CN102363444A - Transverse folding mechanism for empennage - Google Patents
Transverse folding mechanism for empennage Download PDFInfo
- Publication number
- CN102363444A CN102363444A CN2011102658002A CN201110265800A CN102363444A CN 102363444 A CN102363444 A CN 102363444A CN 2011102658002 A CN2011102658002 A CN 2011102658002A CN 201110265800 A CN201110265800 A CN 201110265800A CN 102363444 A CN102363444 A CN 102363444A
- Authority
- CN
- China
- Prior art keywords
- empennage
- joint
- slot
- kinetoplast
- locking pin
- 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.)
- Granted
Links
Images
Landscapes
- Connection Of Plates (AREA)
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 lorizontal folding 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, and empennage generally need be hidden in bomb body inside, has sacrificed bomb body in-to-in expensive real estate; And some situation does not have space mounting, and adopts lorizontal foldingly, and the folded surface rotating shaft is located at the 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 scheme that the present invention adopts is that a kind of lorizontal folding mechanism comprises the empennage joint, rotates and make kinetoplast and edge connector; Said empennage joint constitutes one by aerofoil body, adapter sleeve and slot, and aerofoil body one side is provided with adapter sleeve, and opposite side is provided with slot; The slot place is provided with mounting hole, and the end that kinetoplast is made in said rotation is a tail end, and SAH is housed in the other end; One end of SAH is a circular shaft, and circular shaft is provided with two pin-and-holes, and the other end is flat-shaped body; The circular shaft end of SAH is connected with the rotation propulsion source doing to be equipped with in the kinetoplast, and rotation is made kinetoplast and is provided with locking pin A and locking pin B, and equal correspondence is installed in the pin-and-hole of circular shaft of SAH; The side that kinetoplast is made in rotation is provided with attachment lug, and attachment lug is provided with mounting hole, attachment lug captive joint body; Said edge connector is made up of pedestal and auricle, and pedestal is provided with slot, and 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 SAH.
Said propulsion source is that motor or Hydraulic Pump or firer rotate acting device.
Said locking pin A is elastic body or spring piston.
Said locking pin B is pin drift or shear pin.
Advantage of the present invention is that this mechanism uses edge connector, and empennage and rotation are coupled together as kinetoplast; And through 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 through repacking and launches in the air, and empennage is lorizontal folding, the purpose that In-Flight Deployment puts in place.
Description of drawings
Fig. 1 is an empennage deployed condition scheme drawing of the present invention.
Fig. 2 is an 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 SAH 24 among Fig. 4.
Among the figure: 1, empennage joint, 11, adapter sleeve, 12, the aerofoil body, 2, rotation makes kinetoplast; 21, tail end, 22, attachment lug, 23, pin-and-hole, 24, SAH; 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
Below in conjunction with accompanying drawing and embodiment the present invention is described further, referring to Fig. 1 to Fig. 5, a kind of lorizontal folding mechanism; Comprise empennage joint 1, rotate and make kinetoplast 2 and edge connector 3 that said empennage joint 1 constitutes one by aerofoil body 12, adapter sleeve 11 and slot 5, aerofoil body 12 1 sides are provided with adapter sleeve 11; Opposite side is provided with slot 5, and slot 5 places are provided with mounting hole 4, and the end that kinetoplast 2 is made in said rotation is a tail end 21; SAH 24 is housed in the other end, and an end of SAH 24 is a circular shaft, and circular shaft is provided with two pin-and-holes 23; The other end is flat-shaped body, and the circular shaft end of SAH 24 is connected with the propulsion source 6 that rotation is done to be equipped with in the kinetoplast 2, and 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 SAH 24, and the side that kinetoplast 2 is made in rotation is provided with attachment lug 22, and attachment lug 22 is provided with mounting hole 4; Attachment lug 22 captive joint bodies, said edge connector 3 is made up of pedestal 31 and auricle 32, and pedestal 31 is provided with slot 5; Pedestal 31 is provided with mounting hole 4 with auricle 32; Adapter sleeve 11 is set in tail end 21, and 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 SAH 24.
Said propulsion source 6 is that motor or Hydraulic Pump or firer rotate acting device.
Said locking pin A25 is elastic body or spring piston.
Said locking pin B7 is pin drift or shear pin.
Embodiment 1:
Know that by accompanying drawing 1-3 the lorizontal folding mechanism of empennage is made kinetoplast 2, edge connector 3 etc. and formed by empennage joint 1, rotation; Empennage is when initial position, and rotation is done to be provided with shear pin in the kinetoplast 2, 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, and SAH 24 begins rotation afterwards; Afterwards drive edge connector 3 and rotate, drive empennage joint 1 through edge connector 3 and rotate motion; When SAH 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 lorizontal folding mechanism of empennage is made kinetoplast 2, edge connector 3 etc. and formed by empennage joint 1, rotation; Empennage is when initial position, and rotation is done to be provided with the pin drift that connects task engine control in the kinetoplast 2, 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, and pin drift is extracted, and kinetoplast 2 releases are done in rotation; The Hydraulic Pump moment that rotates of starting working then; SAH 24 begins rotation, drives edge connector 3 afterwards and rotates, and drives empennage joint 1 through edge connector 3 and rotates motion; When SAH 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 (4)
1. a lorizontal folding mechanism is characterized in that, comprises empennage joint (1), rotates and make kinetoplast (2) and edge connector (3); Said empennage joint (1) constitutes one by aerofoil body (12), adapter sleeve (11) and slot (5), and aerofoil body (12) one sides are provided with adapter sleeve (11), and opposite side is provided with slot (5); Slot (5) locates to be provided with mounting hole (4), and the end that kinetoplast (2) is made in said rotation is tail end (21), and SAH (24) is housed in the other end; One end of SAH (24) is a circular shaft, and circular shaft is provided with two pin-and-holes (23), and the other end is flat-shaped body; The circular shaft end of SAH (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), and all correspondence is installed in the pin-and-hole (23) of circular shaft of SAH (24), rotates a side of making kinetoplast (2) and is provided with attachment lug (22); Attachment lug (22) is provided with mounting hole (4); Attachment lug (22) captive joint body, said edge connector (3) is made up of pedestal (31) and auricle (32), and 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), and 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 SAH (24).
2. lorizontal folding mechanism according to claim 1 is characterized in that, said propulsion source (6) is that motor or Hydraulic Pump or firer rotate acting device.
3. lorizontal folding mechanism according to claim 1 is characterized in that, said locking pin A (25) is elastic body or spring piston.
4. lorizontal folding mechanism according to claim 1 is characterized in that, said locking pin B (7) is pin drift or shear pin.
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 true CN102363444A (en) | 2012-02-29 |
| CN102363444B CN102363444B (en) | 2013-07-17 |
Family
ID=45690045
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110265800 Active CN102363444B (en) | 2011-09-09 | 2011-09-09 | Transverse folding mechanism for empennage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102363444B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103522248A (en) * | 2013-10-11 | 2014-01-22 | 北京航天新风机械设备有限责任公司 | Tool special for rudder/airfoil folding |
| 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 |
| CN104085526A (en) * | 2014-06-25 | 2014-10-08 | 西北工业大学 | Integrated structure for connecting, fixing, locking and unlocking wing body of patrolling aircraft |
| CN105424314A (en) * | 2015-12-18 | 2016-03-23 | 中国航天空气动力技术研究院 | Device for control surface unfolding wind tunnel test of free flight model |
| 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 |
| CN109186369A (en) * | 2018-08-24 | 2019-01-11 | 江西洪都航空工业集团有限责任公司 | A kind of missile wing mechanism for installing |
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3063375A (en) * | 1960-05-19 | 1962-11-13 | Wilbur W Hawley | Folding fin |
| GB1342342A (en) * | 1970-04-30 | 1974-01-03 | Hawker Siddeley Dynamics Ltd | Control systems |
| US5816532A (en) * | 1996-12-17 | 1998-10-06 | Northrop Grumman Corporation | Multiposition folding control surface for improved launch stability in missiles |
| US5820072A (en) * | 1995-12-09 | 1998-10-13 | Agency For Defense Development | Apparatus for unfolding and fixing missile fins |
| CN2662966Y (en) * | 2003-11-25 | 2004-12-15 | 熊耀华 | Flight track adjustable toy plane |
-
2011
- 2011-09-09 CN CN 201110265800 patent/CN102363444B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3063375A (en) * | 1960-05-19 | 1962-11-13 | Wilbur W Hawley | Folding fin |
| GB1342342A (en) * | 1970-04-30 | 1974-01-03 | Hawker Siddeley Dynamics Ltd | Control systems |
| US5820072A (en) * | 1995-12-09 | 1998-10-13 | Agency For Defense Development | Apparatus for unfolding and fixing missile fins |
| 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 |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103522248A (en) * | 2013-10-11 | 2014-01-22 | 北京航天新风机械设备有限责任公司 | Tool special for rudder/airfoil folding |
| 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 |
| CN104085526A (en) * | 2014-06-25 | 2014-10-08 | 西北工业大学 | Integrated structure for connecting, fixing, locking and unlocking wing body of patrolling aircraft |
| 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 |
| CN105424314A (en) * | 2015-12-18 | 2016-03-23 | 中国航天空气动力技术研究院 | Device for control surface unfolding wind tunnel test of free flight model |
| 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 |
| CN109186369A (en) * | 2018-08-24 | 2019-01-11 | 江西洪都航空工业集团有限责任公司 | A kind of missile wing mechanism for installing |
| 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 |
| CN114485288B (en) * | 2021-12-27 | 2024-05-28 | 西安现代控制技术研究所 | Unfolding and locking method for small-caliber projectile body-large-span space folding tail wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102363444B (en) | 2013-07-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102363444B (en) | Transverse folding mechanism for empennage | |
| CN201895770U (en) | Locking and unlocking mechanism for aircraft airfoil | |
| CN106347632B (en) | A kind of expansion retaining mechanism | |
| CN109631686B (en) | Flying missile inspection folding wing mechanism | |
| CN104089547B (en) | A kind of Deployment and locking device of folding rudder face | |
| CN107576228B (en) | A kind of high synchronism rudder face folding and expanding mechanism | |
| CN109539902B (en) | Electric-drive folding wing system with large aspect ratio | |
| CN102774494A (en) | Aircraft folding rudder capable of stretching automatically | |
| CN103935531B (en) | A kind of two-dimensional vector regulating mechanism | |
| KR20180082539A (en) | An aircraft having deployable components | |
| CN110230955A (en) | Retaining mechanism and its expansion locking method is unfolded in submersible folding wings synchronous horizontal | |
| CN103693188A (en) | Wing folding and unfolding mechanism of unmanned aerial vehicle | |
| JP6581601B2 (en) | Payload injection system | |
| EP3369653B1 (en) | Hinge mechanism for a weight-shifting coaxial helicopter | |
| CN104527997B (en) | A kind of synchronous device for connecting and unlock satellite | |
| CN104713426B (en) | The laterally folded aerofoil of a kind of sliding wedge formula | |
| CN104677200B (en) | One twice-folded aerofoil horizontal spreading mechanism | |
| CN210833270U (en) | Synchronous transverse unfolding locking mechanism for submerged folding wings | |
| CN109515732B (en) | Combined aircraft based on barrel type launching | |
| CN207417121U (en) | A kind of compressed spring type unmanned plane wing-folding unfolding mechanism | |
| CN204461240U (en) | Twice-folded aerofoil horizontal spreading mechanism | |
| CN202115709U (en) | Space cam-spiral combined repeated folding unlocking mechanism | |
| CN112849400A (en) | Sleeve locking type four-rotor unmanned aerial vehicle for barrel type carrying | |
| CN102278916B (en) | Space cam-screw combined type repeatedly folding-unfolding unlocking mechanism | |
| CN116147426A (en) | Self-constrained time sequence unfolding transverse folding rudder wing mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: JIANGXI HONGDU TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: HONGDU AVIATION INDUSTRY GROUP CO., TD., JIANGXI PROV. Effective date: 20140815 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 330000 NANCHANG, JIANGXI PROVINCE TO: 330096 NANCHANG, JIANGXI PROVINCE |
|
| EE01 | Entry into force of recordation of patent licensing contract |
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 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| TR01 | Transfer of patent right |
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. |
|
| EC01 | Cancellation of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000166 Date of cancellation: 20141202 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
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. |