CN106853871A - A kind of wedge lock separating mechanism - Google Patents
A kind of wedge lock separating mechanism Download PDFInfo
- Publication number
- CN106853871A CN106853871A CN201510892898.2A CN201510892898A CN106853871A CN 106853871 A CN106853871 A CN 106853871A CN 201510892898 A CN201510892898 A CN 201510892898A CN 106853871 A CN106853871 A CN 106853871A
- Authority
- CN
- China
- Prior art keywords
- connecting shaft
- aircraft
- launching tube
- wedge
- separating mechanism
- 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.)
- Pending
Links
- 230000005540 biological transmission Effects 0.000 claims abstract description 3
- 238000000034 method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The invention discloses a kind of wedge lock separating mechanism, including：Aircraft connecting shaft, wedge, launching tube connecting shaft, housing and shear screw；The aircraft connecting shaft is connected with aircraft afterbody；The wedge is stuck between aircraft connecting shaft and launching tube connecting shaft；The relative position of shear screw fixed transmission cylinder connecting shaft and housing；Launching tube connecting shaft is connected with launching tube afterbody；Housing is fixedly linked with emitter tailstock.
Description
Technical field
The present invention relates to vehicle launch barrel structure design field, and in particular to a kind of new wedge lock separating mechanism.
Background technology
The transmitting of gas piston tail pushing-type has launching tube radial dimension small, and the car launcher bicycle amount of shooting is big, and boosting stroke is long, has the advantages that good ejection trajectory performance, is just gradually being applied in the design of vehicle launch barrel structure.Fig. 1 show tail pushing-type emitter structural representation, including annular emission cylinder 01, the gas generator 02 in annular emission cylinder 01 is installed on successively, emitter tailstock 03 and aircraft 04, tail pushing-type emitter structure is special, in order to meet gas sealing requirement, emitter tailstock 03 must be close to the motion of the inwall of launching tube 01 in emission process, therefore traditional lever, bolt-type and magnesium ribbon formula locking separating mechanism can not all meet its Structural Design Requirement, for this, the present invention proposes a kind of novel wedge-shaped locking separating mechanism for being applied to the transmitting of aircraft tail pushing-type.The wedge lock separating mechanism can meet the strength and stiffness requirement under the conditions of gas sealing requirement and comfortable property axial direction big overload in emission process, and automatic unlocking ensures that aircraft is smoothly detached with launching tube under realizing launching operating mode transient conditions.
The content of the invention
The problem that the present invention is solved is the structural requirement that the isolating construction rarely having can not meet the transmitting of gas piston tail pushing-type；To solve described problem, the present invention provides a kind of wedge lock separating mechanism.
A kind of wedge lock separating mechanism that the present invention is provided, including：Aircraft connecting shaft, wedge, launching tube connecting shaft, housing and shear screw；The aircraft connecting shaft is connected with aircraft afterbody；The wedge is stuck between aircraft connecting shaft and launching tube connecting shaft；The relative position of shear screw fixed transmission cylinder connecting shaft and housing；Launching tube connecting shaft is connected with launching tube afterbody；Housing is fixedly linked with emitter tailstock.
Further, the aircraft connecting shaft has radial groove, and the wedge type block is located between the groove and launching tube connecting shaft inwall.
Further, when locking separating mechanism is in comfortable property axial direction big overload, wedge, launching tube connecting shaft and housing pin aircraft connecting shaft.
Further, when locking separating mechanism is in and separates operating mode, emitter tailstock promotes aircraft to travel forward, and launching tube connecting shaft cuts shear screw, and launching tube connecting shaft is extracted from housing, and wedge is separated with aircraft connecting shaft.Before aircraft goes out cylinder, there is no relative motion between aircraft connecting shaft and housing, it is ensured that gas sealing requirement.
Brief description of the drawings
Fig. 1 is tail pushing-type emitter structural representation；
Fig. 2 is the structural representation of the wedge lock separating mechanism that the embodiment of the present invention is provided；
Fig. 3 is the separation initial time schematic diagram of the wedge lock separating mechanism that the embodiment of the present invention is provided；
Fig. 4 is the separation finish time schematic diagram of the wedge lock separating mechanism that the embodiment of the present invention is provided.
Specific embodiment
New wedge lock separating mechanism proposed by the invention is described in further detail below in conjunction with the drawings and specific embodiments.According to following explanation and claims, advantages and features of the invention will become apparent from.It should be noted that accompanying drawing is only used for conveniently, lucidly aiding in illustrating the purpose of the embodiment of the present invention.
Fig. 2 is wedge lock separating mechanism schematic diagram, including：Aircraft connecting shaft 1, wedge 2, launching tube connecting shaft 3, housing 4 and shear screw 5；Wherein, the aircraft connecting shaft 1 is connected with aircraft afterbody；Wedge 2 is connected with aircraft connecting shaft 1, launching tube connecting shaft 3 and housing 4 by contacting；Launching tube connecting shaft 3 is connected with launching tube afterbody；Housing 4 is fixedly linked with emitter tailstock；Shear screw 5 is connected with launching tube connecting shaft 3 and housing 4, launching tube connecting shaft 3 is relatively fixed with housing 4.
Specifically, as shown in Figure 2, when locking separating mechanism is in comfortable property axial direction big overload, there is no relative motion between emitter tailstock and launching tube, launching tube connecting shaft 3 limits wedge 2 and moves, aircraft connecting shaft 1 is under the locking effect of wedge 2, launching tube connecting shaft 3 and housing 4, it is impossible to be axially moved.
Locking separating mechanism is in when separating operating mode, as shown in Figure 3 and Figure 4, there is relative motion between emitter tailstock and launching tube, launching tube connecting shaft 3 cuts shear screw 5, launching tube connecting shaft is extracted from housing 4,4 wedges 2 are separated with aircraft connecting shaft 1 under gravity, and moment is clashed into buffer when tailstock promotes aircraft to reach nozzle, and aircraft connecting shaft 1 is extracted from housing 5 and realizes that aircraft is smoothly detached with launching tube.
Although the present invention is disclosed as above with preferred embodiment; but it is not for limiting the present invention; any those skilled in the art are without departing from the spirit and scope of the present invention; the methods and techniques content that may be by the disclosure above makes possible variation and modification to technical solution of the present invention; therefore; every content without departing from technical solution of the present invention; any simple modification, equivalent variation and modification made to above example according to technical spirit of the invention, belong to the protection domain of technical solution of the present invention.
Claims (4)
1. a kind of wedge lock separating mechanism, it is characterised in that including：Aircraft connecting shaft, wedge, launching tube connecting shaft, housing and shear screw；The aircraft connecting shaft is connected with aircraft afterbody；The wedge is stuck between aircraft connecting shaft and launching tube connecting shaft；The relative position of shear screw fixed transmission cylinder connecting shaft and housing；Launching tube connecting shaft is connected with launching tube afterbody；Housing is fixedly linked with emitter tailstock.
2., according to the wedge lock separating mechanism described in claim 1, it is characterised in that the aircraft connecting shaft has radial groove, the wedge type block is located between the groove and launching tube connecting shaft inwall.
3. according to the wedge lock separating mechanism described in claim 1, it is characterised in that when locking separating mechanism is in comfortable property axial direction big overload, wedge, launching tube connecting shaft and housing pin aircraft connecting shaft.
4. according to the wedge lock separating mechanism described in claim 1, it is characterised in that locking separating mechanism is in when separating operating mode, aircraft travels forward, launching tube connecting shaft cuts shear screw, and launching tube connecting shaft is extracted from housing, and wedge is separated with aircraft connecting shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510892898.2A CN106853871A (en) | 2015-12-08 | 2015-12-08 | A kind of wedge lock separating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510892898.2A CN106853871A (en) | 2015-12-08 | 2015-12-08 | A kind of wedge lock separating mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106853871A true CN106853871A (en) | 2017-06-16 |
Family
ID=59132744
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510892898.2A Pending CN106853871A (en) | 2015-12-08 | 2015-12-08 | A kind of wedge lock separating mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106853871A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871063A (en) * | 2018-07-20 | 2018-11-23 | 航天科工仿真技术有限责任公司 | A kind of fixed structure and fire extinguisher bomb launching tube device of fire extinguisher bomb and launching tube |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5400713A (en) * | 1994-03-09 | 1995-03-28 | Thiokol Corporation | Stage separation and thrust reduction apparatus |
| RU2248521C2 (en) * | 2003-05-06 | 2005-03-20 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Method for providing for safety of launcher at rocket firing and rocket for its realization |
| US20060214062A1 (en) * | 2004-07-30 | 2006-09-28 | Agency For Defense Development | Missile ejection system and launching canister thereof |
| CN101875404A (en) * | 2009-12-17 | 2010-11-03 | 北京理工大学 | Sealed small low-impact release screw bolt |
| CN102155883A (en) * | 2010-12-27 | 2011-08-17 | 北京理工大学 | Small-size quickly separated firer-unlocking bolt |
| KR20140087464A (en) * | 2012-12-31 | 2014-07-09 | 한국항공우주연구원 | Storage device for tension bolt |
-
2015
- 2015-12-08 CN CN201510892898.2A patent/CN106853871A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5400713A (en) * | 1994-03-09 | 1995-03-28 | Thiokol Corporation | Stage separation and thrust reduction apparatus |
| RU2248521C2 (en) * | 2003-05-06 | 2005-03-20 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Method for providing for safety of launcher at rocket firing and rocket for its realization |
| US20060214062A1 (en) * | 2004-07-30 | 2006-09-28 | Agency For Defense Development | Missile ejection system and launching canister thereof |
| CN101875404A (en) * | 2009-12-17 | 2010-11-03 | 北京理工大学 | Sealed small low-impact release screw bolt |
| CN102155883A (en) * | 2010-12-27 | 2011-08-17 | 北京理工大学 | Small-size quickly separated firer-unlocking bolt |
| KR20140087464A (en) * | 2012-12-31 | 2014-07-09 | 한국항공우주연구원 | Storage device for tension bolt |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871063A (en) * | 2018-07-20 | 2018-11-23 | 航天科工仿真技术有限责任公司 | A kind of fixed structure and fire extinguisher bomb launching tube device of fire extinguisher bomb and launching tube |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170616 |
|
| RJ01 | Rejection of invention patent application after publication |