CN104977168A - Closure release device - Google Patents
Closure release device Download PDFInfo
- Publication number
- CN104977168A CN104977168A CN201510413133.6A CN201510413133A CN104977168A CN 104977168 A CN104977168 A CN 104977168A CN 201510413133 A CN201510413133 A CN 201510413133A CN 104977168 A CN104977168 A CN 104977168A
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- blanking cover
- hinge
- driving plate
- closure
- active hinge
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Abstract
The invention discloses a closure release device, whcih comprises a closure folding mechanism, a closure initial locking mechanism and a closure unfolding-in-place locking mechanism, wherein the closure folding mechanism comprises a left driving plate, a left driven plate, a right driving plate, a right driven plate, an upper guide rail and a lower guide rail; the closure initial locking mechanism comprises an explosive bolt and a base; the closure unfolding-in-place locking mechanism comprises a rotating shaft, a torsional spring and push pins; the torsional spring, the left driving plate, and the right driving plate are fixed on the base via the rotating shaft; one end of the torsional spring is fixed on the base, and the other end of the torsional spring is fixed on the left driving plate or the right driving plate so as act as a driving force for enbaling the left driving plate or the right driving plate to rotate around the rotating shaft; and both the left driving plate and the right driving plate are movably connected with the base via the push pins. Accoridng to the closure release device, the applied principle is simple, practicability is strong, the function of blocking a jet nozzle of an engine can be met, jettisoning is not needed, safety influences on a carrier aircraft are eliminated, repeated use cna be achieved, the development cycle is shortened, and the development cost is reduced.
Description
Technical field
The present invention relates to a kind of blanking cover releasing means.
Background technology
When guided missile empty station is tested, be test engine performance, the disposable throwing of general employing puts formula blanking cover shutoff engine tail nozzle.According to carrier aircraft mount point Airflow Environment characteristic and safety requirements, suitable blocking cover structure and throwing must be selected to put mode, and carry out the emulation of blanking cover trajectory, to guarantee that blanking cover throws the security of putting.But in practical flight process, the qigong circumstance complication of carrier aircraft mount point, blanking cover trajectory simulation process cannot consider unexpected factor, and unpredictable blanking cover is thrown and put the potential danger of state to carrier aircraft comprehensively.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
Summary of the invention
The technical issues that need to address of the present invention are to provide a kind of non-throwing and put formula blanking cover releasing means.Both met the functional requirement of shutoff engine tail nozzle when blanking cover is locked, when realizing again blanking cover release, security implication had not been produced to carrier aircraft.
For solving technical matters of the present invention, the technical solution used in the present invention is:
A kind of blanking cover releasing means, this blanking cover releasing means comprises blanking cover fold mechanism, the initial latch mechanism of blanking cover and blanking cover and is deployed into position locking mechanism, described blanking cover fold mechanism comprises left active hinge, left driven hinge, right active hinge, right driven hinge, upper rail and lower guideway, between described left active hinge, left driven hinge and right active hinge, all adopt straight pin to be flexibly connected between right driven hinge, described upper rail and lower guideway are connected by mechanical connection and base; The initial latch mechanism of described blanking cover comprises blasting bolt and base, and described blasting bolt makes left passive blade by securing member, left active blade is reliably in initial fold state; Described blanking cover is deployed into position locking mechanism and comprises stage clip and distribution, described stage clip, distribution are fixed on base, when after the initial latch mechanism release of blanking cover, after left active hinge, right active hinge are deployed into certain angle around the shaft by torsion spring, promote under the effect of stage clip, wedge in the bellmouth of left active hinge, right active hinge, locking blanking cover left active hinge, right active hinge.
The rectangular channel of described upper rail, lower guideway makes the cylindrical end of left passive blade, right passive blade only move along rectangular channel length direction.
Blanking cover releasing means of the present invention mainly adopts slider-crank mechanism principle, devises two symmetrical slider-crank mechanisms, at initial position locking slave arm, to reach the initial lock state of blanking cover; When slave arm unlocks state, take torsion spring as power, drive master arm to rotate, thus make slave arm band movable slider along guide rail movement, when arriving predeterminated position, locking master arm, completes blanking cover release conditions.
Beneficial effect of the present invention: the principle that this blanking cover releasing means uses is simple, practical, meets the function of shutoff engine tail nozzle, put because throwing again, eliminate the security implication to carrier aircraft, and reusable, shorten the lead time and decrease development cost.
Accompanying drawing explanation
Fig. 1 is blanking cover slider-crank mechanism principle figure of the present invention.
Fig. 2 is blanking cover releasing means initial fold view of the present invention.
Fig. 3 a is along A-A to schematic diagram in Fig. 2.
Fig. 3 b is along B-B to schematic diagram in Fig. 2.
Fig. 4 is blanking cover releasing means deployed condition schematic diagram of the present invention.
Fig. 5 is along A-A to schematic diagram in Fig. 4.
1, frame, 2, master arm, 3, slave arm, 4, slide block, 5, driving moment, 6, slide block movement direction, 7, base, 8, blasting bolt, 9, straight pin, 10, upper rail, 11, promote, 12, right active hinge, 13, right driven hinge, 14, lower guideway, 15, left driven hinge, 16, left active hinge, 17, rotating shaft, 18, torsion spring, 19, engine tail nozzle, 20, guide rail rectangular channel, 21, stage clip.
Embodiment
Below in conjunction with the drawings and specific embodiments, the invention will be further described.Following examples, only for illustration of the present invention, are not used for limiting the scope of the invention.
Fig. 2, Fig. 3 a, Fig. 3 a, shown in Fig. 5, blanking cover releasing means of the present invention, this blanking cover releasing means comprises blanking cover fold mechanism, the initial latch mechanism of blanking cover and blanking cover are deployed into position locking mechanism, blanking cover fold mechanism comprises left active hinge 16, left driven hinge 15, right active hinge 12, right driven hinge 13, upper rail 10 and lower guideway 14, two covers are main, driven hinge is left, the right side is symmetrical arranged, self-movement, do not interfere with each other, left active hinge 16, with right active hinge 12 between left driven hinge 15, straight pin 9 is all adopted to be flexibly connected between right driven hinge 13, thus formation rotary gemel, upper rail 10 and lower guideway 14 are connected by mechanical connection and base 1, the initial latch mechanism of blanking cover comprises blasting bolt 8 and base 1, and blasting bolt 8 makes left passive blade 15 by securing member, left active blade 16 is reliably in initial fold state, blanking cover is deployed into position locking mechanism and comprises stage clip 21 and promote 11, stage clip 21, distribution 11 are fixed on base 7, when after the initial latch mechanism release of blanking cover, left active hinge 16, right active hinge 12 by torsion spring 18 around the shaft 17 be deployed into certain angle after, promote 11 under the effect of stage clip 21, wedge in the bellmouth of left active hinge 16, right active hinge 12, locking blanking cover left active hinge 16, right active hinge 12.
Shown in Fig. 3 a and Fig. 3 a, the rectangular channel 20 of upper rail 10, lower guideway 14 makes the cylindrical end of left passive blade 15, right passive blade 13 only move along rectangular channel 20 length direction.
Shown in Fig. 4, for left side blanking cover fold mechanism: torsion spring 18 one end is fixed on base 1, the other end is fixed in left active hinge 16, as the power source of mechanism deploying; Left driven hinge 15 is connected by straight pin 9 with left active hinge 16, and form rotary gemel, wherein left driven hinge 15 is slave arm, and left active hinge 16 is master arm; The movement locus of the left driven hinge 15 of rectangular channel constraint of upper rail 10, lower guideway 14, make its cylindrical end only along side-to-side movement in rectangular channel, namely the cylindrical end of left driven hinge 15 forms moving sets and the revolute of slave arm; Be connected as blanking cover fold mechanism rack section with body by base 1.
The initial latch mechanism of blanking cover forms primarily of blasting bolt 8 and base 1, and blasting bolt 8 makes left passive blade 15 by securing member, left active blade 16 is reliably in initial fold state.
Blanking cover folds into position locking mechanism and then adopts typical spring to promote the latch mechanism of formula.In Fig. 4, label 19 place is engine tail nozzle.
Shown in Fig. 1, blanking cover releasing means of the present invention mainly adopts slider-crank mechanism principle, devises two symmetrical slider-crank mechanisms, at initial position locking slave arm 3, to reach the initial lock state of blanking cover; When slave arm 3 unlocks state, take torsion spring as power, master arm 2 is driven to rotate, thus make slave arm 3 be with movable slider 4 along frame 1(containing guide rail) motion, when arriving predeterminated position, locking master arm 2, label 5 place forms driving moment, label 6 place points to slide block movement direction, thus completes blanking cover release conditions.
Therefore, left active hinge 16, left driven hinge 15, rotating shaft 17, straight pin 9, upper rail 10, lower guideway 14 form a slider-crank mechanism, and torsion spring 18 is as power source.
Workflow is as follows: when blanking cover is in initial fold state, by the blasting bolt between mechanism and body, blanking cover is reliably lock onto initial position, to realize the function of blocking cap mechanism shutoff engine tail nozzle; When engine tail nozzle sealed condition must be removed, mechanism accepts instruction, blasting bolt unlocks, initiatively hinge links driven hinge make slide block along guide rail directed movement under the effect of torsion spring, after expansion puts in place, move apart engine tail nozzle position, remove engine tail nozzle sealed condition, rear distribution locks blanking cover under spring force, realizes the folding release of blanking cover.
Claims (2)
1. a blanking cover releasing means, it is characterized in that: this blanking cover releasing means comprises blanking cover fold mechanism, the initial latch mechanism of blanking cover and blanking cover and is deployed into position locking mechanism, described blanking cover fold mechanism comprises left active hinge, left driven hinge, right active hinge, right driven hinge, upper rail and lower guideway, between described left active hinge, left driven hinge and right active hinge, all adopt straight pin to be flexibly connected between right driven hinge, described upper rail and lower guideway are connected by mechanical connection and base; The initial latch mechanism of described blanking cover comprises blasting bolt and base, and described blasting bolt makes left passive blade by securing member, left active blade is reliably in initial fold state; Described blanking cover is deployed into position locking mechanism and comprises stage clip and distribution, described stage clip, distribution are fixed on base, when after the initial latch mechanism release of blanking cover, after left active hinge, right active hinge are deployed into certain angle around the shaft by torsion spring, promote under the effect of stage clip, wedge in the bellmouth of left active hinge, right active hinge, locking blanking cover left active hinge, right active hinge.
2. a kind of blanking cover releasing means according to claim 1, is characterized in that: the rectangular channel of described upper rail, lower guideway makes the cylindrical end of left passive blade, right passive blade only move along rectangular channel length direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510413133.6A CN104977168B (en) | 2015-07-15 | 2015-07-15 | A kind of blanking cover release device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510413133.6A CN104977168B (en) | 2015-07-15 | 2015-07-15 | A kind of blanking cover release device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104977168A true CN104977168A (en) | 2015-10-14 |
| CN104977168B CN104977168B (en) | 2017-09-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510413133.6A Active CN104977168B (en) | 2015-07-15 | 2015-07-15 | A kind of blanking cover release device |
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| Country | Link |
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| CN (1) | CN104977168B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109488460A (en) * | 2017-09-12 | 2019-03-19 | 江西洪都航空工业集团有限责任公司 | A kind of supersonic inlet blanking cover device |
| CN110905686A (en) * | 2019-10-30 | 2020-03-24 | 北京动力机械研究所 | Multi-flow-path combined engine starting protection structure |
Citations (6)
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| US3580529A (en) * | 1967-09-21 | 1971-05-25 | Oerlikon Buehrle Ag | Rocket with spreadable empennage |
| US3879942A (en) * | 1972-06-22 | 1975-04-29 | Dynamit Nobel Ag | Partition for rocket engines |
| DE3620173A1 (en) * | 1986-06-14 | 1987-12-17 | Dynamit Nobel Ag | Nozzle closure |
| CN103630362A (en) * | 2013-11-29 | 2014-03-12 | 中国航天科技集团公司第六研究院第十一研究所 | Closure actuation device and method for ramjet separation test |
| CN203811056U (en) * | 2014-05-06 | 2014-09-03 | 江西洪都航空工业集团有限责任公司 | Unlocking device for explosive bolt |
| CN204788955U (en) * | 2015-07-15 | 2015-11-18 | 江西洪都航空工业集团有限责任公司 | Blanking cover release |
-
2015
- 2015-07-15 CN CN201510413133.6A patent/CN104977168B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3580529A (en) * | 1967-09-21 | 1971-05-25 | Oerlikon Buehrle Ag | Rocket with spreadable empennage |
| US3879942A (en) * | 1972-06-22 | 1975-04-29 | Dynamit Nobel Ag | Partition for rocket engines |
| DE3620173A1 (en) * | 1986-06-14 | 1987-12-17 | Dynamit Nobel Ag | Nozzle closure |
| CN103630362A (en) * | 2013-11-29 | 2014-03-12 | 中国航天科技集团公司第六研究院第十一研究所 | Closure actuation device and method for ramjet separation test |
| CN203811056U (en) * | 2014-05-06 | 2014-09-03 | 江西洪都航空工业集团有限责任公司 | Unlocking device for explosive bolt |
| CN204788955U (en) * | 2015-07-15 | 2015-11-18 | 江西洪都航空工业集团有限责任公司 | Blanking cover release |
Non-Patent Citations (2)
| Title |
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| 周磊等: "整体式固体火箭冲压发动机尾喷管堵盖研究", 《弹箭与制导学报》 * |
| 张全等: "一种先进的固体火箭冲压发动机堵盖设计", 《现代防御技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109488460A (en) * | 2017-09-12 | 2019-03-19 | 江西洪都航空工业集团有限责任公司 | A kind of supersonic inlet blanking cover device |
| CN109488460B (en) * | 2017-09-12 | 2021-02-19 | 江西洪都航空工业集团有限责任公司 | Blocking cover device for supersonic air inlet |
| CN110905686A (en) * | 2019-10-30 | 2020-03-24 | 北京动力机械研究所 | Multi-flow-path combined engine starting protection structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104977168B (en) | 2017-09-08 |
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