CN202485556U - Deflating tool of missile launcher - Google Patents

Deflating tool of missile launcher Download PDF

Info

Publication number
CN202485556U
CN202485556U CN 201120449035 CN201120449035U CN202485556U CN 202485556 U CN202485556 U CN 202485556U CN 201120449035 CN201120449035 CN 201120449035 CN 201120449035 U CN201120449035 U CN 201120449035U CN 202485556 U CN202485556 U CN 202485556U
Authority
CN
China
Prior art keywords
push rod
concentric
deflating
cylinder
connector
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.)
Expired - Fee Related
Application number
CN 201120449035
Other languages
Chinese (zh)
Inventor
李新强
王焕林
阴亮
任侃
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Chinese Flight Test Establishment
Original Assignee
Chinese Flight Test Establishment
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Chinese Flight Test Establishment filed Critical Chinese Flight Test Establishment
Priority to CN 201120449035 priority Critical patent/CN202485556U/en
Application granted granted Critical
Publication of CN202485556U publication Critical patent/CN202485556U/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Abstract

The utility model belongs to the structural technical field of missile launching machinery in the fire control system of airplanes and especially relates to a special tool for missile launchers, which comprises a connecting body (1) and a threaded push rod (2). The connecting body (1) and the push rod (2) are threadedly connected together. The connecting body (1) is provided with two deflating holes (3). A knurling circular column is connected with a concentric positive hexagonal body so as to form the connecting body (1), while the knurling circular column and the concentric positive hexagonal body are integrally machined. Equal-height concentric screwed holes are arranged inside the hexagonal body. Concentric screwed holes are arranged inside the circular column. The upper end of the circular column is symmetrically provided with two through holes, namely deflating holes (3). The push rod (2) is formed by machining a whole circular column into three segments. The top end of the push rod (2) is provided with a knurling handle and the intermediate segment of the push rod is provided with screw threads. The other end of the push rod is provided with a concentric cylinder. The deflating tool of a missile launcher is designed to be small. When to be connected with the deflating valve of a missile launcher, the deflating tool can be more easily docked with the deflating valve, compared with a conventional longer deflating tool. The working difficulty is reduced especially in cold weather.

Description

Guided missile launcher venting instrument
Technical field
The invention belongs to aircraft fire control system MISSILE LAUNCHING frame for movement technical field, particularly relate to a kind of guided missile launcher specific purpose tool.
Background technology
At present; The many guided missile launchers of active service need use high-purity nitrogen to open hook and auxiliary impelling guided missile; When aircraft extracts, need discharge high nitrogen with anti-error impelling, so before extracting, need to use the venting instrument to discharge the high nitrogen in the guided missile launcher, existing venting instrument is complicated, the high inconvenient machine of cost is equipped with a plurality of venting work; Influence the efficient that the many hanging points of aircraft are exitted simultaneously, influence the carrying out of the work subsequent processing that extracts.To this problem, we design, made new guided missile launcher venting instrument, and are simple in structure, easy to use, with low cost, repeatedly on probation, respond well through aboard.
Summary of the invention
The objective of the invention is:
The purpose of the invention provides a kind of venting instrument of throwing the venting body in the guided missile launcher that more fast bleeds off, and shortens aircraft time, improves the aircraft rate of attendance.
Technical scheme of the present invention is:
Guided missile launcher venting instrument comprises connector 1 and threaded push rod 2, and connector 1 and push rod 2 are linked together by silking; 2 air vents 3 are arranged on the connector 1, and connector 1 is to connect with one heart positive hexahedron on the annular knurl cylinder to form, and the two integral body processes; High concentric threads hole is arranged in the hexahedron etc., the concentric threads hole is arranged in the cylinder, it is air vent that cylinder upper end symmetry has 2 through holes; Push rod 2 is to be processed into three sections with whole cylinder; The top is a knurling handle, and the centre is a screw thread, and the other end is a concentric column.
Advantage of the present invention is:
Because the design of guided missile launcher venting instrument is small and exquisite; Long venting instrument is realized and the docking of deflating valve more easily before when being connected with the missile launcher deflating valve, comparing; Especially under cold snap, reduced work difficulty; This device simplicity of design is practical simultaneously, and it is a plurality of to realize that a machine is equipped with, and in the venting work simultaneously of many hangers, has shortened the time of venting work greatly.
Description of drawings
Fig. 1 is the structural representation of guided missile launcher venting instrument
The 1-connector, 2-push rod, 3-air vent.
Fig. 2 is the profile of cutting open from longitudinal axis.
The specific embodiment
Guided missile launcher venting instrument comprises connector 1 and threaded push rod 2, and connector 1 and push rod 2 are linked together by silking; 2 air vents 3 are arranged on the connector 1; Connector 1 is the with one heart positive hexahedron that on the annular knurl cylinder of the high 15mm of diameter 30mm, meets the high 11mm of diameter 17mm, and cylinder and hexahedron are an integral body, have in the hexahedron diameter be M8 etc. high concentric threads hole; It is the concentric threads hole of M12mm that diameter is arranged in the cylinder; The through hole that it is 3mm that cylinder upper end symmetry has 2 diameters is an air vent, and push rod 2 is that the cylinder with the whole high 37mm of diameter 15mm is processed into three sections, the knurling handle of the high 10mm of top end diameter 15mm; The centre is the concentric M8 screw thread of long 25mm, the concentric column of the high 5mm of other end diameter 5mm.It is characterized in that connector 1 and push rod 2 are linked together by silking; 2 air vents are arranged on the connector 1; Connector 1 docks with the missile launcher deflating valve through silking; Rotation push rod 2 is a little with the valve jacking in the missile launcher deflating valve, and gas can release from 2 air vents on the connector 1.
Guided missile launcher venting instrument is made up of connector 1 and push rod 2, the silking of the silking in connector 1 column part and missile launcher deflating valve is aligned, because lightly conveniently adjusting in the process that aligns of connector; Comparing original venting instrument docking time shortens; The body that is rotatably connected after aligning is stuck on the hexahedron of connector fasteningly with spanner, accomplish being connected of connector and missile launcher deflating valve; Rotate the knurling handle of push rod 2 then; With push rod 2 rotation direction deflating valves, because there is the annular knurl need just can the jacking of deflating valve valve is not a little with hand by instrument on the handle, high nitrogen discharges after 2 air vents on the connector release in valve.

Claims (2)

1. guided missile launcher venting instrument is characterized in that this instrument comprises connector (1) and threaded push rod (2); Connector (1) is linked together by silking with push rod (2), and it is to connect with one heart positive hexahedron on the annular knurl cylinder to form that 2 air vents (3), connector (1) are arranged on the connector (1); The two integral body processes, and high concentric threads hole is arranged in the hexahedron etc., and the concentric threads hole is arranged in the cylinder; It is air vent (3) that cylinder upper end symmetry has 2 through holes, and push rod (2) is to be processed into three sections with whole cylinder, and the top is a knurling handle; The centre is a screw thread, and the other end is a concentric column.
2. guided missile launcher venting instrument as claimed in claim 1; It is characterized in that; Described connector (1) is the with one heart positive hexahedron that on the annular knurl cylinder of the high 15mm of diameter 30mm, meets the high 11mm of diameter 17mm; Have in the hexahedron diameter be M8 etc. high concentric threads hole, it is the concentric threads hole of M12mm that diameter is arranged in the cylinder, the through hole that it is 3mm that cylinder upper end symmetry has 2 diameters is air vent (3); Described push rod (2) is that the cylinder with the whole high 37mm of diameter 15mm is processed into three sections, the knurling handle of the high 10mm of top end diameter 15mm, and the centre is the concentric M8 screw thread of long 25mm, the concentric column of the high 5mm of other end diameter 5mm.
CN 201120449035 2011-11-11 2011-11-11 Deflating tool of missile launcher Expired - Fee Related CN202485556U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 201120449035 CN202485556U (en) 2011-11-11 2011-11-11 Deflating tool of missile launcher

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN 201120449035 CN202485556U (en) 2011-11-11 2011-11-11 Deflating tool of missile launcher

Publications (1)

Publication Number Publication Date
CN202485556U true CN202485556U (en) 2012-10-10

Family

ID=46959973

Family Applications (1)

Application Number Title Priority Date Filing Date
CN 201120449035 Expired - Fee Related CN202485556U (en) 2011-11-11 2011-11-11 Deflating tool of missile launcher

Country Status (1)

Country Link
CN (1) CN202485556U (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103032508A (en) * 2012-12-11 2013-04-10 江西洪都航空工业集团有限责任公司 Decompression device of undercarriage bumper

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103032508A (en) * 2012-12-11 2013-04-10 江西洪都航空工业集团有限责任公司 Decompression device of undercarriage bumper

Similar Documents

Publication Publication Date Title
CN202485556U (en) Deflating tool of missile launcher
CN204209602U (en) Rotatable pipe wrench
CN202684829U (en) One-way valve dismounting device
CN208603508U (en) A kind of ARTMechanical gas pressure axis for papermaking and printing packaging retractable volume system rises axis
CN204366903U (en) Pipeline adpting flange bolt disassembly instrument
CN204300069U (en) A kind of connecting pin
CN104999257A (en) Assembly device and assembly method of hose component metal thread connecting piece
CN203210024U (en) Clamping device of thin-wall cylinder workpieces
CN202943570U (en) Improved valve triangle wrench
CN204692024U (en) Two-stage pressurizing device
CN204450343U (en) Adjustable wrench operating head
CN205817759U (en) A kind of integrated household spanner
CN201848800U (en) Fast unscrewing and screwing wrench
CN110762098A (en) Expansion bolt with clamping block
CN204585087U (en) A kind of helical screw rotary spanner
CN209229114U (en) Valve opening/closing device
CN209648557U (en) A kind of practical sleeve
CN202862106U (en) Pipe wrench handle extender
CN204575360U (en) Tire cutter handle
CN203696855U (en) Special wrench for packing pressing cap of internal lead screw of protective sleeve
CN209380675U (en) Slide block type double cam SF6 valve body universal fixture
CN201973229U (en) Bulb type piston rod
CN204277880U (en) The adjustable composite type wrench of Plane Angle
CN104416515A (en) Screwdriver
CN104552100A (en) Hand-cranked tire disassembly and assembly device

Legal Events

Date Code Title Description
C14 Grant of patent or utility model
GR01 Patent grant
CF01 Termination of patent right due to non-payment of annual fee
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20121010

Termination date: 20181111