansion puts in place aloft.
The technical solution used in the present invention is, a kind of laterally folded mechanism, comprise the empennage joint, kinetoplast and edge connector are made in rotation, described empennage joint is by the aerofoil body, adapter sleeve and slot constitute one, aerofoil body one side is provided with adapter sleeve, opposite side is provided with slot, the slot place is provided with mounting hole, the end that kinetoplast is made in described rotation is tail end, swivel joint is housed in the other end, one end of swivel joint is circular shaft, circular shaft is provided with two pin-and-holes, the other end is flat-shaped body, the circular shaft end of swivel joint is connected with the propulsion source that rotation is done to be equipped with in the kinetoplast, rotation is made kinetoplast and is provided with locking pin A and locking pin B, all correspondence is installed in the pin-and-hole of circular shaft of swivel joint, the side that kinetoplast is made in rotation is provided with attachment lug, attachment lug is provided with mounting hole, attachment lug captive joint body, described edge connector is made up of pedestal and auricle, and pedestal is provided with slot, pedestal and auricle are provided with mounting hole, adapter sleeve is set in tail end, and the slot of empennage joint is connected with the auricle of edge connector, and the pedestal slot of edge connector connects swivel joint.
Described propulsion source is that motor or Hydraulic Pump or firer rotate acting device.
Described locking pin A is elastic body or spring piston.
Described locking pin B is pin drift or shear pin.
Advantage of the present invention is, this mechanism uses edge connector, empennage and rotation are coupled together as kinetoplast, and by the rotation start [RC1] empennage and bomb body are coupled together, rotation is simultaneously made the kinetoplast tail end and is adopted precision to cooperate with the empennage adapter sleeve, so that auxiliary fulcrum to be provided, and also can be according to concrete application scenario, increase antifriction-bearing box in case kinematic mechanism is stuck, guarantee the reliability that empennage launches.Latching device all in the rotation acting device, with its integrated design, reduces the fitting work amount.Make the folding fin modularization, simple in structure, flexible reliable, folding easy accessibility; Guided missile is launched reliable expansion of back empennage in the air and is put in place, and empennage launches forward and backward in stable conditionly, can be applicable to various guided missiles by repacking and launches in the air, and empennage is laterally folded, the purpose that In-Flight Deployment puts in place.
Description of drawings
Fig. 1 is empennage deployed condition scheme drawing of the present invention.
Fig. 2 is empennage folded state scheme drawing of the present invention.
Fig. 3 is the structural representation of empennage joint 1 among Fig. 1.
Fig. 4 is the structural representation that kinetoplast 2 is made in rotation among Fig. 1.
Fig. 5 is the structural representation of edge connector 3 among Fig. 1.
Fig. 6 is the structural representation of swivel joint 24 among Fig. 4.
Among the figure: 1, empennage joint, 11, adapter sleeve, 12, the aerofoil body, 2, kinetoplast is made in rotation, and 21, tail end, 22, attachment lug, 23, pin-and-hole, 24, swivel joint, 25, locking pin A, 3, edge connector, 31, pedestal, 32, auricle, 4, connecting bore, 5, slot, 6, propulsion source, 7, locking pin B.
The specific embodiment
The invention will be further described below in conjunction with drawings and Examples, referring to Fig. 1 to Fig. 5, a kind of laterally folded mechanism, comprise empennage joint 1, kinetoplast 2 and edge connector 3 are made in rotation, described empennage joint 1 is by aerofoil body 12, adapter sleeve 11 and slot 5 constitute one, aerofoil body 12 1 sides are provided with adapter sleeve 11, opposite side is provided with slot 5, slot 5 places are provided with mounting hole 4, the end that kinetoplast 2 is made in described rotation is tail end 21, swivel joint 24 is housed in the other end, one end of swivel joint 24 is circular shaft, circular shaft is provided with two pin-and-holes 23, the other end is flat-shaped body, the circular shaft end of swivel joint 24 is connected with the propulsion source 6 that rotation is done to be equipped with in the kinetoplast 2, rotation is made kinetoplast 2 and is provided with locking pin A25 and locking pin B7, all correspondence is installed in the pin-and-hole 23 of circular shaft of swivel joint 24, the side that kinetoplast 2 is made in rotation is provided with attachment lug 22, attachment lug 22 is provided with mounting hole 4, attachment lug 22 captive joint bodies, described edge connector 3 is made up of pedestal 31 and auricle 32, pedestal 31 is provided with slot 5, pedestal 31 and auricle 32 are provided with mounting hole 4, adapter sleeve 11 is set in tail end 21, the slot 5 of empennage joint 1 is connected with the auricle 32 of edge connector 3, and pedestal 31 slots 5 of edge connector 3 connect swivel joint 24.
Described propulsion source 6 is that motor or Hydraulic Pump or firer rotate acting device.
Described locking pin A25 is elastic body or spring piston.
Described locking pin B7 is pin drift or shear pin.
Embodiment 1:
Know that by accompanying drawing 1-3 the laterally folded mechanism of empennage is made kinetoplast 2, edge connector 3 etc. and formed by empennage joint 1, rotation, empennage is when initial position, rotation is done to be provided with shear pin in the kinetoplast 2, it is the locked and tripper of sleeve mechanism, guarantee that empennage is in stationary state, rotation is made kinetoplast 2 and is provided with the firer and rotates acting device, is the propulsion source 6 of sleeve mechanism, for empennage launches to put in place rotating torque is provided.Its working process is: task engine provides instruction back rotation and makes kinetoplast 2 moment that rotates of starting working, when external force that the moment that provides can bear greater than shear pin, shear pin is cut off, mechanism's release, swivel joint 24 begins rotation afterwards, afterwards drive edge connector 3 and rotate, drive empennage joint 1 by edge connector 3 and rotate motion; When swivel joint 24 rotated to set angle, locking pin A25 advanced in the pin-and-hole 23, makes entire mechanism be in locking state, prevented that empennage from crossing the position and vibratory movement takes place.
Embodiment 2:
Know that by accompanying drawing 1-3 the laterally folded mechanism of empennage is made kinetoplast 2, edge connector 3 etc. and formed by empennage joint 1, rotation, empennage is when initial position, rotation makes to be provided with in the kinetoplast 2 pin drift that connects task engine control, it is the locked and tripper of sleeve mechanism, guarantee that empennage is in stationary state, rotation is done in the kinetoplast 2 Hydraulic Pump to be installed, and is the propulsion source 6 of sleeve mechanism, for empennage launches to put in place rotating torque is provided.Its working process is: after task engine provides instruction, pin drift is at first worked, pin drift is extracted, kinetoplast 2 releases are done in rotation, the Hydraulic Pump moment that rotates of starting working then, swivel joint 24 begins rotation, drives edge connector 3 afterwards and rotates, and drives empennage joint 1 by edge connector 3 and rotates motion; When swivel joint 24 rotated to set angle, locking pin A25 advanced pin-and-hole 23, makes entire mechanism be in locking state, prevented that empennage from crossing the position and vibratory movement takes place.
Claims (2)
1. laterally folded mechanism, it is characterized in that, comprise empennage joint (1), kinetoplast (2) and edge connector (3) are made in rotation, described empennage joint (1) is by aerofoil body (12), adapter sleeve (11) and slot (5) constitute one, aerofoil body (12) one sides are provided with adapter sleeve (11), opposite side is provided with slot (5), slot (5) locates to be provided with mounting hole (4), the end that kinetoplast (2) is made in described rotation is tail end (21), swivel joint (24) is housed in the other end, one end of swivel joint (24) is circular shaft, circular shaft is provided with two pin-and-holes (23), the other end is flat-shaped body, the circular shaft end of swivel joint (24) is connected with the propulsion source (6) that is equipped with in kinetoplast (2) is made in rotation, rotation is made kinetoplast (2) and is provided with locking pin A(25) and locking pin B(7), all correspondence is installed in the pin-and-hole (23) of circular shaft of swivel joint (24), the side that kinetoplast (2) is made in rotation is provided with attachment lug (22), attachment lug (22) is provided with mounting hole (4), attachment lug (22) captive joint body, described edge connector (3) is made up of pedestal (31) and auricle (32), pedestal (31) is provided with slot (5), pedestal (31) and auricle (32) are provided with mounting hole (4), adapter sleeve (11) is set in tail end (21), the slot (5) of empennage joint (1) is connected with the auricle (32) of edge connector (3), and pedestal (31) slot (5) of edge connector (3) connects swivel joint (24).
2. laterally folded mechanism according to claim 1 is characterized in that, described propulsion source (6) is that motor or Hydraulic Pump or firer rotate acting device.
3, laterally folded mechanism according to claim 1 is characterized in that, described locking pin A(25) be elastic body or spring piston.
4, laterally folded mechanism according to claim 1 is characterized in that, described locking pin B(7) be pin or the shear pin that can be pulled out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110265800 CN102363444B (en) | 2011-09-09 | 2011-09-09 | Transverse folding mechanism for empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110265800 CN102363444B (en) | 2011-09-09 | 2011-09-09 | Transverse folding mechanism for empennage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102363444A CN102363444A (en) | 2012-02-29 |
| CN102363444B true CN102363444B (en) | 2013-07-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110265800 Active CN102363444B (en) | 2011-09-09 | 2011-09-09 | Transverse folding mechanism for empennage |
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| CN (1) | CN102363444B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103522248B (en) * | 2013-10-11 | 2015-08-05 | 北京航天新风机械设备有限责任公司 | A kind of special tooling folding for rudder/aerofoil |
| CN103640688A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Rectifying device of missile wing folding mechanism |
| CN104085526B (en) * | 2014-06-25 | 2016-03-30 | 西北工业大学 | A kind of realize patrolling fly device wing body connect, fixing, locked, unblock integral structure |
| CN105424314B (en) * | 2015-12-18 | 2018-02-09 | 中国航天空气动力技术研究院 | Free flight model rudder face deploys flow tunnel testing device |
| CN109186370A (en) * | 2018-07-26 | 2019-01-11 | 重庆长安工业(集团)有限责任公司 | A kind of folded surface unfolding mechanism |
| CN109186369B (en) * | 2018-08-24 | 2020-10-16 | 江西洪都航空工业集团有限责任公司 | Missile wing installation fixed establishment |
| CN114216647A (en) * | 2021-12-16 | 2022-03-22 | 中国航天空气动力技术研究院 | Rudder wing transient unfolding and folding device for wind tunnel test |
| CN114485288A (en) * | 2021-12-27 | 2022-05-13 | 西安现代控制技术研究所 | Unfolding and locking method of small-caliber projectile body-large wingspan space folding tail wing |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3063375A (en) * | 1960-05-19 | 1962-11-13 | Wilbur W Hawley | Folding fin |
| FR2165695B1 (en) * | 1970-04-30 | 1976-02-06 | Hawker Siddeley Dynamics Gb | |
| KR0176320B1 (en) * | 1995-12-09 | 1999-04-01 | 배문한 | Guided missile wing deployment and fixture |
| US5816532A (en) * | 1996-12-17 | 1998-10-06 | Northrop Grumman Corporation | Multiposition folding control surface for improved launch stability in missiles |
| CN2662966Y (en) * | 2003-11-25 | 2004-12-15 | 熊耀华 | Flight track adjustable toy plane |
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2011
- 2011-09-09 CN CN 201110265800 patent/CN102363444B/en active Active
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| Publication number | Publication date |
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| CN102363444A (en) | 2012-02-29 |
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Owner name: JIANGXI HONGDU TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: HONGDU AVIATION INDUSTRY GROUP CO., TD., JIANGXI PROV. Effective date: 20140815 |
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Application publication date: 20120229 Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000166 Denomination of invention: Transverse folding mechanism for empennage Granted publication date: 20130717 License type: Exclusive License Record date: 20140709 |
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Effective date of registration: 20140815 Address after: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee after: Jiangxi Hongdu Technology Co., Ltd. Address before: 330000 Jiangxi city of Nanchang province Qingyunpu new Xiqiao 5001 box 460 box Patentee before: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. |
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Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000166 Date of cancellation: 20141202 |
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Effective date of registration: 20151228 Address after: Jiangxi province 330000 new bridges and 5001 box 460 box Patentee after: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Address before: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee before: Jiangxi Hongdu Technology Co., Ltd. |