CN206469771U - A kind of double mode emitter of airborne missile - Google Patents
A kind of double mode emitter of airborne missile Download PDFInfo
- Publication number
- CN206469771U CN206469771U CN201720119589.6U CN201720119589U CN206469771U CN 206469771 U CN206469771 U CN 206469771U CN 201720119589 U CN201720119589 U CN 201720119589U CN 206469771 U CN206469771 U CN 206469771U
- Authority
- CN
- China
- Prior art keywords
- guide rail
- missile
- guide rails
- rib
- body ejection
- 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.)
- Withdrawn - After Issue
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Abstract
A kind of double mode emitter of airborne missile, its housing is connected on guided-weapon ship, some ribs are packed in case inside, two guide rails fixing supports be arrangeding in parallel are connected on rib, guide rails fixing support is provided with guide rail fixing port, two guide rails are located in the guide rail fixing port of two guide rails fixing supports respectively, and sliding block is mounted on two guide rails, and sliding block lower end is fixedly connected with missile airframe；Cartridge combustion chamber is packed on rib, the high pressure spray gas port of cartridge burner ends is respectively connected with body ejection airway tube, body ejection piston cylinder is set perpendicular to missile airframe, body ejection piston cylinder upper end nozzle is connected with body ejection airway tube, body ejection push rod is located in body ejection piston cylinder cylinder, body launches push rod has the axial stretching free degree relative to body ejection piston cylinder, and being connected with guide rail slide block between guide rail and cartridge combustion chamber separates drive mechanism；Buffer is added between two guide rails；Blocking mechanism is installed between rib and missile airframe.
Description
Technical field
The utility model belongs to airborne missile lift-off technology field, more particularly to a kind of double mode transmitting dress of airborne missile
Put.
Background technology
For modern war, denial of the air turns into the key factor for determining war trend, for denial of the air,
Opportunity of combat needs the substantial amounts of guided missile of carry, and the mount point of guided missile can be located under fuselage, under wing, at wing tip or in ventral, root
According to the difference of guided missile model, the radiation pattern of guided missile is also divided into guide tracked transmitting and ejection type transmitting.
Guide tracked transmitting is also known as from thrust transmitting, and guided missile provides thrust by the engine or boost motor of itself, makes to lead
Bullet departs from the guide rail of emitter.Guided missile depart from emitter before taxiing procedures in, can by guide rail constraint and guiding,
Its initial flight direction is can determine and controlled when guided missile leaves the right or normal track, and can be quickly through interference range, initial disturbance is smaller.At present,
Most of light-duty and medium-sized air-to-air missile generally uses guide tracked radiation pattern.
Ejection type transmitting is to be shot out Missile Body using outer power, waits guided missile to leave after the segment distance of opportunity of combat one, guided missile hair
Motivation is just lighted a fire, along Longitudinal Flight under guided missile itself thrust.At present, most of medium-sized or above air-to-air missiles, vacant lot
Guided missile generally uses ejection type radiation pattern.When guided missile is launched using ejection type, guided missile can be with carry in airplane aerodynamic
With interference flowing field on more serious mount point, " can also partly bury " or " burying entirely " mount point in fuselage or in internal weapon bays on.
Although the characteristics of guide tracked radiation pattern and ejection type radiation pattern are owned by respective and advantage, the two is corresponding
Emitter is all that single-mode, i.e. finite-length launcher can only adapt to the guided missile using guide tracked transmitting, and is launched
Formula emitter can only adapt to the guided missile launched using ejection type, when the guided missile model of a certain mount point needs to change, also
Need to be changed corresponding emitter, it is difficult further raising to cause to shoot efficiency, and the general operation effectiveness of opportunity of combat
Also it can be affected.
Therefore, in order to improve the general operation effectiveness of opportunity of combat, it is necessary to shoot efficiency from raising and start with, if it is possible to save hair
The Renewal process of injection device, can necessarily shorten charging time, thus it is imperative to design a kind of double mode emitter.
Utility model content
The problem of existing for prior art, the utility model provides a kind of double mode emitter of airborne missile, can
The guided missile of guide tracked and ejection type transmitting is adapted to simultaneously, without changing emitter again when ground crew changes guided missile every time,
Effectively shorten charging time, and effectively increase and shoot efficiency and opportunity of combat general operation effectiveness.
To achieve these goals, the utility model is adopted the following technical scheme that：A kind of double mode transmitting dress of airborne missile
Put, including housing, rib, guide rail, guide rails fixing support, sliding block, cartridge combustion chamber, body ejection airway tube, body ejection work
Plug tube, body ejection push rod and guide rail slide block separation drive mechanism；
The housing is connected on guided-weapon ship, and the rib quantity is some, and some ribs are packed in case inside, described
Guide rails fixing support is provided with two, and two guide rails fixing supports be arranged in parallel；Two guide rails fixing supports are connected on rib,
Guide rail fixing port is offered on two guide rails fixing supports, one is each provided with the guide rail fixing port of two guide rails fixing supports
Guide rail, and two guide rails are parallel；Chute at two is arranged with the upper end of slide block, sliding block is mounted on two by chute and led
On rail, sliding block lower end is fixedly connected with missile airframe；
The cartridge combustion chamber is packed on rib, and the high pressure spray gas port of cartridge burner ends is respectively connected with bullet
Body launches airway tube；The body ejection piston cylinder is set perpendicular to missile airframe, body ejection piston cylinder upper end nozzle and bullet
Body ejection airway tube is connected, and the body ejection push rod is located in body ejection piston cylinder cylinder, and body ejection push rod is relative
There is the axial stretching free degree in body ejection piston cylinder；The guide rail slide block separation drive mechanism is connected to guide rail and cartridge
Between combustion chamber.
The guide rail slide block separation drive mechanism includes cylinder barrel, piston, drive connecting rod, symmetrical expression crank, the first driven company
Bar and the second follower link；The cylinder barrel is set perpendicular to missile airframe, cylinder barrel upper end and the high pressure in the middle part of cartridge combustion chamber
Puff prot is connected, and the piston is located in cylinder barrel cylinder, and piston lower surface is hinged with drive connecting rod one end；The symmetrical expression
Crank is located at cylinder barrel obliquely downward, and symmetrical expression crank center is provided with a rotating shaft, and symmetrical expression crank has relative to rotating shaft to be turned
The dynamic free degree, rotating shaft is fixed relative to rib and guide rails fixing support position；Described first follower link one end is hinged on one and led
On rail, the first follower link other end is hinged on symmetrical expression crank one end；Described second follower link one end is hinged on another
On guide rail, the second follower link other end is hinged on the symmetrical expression crank other end；The drive connecting rod other end is bent with symmetrical expression
Handle one end is hinged.
Buffer is added between two guide rails, the cushioned resistance of buffer is more than missile airframe in non-emissive shape
Inertial impact force when state or guide tracked reflection, and the cushioned resistance of buffer is less than missile airframe leading when ejection type is launched
Rail sliding block separates driving force.
Blocking mechanism is installed between the rib and missile airframe, blocking mechanism include latched lever, gear bounding against the bar bar,
Block, buffer spring, locking tension spring and pedestal；The block is packed on missile airframe, and the pedestal is packed in rib
On, the gear bounding against the bar bar upper end is connected by buffer spring with pedestal, and gear bounding against the bar bar lower end is resisted against block trailing flank；It is described to close
Lever upper end is locked by hinge on gear bounding against the bar bar top, latched lever lower end is resisted against block leading flank, the locking is drawn
Power spring is connected between latched lever and gear bounding against the bar bar, and block is clamped between latched lever and gear bounding against the bar bar.
Be connected between the missile airframe and guided-weapon ship by cable, by cable carry out electric signal transmission, cable with
It is connected between missile airframe by quick tension fracture type joint, lifting spring is added between cable and rib.
The beneficial effects of the utility model：
The utility model compared with prior art, the guided missile of guide tracked and ejection type transmitting, ground service can be adapted to simultaneously
Without changing emitter again when personnel change guided missile every time, effectively shorten charging time, and effectively increase shoot efficiency and
Opportunity of combat general operation effectiveness.
Brief description of the drawings
Fig. 1 is a kind of double mode emitter of airborne missile (housing is not drawn into) structural representation of the present utility model；
Fig. 2 is that the double mode emitter of airborne missile of the present utility model is equipped with schematic diagram with missile airframe；
Fig. 3 is the structural representation that guide rail slide block of the present utility model separates drive mechanism；
Fig. 4 is rib of the present utility model and guide rails fixing support structural representation；
Fig. 5 is blocking mechanism structural representation of the present utility model；
In figure, 1-housing, 2-rib, 3-guide rail, 4-guide rails fixing support, 5-sliding block, 6-cartridge combustion chamber,
7-body launches airway tube, 8-body ejection piston cylinder, 9-body ejection push rod, 10-guide rail fixing port, 11-Missile Body
Body, 12-cylinder barrel, 13-piston, 14-drive connecting rod, 15-symmetrical expression crank, the 16-the first follower link, 17-the second from
Dynamic connecting rod, 18-rotating shaft, 19-buffer, 20-latched lever, 21-gear bounding against the bar bar, 22-block, 23-buffer spring,
24-locking tension spring, 25-pedestal, 26-bearing pin, 27-cable, 28-quick tension fracture type joint.
Embodiment
The utility model is described in further detail with specific embodiment below in conjunction with the accompanying drawings.
As shown in Fig. 1~5, a kind of double mode emitter of airborne missile, including housing 1, rib 2, guide rail 3, guide rail are solid
Determine frame 4, sliding block 5, cartridge combustion chamber 6, body ejection airway tube 7, body ejection piston cylinder 8, body ejection push rod 9 and guide rail
Sliding block separates drive mechanism；
The housing 1 is connected on guided-weapon ship, and the quantity of rib 2 is some, and some ribs 2 are packed in the inner side of housing 1,
The guide rails fixing support 4 is provided with two, and two guide rails fixing supports 4 be arranged in parallel；Two guide rails fixing supports 4 are connected in muscle
On rib 2, guide rail fixing port 10 is offered on two guide rails fixing supports 4, in the guide rail fixing port 10 of two guide rails fixing supports 4
A guide rail 3 is inside each provided with, and two guide rails 3 are parallel；Chute at two is arranged with the upper end of sliding block 5, sliding block 5 leads to
Cross chute to be mounted on two guide rails 3, the lower end of sliding block 5 is fixedly connected with missile airframe 11；
The cartridge combustion chamber 6 is packed on rib 2, and the high pressure spray gas port at the two ends of cartridge combustion chamber 6 is each connected
There is body to launch airway tube 7；The body ejection piston cylinder 8 is set perpendicular to missile airframe 11,8 upper ends of body ejection piston cylinder
Nozzle is connected with body ejection airway tube 7, and the body ejection push rod 9 is located in body ejection piston 8 cylinders of cylinder, body bullet
Penetrate push rod 9 has the axial stretching free degree relative to body ejection piston cylinder 8；The guide rail slide block separation drive mechanism is connected to
Between guide rail 3 and cartridge combustion chamber 6.
Guide rail slide block separation drive mechanism includes cylinder barrel 12, piston 13, drive connecting rod 14, symmetrical expression crank 15, the
One follower link 16 and the second follower link 17；The cylinder barrel 12 is set perpendicular to missile airframe 11, and the upper end of cylinder barrel 12 is put with throwing
The high pressure spray gas port for playing the middle part of combustion chamber 6 is connected, and the piston 13 is located in the cylinder of cylinder barrel 12, the lower surface of piston 13 and active
The one end of connecting rod 14 is hinged；The symmetrical expression crank 15 is located at the obliquely downward of cylinder barrel 12, and one is provided centrally with symmetrical expression crank 15
Root rotating shaft 18, symmetrical expression crank 15 has rotational freedom relative to rotating shaft 18, and rotating shaft 18 is relative to rib 2 and guide rails fixing support
4 positions are fixed；Described one end of first follower link 16 is hinged on a guide rail 3, and the other end of the first follower link 16 is hinged on
The one end of symmetrical expression crank 15；Described one end of second follower link 17 is hinged on another guide rail 3, and the second follower link 17 is another
End is hinged on the other end of symmetrical expression crank 15；The other end of drive connecting rod 14 is hinged with the one end of symmetrical expression crank 15.
Buffer 19 is added between two guide rails 3, the cushioned resistance of buffer 19 exists more than missile airframe 11
Inertial impact force when non-emitting states or guide tracked reflection, and the cushioned resistance of buffer 19 is less than missile airframe 11 in ejection
Guide rail separation driving force when formula is launched.
Blocking mechanism is installed between the rib 2 and missile airframe 11, blocking mechanism includes latched lever 20, gear bullet
Lever 21, block 22, buffer spring 23, locking tension spring 24 and pedestal 25；The block 22 is packed on missile airframe 11,
The pedestal 25 is packed on rib 2, and the upper end of gear bounding against the bar bar 21 is connected by buffer spring 23 with pedestal 25, keeps off bounding against the bar bar
21 lower ends are resisted against the trailing flank of block 22；The upper end of latched lever 20 is hinged on the top of gear bounding against the bar bar 21 by bearing pin 26, closes
Lock lever 20 lower end is resisted against the leading flank of block 22, and the locking tension spring 24 is connected to latched lever 20 and gear bounding against the bar bar 21
Between, block 22 is clamped between latched lever 20 and gear bounding against the bar bar 21.
It is connected between the missile airframe 11 and guided-weapon ship by cable 27, electric signal transmission is carried out by cable 27,
It is connected between cable 27 and missile airframe 11 by quick tension fracture type joint 28, lifting bullet is added between cable 27 and rib 2
Spring.
Illustrate first use process of the present utility model below in conjunction with the accompanying drawings：
When missile airframe 11 carries out guide tracked transmitting, missile airframe 11 is provided by the engine or boost motor of itself and pushed away
Power.
When thrust generation before, missile airframe 11 still in blocking mechanism locking-in state, when thrust is produced, missile airframe
Unblock is realized in 11 stops that block 22 can be driven to shake off latched lever 20；After unblock and before missile airframe 11 departs from guide rail 3,
Sliding block 5 on missile airframe 11 will be slided along guide rail 3, the constraint and guiding of missile airframe 11 be realized, with missile airframe 11
Slide on guides 3, cable 27 will be tightened constantly, until quick tension fracture type joint 28 disconnects, under lifting spring effect, quickly
Tension fracture type joint 28 will quickly be raised with cable 27 and away from body surface, until missile airframe 11 smoothly departs from guide rail 3.
When missile airframe 11 carries out ejection type transmitting, cartridge combustion chamber 6 starts, and its gases at high pressure produced passes through bullet
Body ejection airway tube 7 enters in body ejection piston cylinder 8, and drives body ejection push rod 9 to eject at a high speed；Meanwhile, cartridge combustion
Burning the gases at high pressure of the generation of room 6 will also enter in the cylinder barrel 12 of guide rail slide block separation drive mechanism, and drive under the high speed of piston 13
Move, drive drive connecting rod 14 to move, and then drive symmetrical expression crank 15 18 to rotate around the shaft, pass through the rotation of symmetrical expression crank 15
The high-speed synchronous retraction of the first follower link 16 and the second follower link 17 is realized, and then by the synchronous opposite pulling of two guide rails 3,
Until sliding block 5 departs from from guide rail 3；In the case where the body ejection push rod 9 of high speed ejection is acted on, missile airframe 11 is gone out by ejection,
Quick tension fracture type joint 28 will quickly disconnect in ejection process, wait missile airframe 11 to leave after the segment distance of carrier aircraft one, guided missile starts
Machine is lighted a fire.
Scheme in embodiment simultaneously is not used to limit scope of patent protection of the present utility model, all without departing from the utility model
Carried out by equivalence enforcement or change, be both contained in the scope of the claims of this case.
Claims (5)
1. a kind of double mode emitter of airborne missile, it is characterised in that：Including housing, rib, guide rail, guide rails fixing support, cunning
Block, cartridge combustion chamber, body ejection airway tube, body ejection piston cylinder, body ejection push rod and guide rail slide block separation driving
Mechanism；
The housing is connected on guided-weapon ship, and the rib quantity is some, and some ribs are packed in case inside, the guide rail
Fixed mount setting has two, and two guide rails fixing supports be arranged in parallel；Two guide rails fixing supports are connected on rib, at two
Guide rail fixing port is offered on guide rails fixing support, being each provided with one in the guide rail fixing port of two guide rails fixing supports leads
Rail, and two guide rails are parallel；Chute at two is arranged with the upper end of slide block, sliding block is mounted on two guide rails by chute
On, sliding block lower end is fixedly connected with missile airframe；
The cartridge combustion chamber is packed on rib, and the high pressure spray gas port of cartridge burner ends is respectively connected with body bullet
Penetrate airway tube；The body ejection piston cylinder is set perpendicular to missile airframe, body ejection piston cylinder upper end nozzle and body bullet
Penetrate airway tube to be connected, the body ejection push rod is located in body ejection piston cylinder cylinder, and body launches push rod relative to bullet
Body ejection piston cylinder has the axial stretching free degree；The guide rail slide block separation drive mechanism is connected to guide rail and burnt with cartridge
Between room.
2. the double mode emitter of a kind of airborne missile according to claim 1, it is characterised in that：The guide rail slide block point
Include cylinder barrel, piston, drive connecting rod, symmetrical expression crank, the first follower link and the second follower link from drive mechanism；The cylinder
Cylinder is set perpendicular to missile airframe, and cylinder barrel upper end is connected with the high pressure spray gas port in the middle part of cartridge combustion chamber, the piston position
In in cylinder barrel cylinder, piston lower surface is hinged with drive connecting rod one end；The symmetrical expression crank is located at cylinder barrel obliquely downward, right
Title formula crank center is provided with a rotating shaft, and symmetrical expression crank has rotational freedom relative to rotating shaft, and rotating shaft is relative to rib
And guide rails fixing support position is fixed；Described first follower link one end is hinged on a guide rail, the first follower link other end
It is hinged on symmetrical expression crank one end；Described second follower link one end is hinged on another guide rail, and the second follower link is another
End is hinged on the symmetrical expression crank other end；The drive connecting rod other end is hinged with symmetrical expression crank one end.
3. the double mode emitter of a kind of airborne missile according to claim 1, it is characterised in that：In two guide rails
Between add buffer, the cushioned resistance of buffer is more than inertia of the missile airframe in non-emitting states or guide tracked reflection
Impulsive force, and the cushioned resistance of buffer is less than guide rail slide block separation driving force of the missile airframe when ejection type is launched.
4. the double mode emitter of a kind of airborne missile according to claim 1, it is characterised in that：In the rib with leading
Blocking mechanism is installed, blocking mechanism includes latched lever, gear bounding against the bar bar, block, buffer spring, locking pulling force between bullet body
Spring and pedestal；The block is packed on missile airframe, and the pedestal is packed on rib, and the gear bounding against the bar bar upper end passes through
Buffer spring is connected with pedestal, and gear bounding against the bar bar lower end is resisted against block trailing flank；The latched lever upper end passes through hinge
On gear bounding against the bar bar top, latched lever lower end is resisted against block leading flank, the locking tension spring be connected to latched lever with
Keep off between bounding against the bar bar, block is clamped between latched lever and gear bounding against the bar bar.
5. the double mode emitter of a kind of airborne missile according to claim 1, it is characterised in that：The missile airframe with
It is connected between guided-weapon ship by cable, electric signal transmission is carried out by cable, by quickly drawing between cable and missile airframe
Disconnected formula joint is connected, and lifting spring is added between cable and rib.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720119589.6U CN206469771U (en) | 2017-02-09 | 2017-02-09 | A kind of double mode emitter of airborne missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720119589.6U CN206469771U (en) | 2017-02-09 | 2017-02-09 | A kind of double mode emitter of airborne missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206469771U true CN206469771U (en) | 2017-09-05 |
Family
ID=59704014
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720119589.6U Withdrawn - After Issue CN206469771U (en) | 2017-02-09 | 2017-02-09 | A kind of double mode emitter of airborne missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206469771U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106643294A (en) * | 2017-02-09 | 2017-05-10 | 沈阳航空航天大学 | Dual-mode launcher for airborne missile |
-
2017
- 2017-02-09 CN CN201720119589.6U patent/CN206469771U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106643294A (en) * | 2017-02-09 | 2017-05-10 | 沈阳航空航天大学 | Dual-mode launcher for airborne missile |
| CN106643294B (en) * | 2017-02-09 | 2018-01-16 | 沈阳航空航天大学 | A kind of airborne missile double mode emitter |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170905 Effective date of abandoning: 20180116 |