CN109696088A - Close-coupled missile wing companding mechanism and guided missile - Google Patents
Close-coupled missile wing companding mechanism and guided missile Download PDFInfo
- Publication number
- CN109696088A CN109696088A CN201811496609.7A CN201811496609A CN109696088A CN 109696088 A CN109696088 A CN 109696088A CN 201811496609 A CN201811496609 A CN 201811496609A CN 109696088 A CN109696088 A CN 109696088A
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- Prior art keywords
- missile wing
- missile
- wing
- coupled
- close
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
Abstract
The present invention provides a kind of close-coupled missile wing companding mechanism and guided missiles, can increase tactical missile scope, extend battle sky, increase permissible load factor, improve maneuverability, save exterior space, bury carry convenient for interior.The invention discloses close-coupled missile wing companding mechanism, main features are as follows: the composition such as telescopic wing, connecting rod, piston sleeve, piston rod, axis, bracket, spring, push-plate, exploder, locking pin, block.It can be realized under the conditions of opening up limited to size using close-coupled missile wing companding mechanism and combine the different requirements for meeting ejection launch safety and end high maneuver.
Description
Technical field
The present invention relates to guided missile general technical fields, and in particular, to close-coupled missile wing companding mechanism.Especially a kind of intelligence
It can aircraft close-coupled missile wing companding mechanism.
Background technique
Increasingly complicated battlefield surroundings propose increasingly higher demands to the operational performance of tactical missile, force its flight
Envelope curve further expansion, New technical use continue to bring out.To increase anti-missile missile range, battle sky is extended, increase can be used
It carries, improves maneuverability, save exterior space, bury carry convenient for interior.There are no guided missiles using flexible wing mechanism in the prior art.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of close-coupled missile wing companding mechanisms.
A kind of close-coupled missile wing companding mechanism provided according to the present invention, comprising: missile wing, bracket, shaft member, exploder；
The missile wing rotation axis of missile wing is rack-mount, and missile wing passes through piston rod, piston sleeve, connecting rod, push-plate connection peace
In the consistent shaft member of elastomer axis；
When missile wing contraction state, push-plate is fixed on the initial position of axis by exploder.
Preferably, when exploder receives missile-borne computer expansion instruction, exploder work pin retraction exploder ontology
Interior, push-plate moves under spring impetus along axis, pushes connecting rod, so that piston sleeve opening angle becomes larger, pushing piston-rod
To push missile wing to screw out body around bracket；Missile wing expands in place, and missile wing missile wing inner edge is adjacent to the completion of the link stopper inside groove on bracket
The latch pin for sealing, and being pressurized, which enters in missile wing, fixes missile wing in marginal pore, and connects in bullet after locking pin stretching
Circuit provides the feedback signal that missile wing expands in place.
A kind of guided missile provided according to the present invention, using above-mentioned close-coupled missile wing companding mechanism.
Compared with prior art, the present invention have it is following the utility model has the advantages that
The present invention can be realized under the conditions of opening up limited to size using close-coupled missile wing companding mechanism and be combined completely
Sufficient ejection launch safety and the different of end high maneuver require.The present invention can increase scope, extend battle sky,
Increase permissible load factor, improve maneuverability, saves exterior space, bury carry convenient for interior.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is a kind of guided missile close-coupled missile wing companding structural scheme of mechanism of the present invention.
It is shown in figure:
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
As shown in Figure 1, being a kind of structural schematic diagram of the close-coupled missile wing companding mechanism of guided missile of the present invention, missile wing in Fig. 1
Rotation axis is fixed by the bracket in cabin, and missile wing is fastened on elastomer axis by piston rod, piston sleeve, connecting rod and push-plate
On consistent axis, when missile wing contraction state, push-plate is fixed on the initial position of axis by exploder.It is calculated on bullet when exploder receives
When machine expansion instruction, exploder works in pin retraction exploder ontology, and push-plate moves under spring impetus along axis, pushes
Connecting rod, so that piston sleeve opening angle becomes larger, pushing piston-rod is to push missile wing to screw out body around bracket.Missile wing is deployed into
Position, missile wing missile wing inner edge is adjacent to link stopper inside groove and completes sealing, and the latch pin being pressurized enters missile wing in missile wing in marginal pore
It is fixed, and circuit in bullet is connected after locking pin stretching, provide the feedback signal that missile wing expands in place.
Before not receiving missile-borne computer expansion instruction, missile wing is entirely retracted to body for the close-coupled missile wing companding mechanism
Inside, after receiving missile-borne computer expansion instruction, rapid deployment missile wing, and complete missile wing locking and sealing function, mechanism
It is formed including telescopic wing, connecting rod, piston sleeve, piston rod, axis, bracket, spring, push-plate, exploder, locking pin, block etc..
In order to achieve the above object of the invention, the technical scheme adopted by the invention is that before not receiving missile-borne computer expansion instruction,
Telescopic wing is connected to push-plate by connecting rod, piston sleeve, piston rod and is placed on the axis for being fixed on elastomer axis, and push-plate passes through
Priming system is fixed to guarantee that missile wing does not receive missile-borne computer instruction moment missile wing again and is entirely retracted to body.When exploder receives aerofoil
After expansion instruction, pin is unlocked, push-plate fast and safely expands in place under the action of the spring, by telescopic wing, and telescopic wing is fully deployed
After in place, missile wing inner edge is adjacent to link stopper inside groove, and rear latch pin enters in missile wing in marginal pore in place, completes locking function.
And missile wing inner edge is adjacent to the sealing performance requirement that link stopper inside groove completes missile wing.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (3)
1. a kind of close-coupled missile wing companding mechanism characterized by comprising missile wing, bracket, shaft member, exploder；
The missile wing rotation axis of missile wing is rack-mount, and missile wing is mounted on by piston rod, piston sleeve, connecting rod, push-plate connection
In the consistent shaft member of elastomer axis；
When missile wing contraction state, push-plate is fixed on the initial position of axis by exploder.
2. close-coupled missile wing companding mechanism according to claim 1, which is characterized in that when exploder receives missile-borne computer
When expansion instruction, exploder works in pin retraction exploder ontology, and push-plate moves under spring impetus along axis, the company of promotion
Bar, so that piston sleeve opening angle becomes larger, pushing piston-rod is to push missile wing to screw out body around bracket；Missile wing is deployed into
Position, missile wing missile wing inner edge is adjacent to the link stopper inside groove on bracket and completes sealing, and the latch pin being pressurized enters marginal pore in missile wing
It is interior to fix missile wing, and circuit in bullet is connected after locking pin stretching, provide the feedback signal that missile wing expands in place.
3. a kind of guided missile, which is characterized in that use close-coupled missile wing companding mechanism of any of claims 1 or 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811496609.7A CN109696088B (en) | 2018-12-07 | 2018-12-07 | Compact missile wing contraction and expansion mechanism and missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811496609.7A CN109696088B (en) | 2018-12-07 | 2018-12-07 | Compact missile wing contraction and expansion mechanism and missile |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109696088A true CN109696088A (en) | 2019-04-30 |
| CN109696088B CN109696088B (en) | 2021-06-08 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811496609.7A Active CN109696088B (en) | 2018-12-07 | 2018-12-07 | Compact missile wing contraction and expansion mechanism and missile |
Country Status (1)
| Country | Link |
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| CN (1) | CN109696088B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110567327A (en) * | 2019-08-08 | 2019-12-13 | 四川航天川南火工技术有限公司 | Circumferential unlocking structure of gas piston |
| CN112572758A (en) * | 2020-12-18 | 2021-03-30 | 上海机电工程研究所 | Dynamic sealing mechanism between telescopic wing and aircraft cabin |
| CN113682460A (en) * | 2021-09-09 | 2021-11-23 | 北京航空航天大学 | Deformable missile wing and flight device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110567327A (en) * | 2019-08-08 | 2019-12-13 | 四川航天川南火工技术有限公司 | Circumferential unlocking structure of gas piston |
| CN112572758A (en) * | 2020-12-18 | 2021-03-30 | 上海机电工程研究所 | Dynamic sealing mechanism between telescopic wing and aircraft cabin |
| CN113682460A (en) * | 2021-09-09 | 2021-11-23 | 北京航空航天大学 | Deformable missile wing and flight device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109696088B (en) | 2021-06-08 |
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