CN103569350B - Initiative missile wing mechanism - Google Patents
Initiative missile wing mechanism Download PDFInfo
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- CN103569350B CN103569350B CN201310547541.1A CN201310547541A CN103569350B CN 103569350 B CN103569350 B CN 103569350B CN 201310547541 A CN201310547541 A CN 201310547541A CN 103569350 B CN103569350 B CN 103569350B
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- missile wing
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- gear
- missile
- inner gear
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Abstract
The invention relates to an initiative missile wing mechanism, which belongs to the technical field of an aircraft. A missile wing can be initiatively ejected through a control command at a flight time according to the requirement. An unlocking device consisting of a gear mechanism and a thread bushing has an unlocking function, the missile wing is driven to be unfolded by utilizing a spring determined by an acting force, so that the unfolding time is determined, and the unfolding synchronism is good. By adopting a locking pin, the missile wing is ensured to be accurately positioned and reliably locked after the missile wing is turned to a predetermined angle, the interference on a missile body is small, and the gesture stability of a folding wing in the flying process of a missile can be maintained. By adopting the compact miniaturized structure, the initiative missile wing mechanism is particularly applicable to the annular space with limited radial size.
Description
Technical field
The present invention relates to a kind of initiatively missile wing mechanism, belong to vehicle technology field.
Background technology
Missile wing is the important component part of body.For reducing the lateral dimension of guided missile, saving the storing space of feedway, missile wing is folded in body.And missile wing need be launched to present different aerodynamic configuration structures to improve manoevreability and fighting capacity in certain flight period, therefore need the missile wing closed in body to launch in good time.The ejecting mechanism of missile wing is the key mechanism ensureing that missile wing launches smoothly, and its performance directly affects the stability of missile wing, rapidity and reliability.It launches the requirement that motion must meet duration of run, expanded angle, expansion asynchronism; When expansion puts in place, missile wing answers accurate positioning, reliable lock, little to bomb body interference.
Missile wing mechanisms a large amount of is at present passive type, missile wing is turned back superimposed to firing box (cylinder) inwall by these guided missiles before transmission, leave canister launcher moment Automatic-expanding under unwind force effect to put in place and lock, do not possess after leaving canister launcher as required in the function that certain flight period launches.Also have some initiatively missile wing mechanisms, priming system accepts ignition signal, drives single the span to open.But the bursting force of priming system and in-service time have uncertainty, and usually adopt single priming system to drive the mode of single the wing, therefore duration of run has uncertainty and launches synchronism poor.
Summary of the invention
The object of the invention is to solve problems of the prior art, proposing a kind of initiatively missile wing mechanism.
The object of the invention is to be achieved through the following technical solutions.
A kind of initiatively missile wing mechanism of the present invention, external equipment is anchor shaft; This mechanism comprises tripper, actuating device, latching device and missile wing;
Described release mechanism comprises motor, electric machine support, left box body, external gear, gear wheel shaft, inner gear, threaded connecting sleeve, spacing ring, stop nut, a pair needle bearing, a pair needle roller thrust bearing, key A, key B, clamp nut A, end cap, pair of bearings;
Described actuating device comprises spring A, rotating shaft, clamp nut B, right case and spring A Connection Block;
Described latching device comprises locking pin, spring B and blocking.
Gear wheel shaft is fixedly supported in the hole of inner gear by pair of bearings; It is spacing that the bearing on the left side carries out axial restraint by the end cap on the left side and the axle rank of gear wheel shaft; It is spacing that the bearing on the right carries out axial restraint by the axle rank of gear wheel shaft and the rank, hole of inner gear; External gear is connected with gear wheel shaft by key B; External gear is locked on gear wheel shaft by clamp nut A;
Inner gear engages with external gear, and inner gear to be radially supported in left box body by a pair needle bearing and to carry out axial location by a pair needle roller thrust bearing;
The needle roller thrust bearing on the left side carries out axial location by the axle rank on the rank, hole of left box body and inner gear, and the needle roller thrust bearing on the right carries out axial location by the axle rank on stop nut and inner gear; Threaded connecting sleeve is threaded with inner gear; The radial projection structure put that is threaded is stuck in the groove of spacing ring, and spacing ring is fixedly connected on left box body by screw;
Electric machine support is fixed by screws in left box body; Motor is fixed by screws on electric machine support; Motor is connected with gear wheel shaft the transmission carrying out torque by key A.
Missile wing coordinates with shaft hole shaft clearance, is connected in right case by rotating shaft; Rotating shaft is fixed on the support of right case by the axle rank on the left side and the clamp nut B on the right.
Rotating shaft is fixed in right case by nut; One end of spring A is connected on missile wing, and the other end of spring A is fixedly connected on spring A Connection Block.
Missile wing is when closure state, and there are locking pin, spring B and blocking in right case support left and right in hole respectively.Locking pin coordinates with the interporal lacuna of right case support, and the small end of locking pin withstands on missile wing entity place, and the large end place of locking pin is pushed down by spring B.Blocking pressing spring B, blocking be threaded connection be fixed on right case support hole outside;
Left box body and right case composition hollow cylinder, the center shaft at center and hollow cylinder that anchor shaft is positioned at hollow cylinder overlaps, and this active missile wing mechanism is placed in the hoop space outside anchor shaft.
Working process: peripheral equipment sends unlocking control signal to motor, driven by motor external gear rotates, thus inner gear rotates, and inner gear drives threaded connecting sleeve to be moved to the left, thus missile wing loses spacing, and missile wing launches to put in place under the effect of spring A.When the pin hole of missile wing goes to coaxial with locking pin, the locking pin located about right case support enters the pin hole place of missile wing under the effect of spring B, thus missile wing is deployed into position locking.
Beneficial effect
1) mechanism can accept control command in certain flight period as required and initiatively eject missile wing.2) tripper of gear mechanism and screw collar combination has simultaneously unlocking function, and the Spring driving missile wing adopting application force to determine launches, and therefore duration of run is determined and to launch synchronism good.3) missile wing forwards the accurate location after predetermined angular and reliable locking to adopt locking pin to ensure, little to bomb body interference, is conducive to keeping folding wings attitude stability in missile flight process.4) compact small light layout, is specially adapted to the annulus that radial dimension is limited.Active missile wing mechanism of the present invention can accept control command in certain flight period as required and initiatively eject missile wing.
This active missile wing mechanism has unblock, ejects and lock function, can reach fast, stablize and immediately launch accurately.Its mechanism's applied range, launches also to can be used on other relevant development mechanism except can be used for missile wing.
Accompanying drawing explanation
Fig. 1 is the composition schematic diagram of missile wing mechanism of the present invention;
Fig. 2 is the birds-eye view of missile wing mechanism of the present invention;
Fig. 3 is that the B-B of Fig. 2 analyses and observe partial enlarged drawing;
Fig. 4 is that missile wing is deployed into position locking view;
Fig. 5 is the A district enlarged drawing of Fig. 4.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described.
Embodiment
As shown in Figure 1, Figure 2 and Figure 3, a kind of initiatively missile wing mechanism, external equipment is anchor shaft 15; This mechanism comprises tripper, actuating device, latching device and missile wing 8;
Described release mechanism comprises motor 1, electric machine support 21, left box body 2, external gear 3, gear wheel shaft 4, inner gear 5, threaded connecting sleeve 6, spacing ring 7, stop nut 12, a pair needle bearing 13, a pair needle roller thrust bearing 14, key A20, key B17, clamp nut A16, end cap 18, pair of bearings 19;
Described actuating device comprises spring A11, rotating shaft 9, clamp nut B22, right case 10 and spring A Connection Block 26;
Described latching device comprises locking pin 23, spring B 24 and blocking 25.
Gear wheel shaft 4 is fixedly supported in the hole of inner gear 5 by pair of bearings 19; It is spacing that the bearing 19 on the left side carries out axial restraint by the end cap 18 on the left side and the axle rank of gear wheel shaft 4; It is spacing that the bearing 19 on the right carries out axial restraint by the axle rank of gear wheel shaft 4 and the rank, hole of inner gear 5; External gear 3 is connected with gear wheel shaft 4 by key B17; External gear 3 is locked on gear wheel shaft 4 by clamp nut A16;
Inner gear 5 engages with external gear 3, and inner gear 5 to be radially supported in left box body 2 by a pair needle bearing 13 and to carry out axial location by a pair needle roller thrust bearing 14;
The needle roller thrust bearing 14 on the left side carries out axial location by the axle rank on the rank, hole of left box body 2 and inner gear 5, and the needle roller thrust bearing 14 on the right carries out axial location by the axle rank on stop nut 12 and inner gear 5; Threaded connecting sleeve 6 is threaded with inner gear 5; Radial projection structure on threaded connecting sleeve 6 is stuck in the groove of spacing ring 7, and spacing ring 7 is fixedly connected on left box body 2 by screw;
Electric machine support 21 is fixed by screws in left box body 2; Motor 1 is fixed by screws on electric machine support 21; Motor 1 is connected with gear wheel shaft 4 transmission carrying out torque by key A20.
Missile wing 8 coordinates with rotating shaft 9 hole shaft clearance, is connected in right case 10 by rotating shaft 9; Rotating shaft 9 is fixed on the support of right case 10 by the axle rank on the left side and the clamp nut B on the right.
Rotating shaft 9 is fixed in right case 17 by nut; One end of spring A11 is connected on missile wing 8, and the other end of spring A11 is fixedly connected on spring A Connection Block 26.
Missile wing 8, when closure state, has locking pin 23, spring B 24 and blocking 25 respectively in hole, right case support left and right.Locking pin 23 coordinates with the interporal lacuna of right case 10 support, and the small end of locking pin 23 withstands on missile wing 8 entity place, and the large end place of locking pin 23 is pushed down by spring B 24.Block 25 pressing spring B24, blocking 25 be threaded connection be fixed on right case 10 support hole outside;
Left box body 2 and right case 10 form hollow cylinder, and the center shaft at center and hollow cylinder that anchor shaft 15 is positioned at hollow cylinder overlaps, and this active missile wing mechanism is placed in the hoop space outside anchor shaft 15.
Working process: peripheral equipment sends unlocking control signal to motor 1, motor 1 drives external gear 3 to rotate, thus inner gear 5 rotates, and inner gear 5 drives threaded connecting sleeve 6 to be moved to the left, thus missile wing 8 loses spacing, missile wing 8 launches to put in place under the effect of spring A11.When the pin hole 27 of missile wing 8 goes to coaxial with locking pin 23, as shown in Figure 4 and Figure 5, the locking pin 23 located about right case 10 support enters pin hole 27 place of missile wing 8 under the effect of spring B 24, thus missile wing 8 is deployed into position locking.
Claims (1)
1. an active missile wing mechanism, external equipment is anchor shaft; It is characterized in that: this mechanism comprises tripper, actuating device, latching device and missile wing;
Described tripper comprises motor, electric machine support, left box body, external gear, gear wheel shaft, inner gear, threaded connecting sleeve, spacing ring, the first stop nut, a pair first needle bearings, a pair second needle roller thrust bearings, key A, key B, the second clamp nut A, end cap, a pair the 3rd bearings;
Described actuating device comprises spring A, rotating shaft, the 3rd clamp nut B, right case and spring A Connection Block;
Described latching device comprises locking pin, spring B and blocking;
Gear wheel shaft is fixedly supported in the hole of inner gear by a pair the 3rd bearings; It is spacing that 3rd bearing on the left side carries out axial restraint by the end cap on the left side and the axle rank of gear wheel shaft; It is spacing that 3rd bearing on the right carries out axial restraint by the axle rank of gear wheel shaft and the rank, hole of inner gear; External gear is connected with gear wheel shaft by key B; External gear is locked on gear wheel shaft by the second clamp nut A;
Inner gear engages with external gear, and inner gear to be radially supported in left box body by a pair first needle bearings and to carry out axial location by a pair second needle roller thrust bearings;
Second needle roller thrust bearing on the left side carries out axial location by the axle rank on the rank, hole of left box body and inner gear, and second needle roller thrust bearing on the right carries out axial location by the axle rank on the first stop nut and inner gear; Threaded connecting sleeve is threaded with inner gear; The radial projection structure put that is threaded is stuck in the groove of spacing ring, and spacing ring is fixedly connected on left box body by the first screw;
Electric machine support is fixed in left box body by the second screw; Motor is fixed on electric machine support by the 3rd screw; Motor is connected with gear wheel shaft the transmission carrying out torque by key A;
Threaded connecting sleeve coordinates with missile wing is spacing, and missile wing coordinates with shaft hole shaft clearance, is connected in right case by rotating shaft; Rotating shaft is fixed on the support of right case by the axle rank on the left side and the 3rd clamp nut B on the right;
Rotating shaft is fixed in right case by the 4th nut; One end of spring A is connected on missile wing, and the other end of spring A is fixedly connected on spring A Connection Block;
Missile wing is when closure state, and there are locking pin, spring B and blocking in right case support left and right in hole respectively; Locking pin coordinates with the interporal lacuna of right case support, and the small end of locking pin withstands on missile wing entity place, and the large end place of locking pin is pushed down by spring B; Blocking pressing spring B, blocking be threaded connection be fixed on right case support hole outside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310547541.1A CN103569350B (en) | 2013-11-06 | 2013-11-06 | Initiative missile wing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310547541.1A CN103569350B (en) | 2013-11-06 | 2013-11-06 | Initiative missile wing mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103569350A CN103569350A (en) | 2014-02-12 |
| CN103569350B true CN103569350B (en) | 2015-07-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310547541.1A Active CN103569350B (en) | 2013-11-06 | 2013-11-06 | Initiative missile wing mechanism |
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| CN (1) | CN103569350B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596360B (en) * | 2015-01-12 | 2016-06-22 | 湖北航天技术研究院总体设计所 | A kind of folding wings unlocks Che Shou mechanism |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB574087A (en) * | 1940-05-29 | 1945-12-20 | George Alexander Roberts Powel | A method of and means for cutting wire entanglements |
| US6880780B1 (en) * | 2003-03-17 | 2005-04-19 | General Dynamics Ordnance And Tactical Systems, Inc. | Cover ejection and fin deployment system for a gun-launched projectile |
| CN102226671A (en) * | 2011-05-26 | 2011-10-26 | 浙江理工大学 | Redundant locking type longitudinal expansion mechanism of folding wing |
| CN202115709U (en) * | 2011-05-26 | 2012-01-18 | 浙江理工大学 | Space cam-spiral combined repeated folding unlocking mechanism |
| CN202126218U (en) * | 2011-05-26 | 2012-01-25 | 浙江理工大学 | Directly-connected lengthways unfolding mechanism for folding wings |
| CN202993998U (en) * | 2012-12-12 | 2013-06-12 | 江西洪都航空工业集团有限责任公司 | Integration structure of missile wing connecting lug grooves and missile body |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6921052B2 (en) * | 2003-11-28 | 2005-07-26 | The United States Of America As Represented By The Secretary Of The Army | Dragless flight control system for flying objects |
-
2013
- 2013-11-06 CN CN201310547541.1A patent/CN103569350B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB574087A (en) * | 1940-05-29 | 1945-12-20 | George Alexander Roberts Powel | A method of and means for cutting wire entanglements |
| US6880780B1 (en) * | 2003-03-17 | 2005-04-19 | General Dynamics Ordnance And Tactical Systems, Inc. | Cover ejection and fin deployment system for a gun-launched projectile |
| CN102226671A (en) * | 2011-05-26 | 2011-10-26 | 浙江理工大学 | Redundant locking type longitudinal expansion mechanism of folding wing |
| CN202115709U (en) * | 2011-05-26 | 2012-01-18 | 浙江理工大学 | Space cam-spiral combined repeated folding unlocking mechanism |
| CN202126218U (en) * | 2011-05-26 | 2012-01-25 | 浙江理工大学 | Directly-connected lengthways unfolding mechanism for folding wings |
| CN202993998U (en) * | 2012-12-12 | 2013-06-12 | 江西洪都航空工业集团有限责任公司 | Integration structure of missile wing connecting lug grooves and missile body |
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| Publication number | Publication date |
|---|---|
| CN103569350A (en) | 2014-02-12 |
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