CN203629478U - Paddle-type folding mechanism used for horizontally folding missile wings - Google Patents
Paddle-type folding mechanism used for horizontally folding missile wings Download PDFInfo
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- CN203629478U CN203629478U CN201320713576.3U CN201320713576U CN203629478U CN 203629478 U CN203629478 U CN 203629478U CN 201320713576 U CN201320713576 U CN 201320713576U CN 203629478 U CN203629478 U CN 203629478U
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Abstract
The utility model discloses a paddle-type folding mechanism used for horizontally folding missile wings. The mechanism comprises a front baffle of an outer wing, a rear baffle of the outer wing, a front baffle of an inner wing, a rear baffle of the inner wing, a front adapter of a torsion bar, a rear adapter of the torsion bar, and a locking mechanism, wherein one end of the front adapter is inserted in two side walls of a framework of the inner wing respectively by means of through holes in the front baffle of the inner wing and the rear baffle of the inner wing, the other end thereof is inserted into two side walls of a framework of the outer wing by means of through holes in the front baffle of the outer wing and the rear baffle of the outer wing, and a torsion bar on which prestress is exerted is arranged between the front adapter and the rear adapter of the torsion bar, so that the outer wing can be rotatablely connected relative to the inner wing by the action of the torsion bar; the locking mechanism is arranged on two side end surfaces of the framework of the inner wing, and can lock the outer wing and the inner wing when the outer wing is rotatablely unfolded or folded relative to the inner wing in place. The mechanism disclosed by the utility model can achieve the aim that folding missile wings are manually or automatically unfolded and locked, and has the advantages of good bearing performance, small shaking clearance between wing surfaces, and convenience for disassembly and assembly.
Description
Technical field
The utility model belongs to the folding wing technical field of aircraft, is specifically related to a kind of fold mechanism for folding wing.
Background technology
For dwindling guided missile volume on storage, transportation and emitter, and part or all of missile wing is folding, the span is reduced, when guided missile flies away from after emitter, missile wing Automatic-expanding, guarantees guided missile normal flight.Also the folded surface of some guided missile, only for dwindling the volume of storage, transportation, in the time that guided missile installs on emitter, launches by missile wing.
Folding wing be aerofoil exhibition to a part or wing root portion fold mechanism missile wing is folding, after constraint relief, missile wing is Automatic-expanding and locks on assigned position, can realize missile wing folding, launch and the mechanism of locking is the fold mechanism of folding wing.The fold mechanism of folding wing generally comprises expanding unit and locking device two parts.The effect of expanding unit is to make to launch under certain condition in the aerofoil of folded state.The effect of locking device is, after the folded part of missile wing launches, can make the standing part of missile wing and folded part lock reliably as a whole, so that shared aerodynamic force, for guided missile provides lift.
At present common folding wing form mainly contains: the folded formula of volume, submersible, the folded formula of tail, longitudinal folding formula, laterally folded formula, collapsible and telescopic folding type etc. repeatedly.Launch locking system and mostly be spring mechanism, the gaseous-pressure system that also useful hydraulic system or priming system form.Be to connect reliably to the requirement of fold mechanism, mechanism is simple, launches rapidly, and locking firmly, lightweight, volume is little, aerodynamic configuration good.
Fold mechanism, as the important component part of folding wing, according to differences such as the size of folding wing, installing space and environment for use condition, mechanical environment conditions, can adopt multi-form fold mechanism.The normal fold mechanism adopting is broadly divided into two classes at present, and a class is the axial fold mechanism along rudderpost direction (being perpendicular to wing root chord for the wing), and a class is perpendicular to the laterally folded mechanism of rudderpost direction (being to be parallel to wing root chord for the wing).Axially fold mechanism normally adds compression spring set by locking pin, fold mechanism is retrained by aerofoil, after expansion puts in place, inserting pin-and-hole locks, or by inertia in aerofoil expansion process, locking pin is compressed, after expansion puts in place, insert pin-and-hole again and lock, axial locking mechanism can form by one to two group.This kind of fold mechanism is simple and reliable for structure, cost is low, take size little, on the little Missile Folding missile wing of size application wider, also there are some defects: as folding wing can not bear larger load, and in the time of aerofoil excess Temperature, Compress Spring easily lost efficacy, and then caused retaining mechanism to lose efficacy, in addition, in the time that body stands larger vibration environment and lateral overload, axial locking mechanism is easily loosening.Laterally folded mechanism form is comparatively various, by two locking points of horizontally set, makes folding wing can bear larger aerofoil normal load.This kind of fold mechanism is by two locking pins are set on folding wing, Compress Spring is installed in locking pin rear end, two locking pins are fixed in the both ends of the surface of folding rudder inner wing by a connecting rod, in the time that folding wing outer wing launches, inertia by folding wing outer wing is cut off connecting rod, be fixed on the locking pin release in folding wing inner wing and under the effect of Compress Spring, eject the pin-and-hole that inserts folding wing outer wing two ends, making folding wing outer wing lock and fix.This kind of fold mechanism can bear larger load, and locking better, can produce fifth wheel but cut off connecting rod, and the reliability of launching locking reduces, this fold mechanism is without lock function only simultaneously, and at vibration level, in the large or environment that Aerodynamic Heating is harsher, fold mechanism is easily loosening.
In recent years, on guided missile, adopt the trend of folded surface increasing, adopt folding wing not only can dwindle the lateral dimension of guided missile, be convenient to box type storing dress, transportation and transmitting, also can save the storing space of guided missile simultaneously, increase the carrying capacity of vehicle or naval vessels, reduce position number of vehicles, improve its combat capabilities.Therefore, the research of reinforcement fold mechanism has important and real meaning to folding wing application practice in guided missile.
Utility model content
The purpose of this utility model is to provide a kind of piece-picking type fold mechanism for laterally folded missile wing, realizing laterally folded missile wing can automatic unlocking, expansion, and lock on assigned position, the span is reduced, and then dwindle guided missile volume on storage, transportation and emitter, when guided missile flies away from after emitter, missile wing Automatic-expanding, guarantees guided missile normal flight.
A kind of piece-picking type fold mechanism for laterally folded missile wing that the utility model provides, is arranged between wing outer wing and inner wing, for realizing relatively rotating and locking between described outer wing and inner wing, it is characterized in that, this fold mechanism comprises:
Outer wing front apron and outer wing backboard, it is fixedly installed on respectively the two side for mating with inner wing on outer wing skeleton 1 by screw;
Inner wing front apron and inner wing backboard, it is fixedly mounted on inner wing skeleton 2 with on corresponding both sides end face outer wing coupling by screw;
Adapter after adapter and torque arm before torque arm, insert in the two side on described inner wing skeleton by the through hole on inner wing front apron and inner wing backboard respectively its one end, the other end inserts in the two side on outer wing skeleton by the through hole on described outer wing front apron and outer wing backboard, and after this front adapter and torque arm, between adapter, be provided with and be applied with prestressed torque arm, can realize the relative inner wing of described outer wing by its effect and connect rotationally;
Lockable mechanism, it is arranged on the described both sides end face of inner wing skeleton, and it can realize both lockings at described outer wing after inner wing rotates expansion or folding putting in place.
As improvement of the present utility model, described lockable mechanism comprises the spring catch in the perforate that is arranged on inner wing skeleton side end face, its one end is arranged in described perforate by Compress Spring, the other end can stretch in the side-wall hole of described outer wing skeleton by this Compress Spring effect after the relative inner wing of described outer wing launches to put in place, realizes both and relatively fixes and locking.
As improvement of the present utility model, described lockable mechanism also comprises release catch rotating shaft reconciliation stopper sheet, this release catch is fixed on and is arranged on inner wing skeleton by the rotating shaft of release catch, ball-and-socket on this release catch and the bulb on spring catch connect with by its constraint, described release catch is under the effect of peripheral force, release catch rotating shaft axial rotation relatively, thus the constraint to this spring catch can be removed.
As improvement of the present utility model, this mechanism also comprises inner wing front shaft sleeve and inner wing rear axle housing, and described lockable mechanism is two covers, and spring catch is wherein sleeved in the perforate of described inner wing skeleton side end face by this inner wing front shaft sleeve and inner wing rear axle housing respectively.
In the utility model, missile wing is made up of outer wing and inner wing, and wherein inner wing maintains static, outer wing and inner wing by torque arm before after adapter and torque arm adapter link and be integrated, and outer wing rotates relative to inner wing.
In the utility model, be empty in the middle of outer wing skeleton, front end has two circular counter bore, and upper rear end is step circular hole, and bottom is manhole; Have a tapped through hole along outer wing skeleton normal direction, the circular hole of top and the bottom, outer wing skeleton two ends is coaxially.A circular shaft is protruded in outer wing front apron bottom, have two through holes, and bottom circular hole is coaxial with circular shaft along spanwise simultaneously.On outer wing backboard, there are two circular shafts, are processed with respectively the different manhole of diameter along circular shaft axis.
In the utility model, inner wing front apron is processed with a conical through-hole, a rectangular opening, large special-shaped through hole and two screwed holes in wide bottom, little centre, a top from top to bottom successively, is processed with " U " shape groove in the bottom of special-shaped through hole one side simultaneously.Described inner wing backboard and described inner wing front apron are symmetrical member, and the plane of symmetry is the end face of described inner wing front apron.Adapter is a Step Shaft before described torque arm, and one end is rectangular shaft, and one end is circular shaft, in rectangular shaft one end, be processed with a manhole along the axis of Step Shaft, meanwhile, is evenly equipped with 4 manholes in rectangular shaft one end; In circular shaft one end, be processed with a rectangular through-hole along the axis of Step Shaft.After described torque arm, adapter is a Step Shaft, and one end is rectangular shaft, and one end is circular shaft, is processed with a manhole along the axis of Step Shaft, meanwhile, is evenly equipped with 4 manholes in rectangular shaft one end.Described spring catch is step pin, and step pin mid diameter maximum, is processed with a tapped through hole, and two ends diameter is less, and wherein one end circular shaft has certain tapering, is protruding with 1/3 sphere at cone end end face.The rotating shaft of described release catch is Step Shaft, is divided into three sections, and diameter diminishes successively, and the larger end of diameter is processed with the counterbore of inner cross shape along axis, and the less one end of diameter is processed with external screw thread.Described release catch is " racket " shape, the middle circular shaft that protrudes, and one end has processed a stepped counterbore, and one end is processed with the ball-and-socket of a depression 1/4.Described inner wing front shaft sleeve is a pipe, pipe one end is processed with length " U " the shape hole of two certain angles of being separated by (being angle folding), simultaneously be processed with respectively a manhole growing " U " shape bore end opposite, and cut half at the pipe of growing " U " shape outer end of hole.Described inner wing rear axle housing and described inner wing front shaft sleeve structure are symmetrical member, and the plane of symmetry is the end face of inner wing front shaft sleeve.The described screw II of marking closely is threaded, a chamfer, and one end has processed " one " word groove.
In the utility model, torque arm is metallic elastic component, and certain relative moment of torsion can be born in torque arm two ends, when torque arm is during in twisting states, has certain elastic potential energy, and its function and torsionspring are similar.Its two ends are radially processed with respectively a manhole.
The utility model combines the advantage of axial fold mechanism and laterally folded mechanism, can realize folding wing expansion and locking manually or automatically, has load performance good, it is little that aerofoil rocks gap, and easy accessibility can repeatedly use, be convenient to safeguard, and connect reliably, mechanism is simple, launch rapidly, lightweight, volume is little, aerodynamic configuration is better, be suitable for flying away from after emitter at guided missile, missile wing Automatic-expanding, applies in the middle-size and small-size folding wing of assurance guided missile normal flight.
Accompanying drawing explanation
Fig. 1 is folding wing of the present utility model half sectional view in the time launching locking respectively.
Fig. 2 (a)-2 (c) is the cutaway view of outer wing in folding wing of the present utility model.
Fig. 3 (a)-3 (c) is inner wing cutaway view in folding wing of the present utility model.
Fig. 4 is latch schematic diagram of the present utility model.
Fig. 5 (a)-5 (c) is torque arm of the present utility model and limited block connection diagram.
In figure, 1 is outer wing skeleton, and 2 is inner wing skeleton, and 3 is torque arm, 4 for marking closely screw, and 5 is limited block, and 6 is outer wing front apron, and 7 is outer wing backboard, 8 is inner wing front apron, and 9 is inner wing backboard, and 10 is adapter before torque arm, and 11 is adapter after torque arm, 12 is spring catch, and 13 is Compress Spring, and 14 is the rotating shaft of release catch, 15 is screw, and 16 is release catch, and 17 is inner wing front shaft sleeve, 18 is inner wing rear axle housing, and 19 is screw, and 23 is bearing pin.
The specific embodiment
In order to make the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein is only in order to explain the utility model, and be not used in restriction the utility model.
As shown in Figure 1 to 4, the piece-picking type fold mechanism for laterally folded missile wing that the utility model provides comprises the outer wing skeleton 1 of outer wing, be fixed on outer wing front apron 6 and the outer wing backboard 7 on outer wing skeleton 1 by screw 15 and screw 19, inner wing skeleton 2 in inner wing, be fixed on inner wing front apron 8 and the inner wing backboard 9 on inner wing skeleton 2 by screw 15 and screw 19, be fixed on before the torque arm on inner wing adapter 11 after adapter 10 and torque arm by marking closely screw, be arranged on successively the inner wing front shaft sleeve 17 at inner wing two ends, inner wing rear axle housing 18, Compress Spring 13 and spring catch 12, be fixed on the release catch 16 on inner wing skeleton 2 by release catch rotating shaft 14, torque arm 3, mark closely screw 4, limited block 5, latch, stop screw and bearing pin 23.
Outer wing front apron 6 and outer wing backboard 7 are inserted in the both ends of the surface circular hole of outer wing skeleton 1 successively, be fixed on successively the common formation outer wing of outer wing skeleton 1 by screw 15 and screw 19.
By inner wing front apron 8 and inner wing backboard 9 successively with inner wing skeleton on corresponding aperture axial alignment, be fixed on inner wing skeleton 2 by screw 15 and screw 19, then pack successively before torque arm adapter 11 after adapter 10 and torque arm into, wherein before torque arm after adapter 10 and torque arm adapter 11 can be in the rectangular opening on the top of inner wing skeleton 2 can before and after move freely.Inner wing front shaft sleeve 17, inner wing rear axle housing 18, Compress Spring 13 and spring catch 12 are packed in inner wing skeleton 2 bottom circular holes successively, subsequently release catch 16 is fixed on inner wing skeleton 2 by release catch rotating shaft 14, the ball-and-socket of release catch 16 and spring catch 12 bulbs connect, wherein release catch 16 is under the effect of peripheral force, release catch rotating shaft 14 axial rotation relatively, above-mentioned part forms inner wing jointly.
By outer wing and inner wing alignment, keep outer foramen alare coaxial with interior foramen alare, then successively adapter 11 after adapter before torque arm 10 and torque arm is dialed in the circular hole of outer wing skeleton 1 along inner wing skeleton 2 axially bored lines respectively by latch, use is marked closely screw and respectively itself and inner wing skeleton 2 is fixed together, and so far outer wing is connected as a whole by adapter before torque arm 10 with adapter after torque arm 11 with inner wing.
The rectangle slotted eye bottom surface of torque arm 3 one end and limited block 5 is connected, and by bearing pin 23, torque arm 3 one end and limited block 5 are connected as a single entity, then from rear to front successively through the rectangular channel of adapter 10 before the rectangular opening of the circular hole of adapter 11 after outer wing skeleton 1 rear end circular hole, torque arm, inner wing skeleton 2 and circular hole, torque arm, with the counterbore bottom surface butt of outer wing skeleton 1; Make limited block 5 rotate certain angle by instrument, himself circular hole is alignd with the screwed hole on outer wing skeleton 1, tighten and mark closely screw 4.
In the utility model, when outer wing is in the time launching locking state, stir backward spring catch 12 to inner wing skeleton 2 screwed hole places by latch, be screwed into respectively stop screw at inner wing skeleton 2 two ends, by spring catch 12 releases, get final product the circumferential constraint of release outer wing, relatively interior outer wing wingfold is packed in emitter; In the time that folding wing is in emitter, in folded state, when folding wing is from emitter moment out, the suffered circumferential constraint of folding wing is disengaged, outer wing is under the elastic potential energy effect of torque arm 3, launch rapidly, drive release catch 16 to rotate around release catch rotating shaft 14 simultaneously, after release catch rotating shaft 14 rotates to an angle, remove the axial constraint of spring catch 12, spring catch 12, under the spring-force driven dual of Compress Spring 13, inserts rapidly in the axis hole of outer wing front apron 6 and outer wing backboard 7, and outer wing is locked.
In the utility model, key is the space that utilizes missile wing inner limited, piece-picking type fold mechanism by part compositions such as outer wing skeleton 1, outer wing front apron 6, outer wing backboard 7, torque arm 3, release catch rotating shaft 14, release catch 16, spring catch 12, Compress Springs 13 is realized the interlock of outer wing skeleton 1, release catch 16, spring catch 12, Compress Spring 13, and then realizes expansion and the locking of outer wing 1.
Owing to being subject to the restriction of folding wings release form and geometric space, the utility model is suitable for and need to dwindles the volume in storage, transportation, and when guided missile flies away from after emitter, missile wing Automatic-expanding, guarantees guided missile normal flight.
Those skilled in the art will readily understand; the foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all any modifications of doing within spirit of the present utility model and principle, be equal to and replace and improvement etc., within all should being included in protection domain of the present utility model.
Claims (4)
1. for a piece-picking type fold mechanism for laterally folded missile wing, be arranged between wing outer wing and inner wing, for realizing relatively rotating and locking between described outer wing and inner wing, it is characterized in that, this fold mechanism comprises:
Outer wing front apron (6) and outer wing backboard (7), it is fixedly installed on respectively the two side for mating with inner wing on outer wing skeleton (1) by screw;
Inner wing front apron (8) and inner wing backboard (9), it is fixedly mounted on inner wing skeleton (2) with on corresponding both sides end face outer wing coupling by screw;
Adapter (11) after adapter (10) and torque arm before torque arm, insert in the two side on described inner wing skeleton (2) by the through hole on inner wing front apron (8) and inner wing backboard (9) respectively its one end, the other end inserts respectively in the two side on outer wing skeleton (1) by the through hole on described outer wing front apron (6) and outer wing backboard (7), and after this front adapter (10) and torque arm, between adapter (11), be provided with and be applied with prestressed torque arm (3), can realize the relative inner wing of described outer wing by its effect and connect rotationally;
Lockable mechanism, it is arranged on the described both sides end face of inner wing skeleton (2), and it can realize both lockings at described outer wing after inner wing rotates expansion or folding putting in place.
2. a kind of piece-picking type fold mechanism for laterally folded missile wing according to claim 1, it is characterized in that, described lockable mechanism comprises the spring catch (12) in the perforate that is arranged on inner wing skeleton (2) side end face, its one end is arranged in described perforate by Compress Spring (13), the other end can stretch in the side-wall hole of described outer wing skeleton (1) by this Compress Spring (13) effect after the relative inner wing of described outer wing launches to put in place, realizes both and relatively fixes and locking.
3. a kind of piece-picking type fold mechanism for laterally folded missile wing according to claim 2, it is characterized in that, described lockable mechanism also comprises release catch rotating shaft (14) reconciliation stopper sheet (16), this release catch (16) is fixed on and is arranged on inner wing skeleton (2) by release catch rotating shaft (14), bulb on ball-and-socket and spring catch (12) on this release catch (16) connects with by its constraint, described release catch (16) is under the effect of peripheral force, release catch rotating shaft (14) axial rotation relatively, thereby can remove the constraint to this spring catch (12).
4. according to a kind of piece-picking type fold mechanism for laterally folded missile wing described in any one in claim 1-3, it is characterized in that, this mechanism also comprises inner wing front shaft sleeve (17) and inner wing rear axle housing (18), described lockable mechanism is two covers, and spring catch (12) is wherein sleeved in the perforate of described inner wing skeleton (2) side end face by this inner wing front shaft sleeve (17) and inner wing rear axle housing (18) respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320713576.3U CN203629478U (en) | 2013-11-13 | 2013-11-13 | Paddle-type folding mechanism used for horizontally folding missile wings |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320713576.3U CN203629478U (en) | 2013-11-13 | 2013-11-13 | Paddle-type folding mechanism used for horizontally folding missile wings |
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| CN203629478U true CN203629478U (en) | 2014-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201320713576.3U Expired - Lifetime CN203629478U (en) | 2013-11-13 | 2013-11-13 | Paddle-type folding mechanism used for horizontally folding missile wings |
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| CN (1) | CN203629478U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104165553A (en) * | 2014-09-02 | 2014-11-26 | 湖北航天技术研究院总体设计所 | Locking and unlocking mechanism for folding wing |
| CN104677201A (en) * | 2015-02-09 | 2015-06-03 | 浙江理工大学 | Pucker rudder development mechanism for quickly adjusting attack angle |
| CN105258933A (en) * | 2015-11-06 | 2016-01-20 | 航天科工哈尔滨风华有限公司 | Folded rudder core unfolding testing apparatus |
| CN105737685A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Wing face double-direction double-position folding structure |
| CN106225604A (en) * | 2016-07-29 | 2016-12-14 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN107289822A (en) * | 2017-07-19 | 2017-10-24 | 贵州航天风华精密设备有限公司 | A kind of missile airfoil fold mechanism with multiple rows of torsion bar |
| CN109405669A (en) * | 2018-08-31 | 2019-03-01 | 江西洪都航空工业集团有限责任公司 | A kind of Quick Release aerofoil automatic locking mechanism |
| CN114199083A (en) * | 2021-11-22 | 2022-03-18 | 上海机电工程研究所 | Missile folding rudder self-locking system |
-
2013
- 2013-11-13 CN CN201320713576.3U patent/CN203629478U/en not_active Expired - Lifetime
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104165553A (en) * | 2014-09-02 | 2014-11-26 | 湖北航天技术研究院总体设计所 | Locking and unlocking mechanism for folding wing |
| CN104165553B (en) * | 2014-09-02 | 2016-07-06 | 湖北航天技术研究院总体设计所 | A kind of locking solution latch mechanism for folding wings |
| CN104677201A (en) * | 2015-02-09 | 2015-06-03 | 浙江理工大学 | Pucker rudder development mechanism for quickly adjusting attack angle |
| CN104677201B (en) * | 2015-02-09 | 2016-08-24 | 浙江理工大学 | Quickly adjust the angle of attack with folding rudder development mechanism |
| CN105258933A (en) * | 2015-11-06 | 2016-01-20 | 航天科工哈尔滨风华有限公司 | Folded rudder core unfolding testing apparatus |
| CN105737685A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Wing face double-direction double-position folding structure |
| CN106225604A (en) * | 2016-07-29 | 2016-12-14 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN106225604B (en) * | 2016-07-29 | 2018-01-26 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN107289822A (en) * | 2017-07-19 | 2017-10-24 | 贵州航天风华精密设备有限公司 | A kind of missile airfoil fold mechanism with multiple rows of torsion bar |
| CN109405669A (en) * | 2018-08-31 | 2019-03-01 | 江西洪都航空工业集团有限责任公司 | A kind of Quick Release aerofoil automatic locking mechanism |
| CN114199083A (en) * | 2021-11-22 | 2022-03-18 | 上海机电工程研究所 | Missile folding rudder self-locking system |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140604 |