CN204064129U - Anti-ballistic attack guided missile - Google Patents
Anti-ballistic attack guided missile Download PDFInfo
- Publication number
- CN204064129U CN204064129U CN201420312196.3U CN201420312196U CN204064129U CN 204064129 U CN204064129 U CN 204064129U CN 201420312196 U CN201420312196 U CN 201420312196U CN 204064129 U CN204064129 U CN 204064129U
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- CN
- China
- Prior art keywords
- bullet
- guided missile
- female
- missile
- tail end
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- 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
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Abstract
A kind of anti-ballistic attack guided missile, is made up of female bullet (1), bullet (2) and micro-unmanned reconnaissance plane (3); The bullet inner top of described female bullet (1) is equipped with micro-unmanned reconnaissance plane (3), and the bullet of female bullet (1) circumferentially uniform bullet trajectory outlet (5); Bullet (2) and master control system (4) are equipped with in the body top of described female bullet (1), and main propellant (6) is equipped with in bottom, and tail end is equipped with sustainer (7); The top of described bullet (2) has warhead (8), secondary control system (9) is housed, and two secondary propellants (10) are equipped with at middle part, and tail end is equipped with secondary engine (11).The utility model first scouts rear attack, can be intended to by concealed attack, and accurately can obtain the information of enemy's guided missile or target, effectively hit enemy's guided missile or target.Particularly can solve existing anti-missile system and be unable to cope with the problem that saturation type hits or many ripples hit.
Description
Technical field
The utility model belongs to missilery field, is specifically related to a kind of anti-ballistic attack guided missile.
Technical background
Missile defense systems should be able to Timeliness coverage and correctly identify target, make decisions to target precision tracking, rapidly and effectively tackle.Usually first found by missile early warning system and correctly identify target, command and control system makes decisions rapidly, and commander launches antiballistic missile, then by guidance system smart missiles interception target exactly.But the interception guided missile quantity that system of defense processes multiobject ability and equipment is all limited simultaneously, when have multiple attack target enter a system of defense simultaneously time, system is easily saturated.Visible existing anti-missile system is unable to cope with saturation type and hits or time strike of many ripples.
Summary of the invention
The technical problem that the utility model solves: a kind of anti-ballistic attack guided missile of design, first scouts and attacks afterwards, can be intended to by concealed attack, and accurately can obtain the information of enemy's guided missile or target, effectively hit enemy's guided missile or target.Particularly can solve existing anti-missile system and be unable to cope with the problem that saturation type hits or many ripples hit.
The technical solution adopted in the utility model: a kind of anti-ballistic attack guided missile, described guided missile is made up of female bullet, bullet and micro-unmanned reconnaissance plane; The bullet inner top of described female bullet is equipped with micro-unmanned reconnaissance plane, and the circumferentially uniform bullet trajectory outlet of the bullet of female bullet; Bullet and master control system are equipped with in the body top of described female bullet, and main propellant is equipped with in bottom, and tail end is equipped with sustainer; The top of described bullet has warhead, secondary control system is housed, and two secondary propellants are equipped with at middle part, and tail end is equipped with secondary engine.
The bullet inner top of described female bullet is at least equipped with the micro-unmanned reconnaissance plane of three framves, and circumferentially at least uniform three bullet trajectory outlet of the bullet of female bullet; Three pieces of bullets are at least equipped with on the body top of described female bullet.
The tail end of described female bullet is equipped with three sustainers, and the tail end of described bullet is equipped with a secondary engine.
The utility model compared with prior art can realize following beneficial effect:
1, first scout after once launching and attack afterwards, can be intended to by concealed attack, and accurately can obtain the information of enemy's guided missile or target, effectively hit enemy's guided missile or target.
2, an arrow multiple warhead can carry out interception destruction to multiple target, solves existing anti-missile system and is unable to cope with the problem that saturation type hits or many ripples hit.
3, after small-sized daughter missile Secondary Emission, after speed superposition, flight is faster, effectively hits interdiction capability and is increased dramatically.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Detailed description of the invention
1 a kind of embodiment of the present utility model is described by reference to the accompanying drawings.
A kind of anti-ballistic attack guided missile, is made up of female bullet 1, bullet 2 and micro-unmanned reconnaissance plane 3; Described female bullet 1 bullet inner top is equipped with the micro-unmanned reconnaissance plane 3 of three framves, and circumferentially uniform three bullet trajectory outlet 5 of female bullet 1 bullet; Three pieces of bullets 2 and master control system 4 are equipped with in the body top of described female bullet 1, and main propellant 6 is equipped with in bottom, and tail end is equipped with three sustainers 7; The top of described bullet 2 has warhead 8, secondary control system 9 is housed, and two secondary propellants 10 are equipped with at middle part, and tail end is equipped with a secondary engine 11.
Operation principle: when launching female bullet 1 by master control system 4 after early warning system radar contact to enemy missile or target, the micro-unmanned reconnaissance plane 3 of three framves that female bullet 1 carries after launching is according to self investigation radius, order delivers from godown and automatically scouts enemy missile or target respectively, when enemy missile or target enter in the effective firing area of bullet 2, the enemy's information spied out is sent to secondary control system 9 emission bullet 2 by micro-unmanned reconnaissance plane 3, and bullet 2 is caught automatically, follow the trail of, lock enemy missile or target interception destroys.Automatically close self-destruction after investigation signal when scounting aeroplane 3 departs from scope of investigation, prevent from revealing investigation information.
The utility model not only can tackle multiple enemy missile, solves existing anti-missile system and is unable to cope with the problem that saturation type hits or many ripples hit; And can by the long-range delivery in ground, medium-long range hits multiple unfriendly target, is similar to unmanned plane operation, can greatly reduce combatant's casualty rate.
Above-described embodiment, just preferred embodiment of the present utility model, is not used for limiting the utility model practical range, therefore all equivalent variations done with content described in the utility model claim, all should be included within the utility model right.
Claims (3)
1. an anti-ballistic attack guided missile, is characterized in that: described guided missile is made up of female bullet (1), bullet (2) and micro-unmanned reconnaissance plane (3); The bullet inner top of described female bullet (1) is equipped with micro-unmanned reconnaissance plane (3), and the bullet of female bullet (1) circumferentially uniform bullet trajectory outlet (5); Bullet (2) and master control system (4) are equipped with in the body top of described female bullet (1), and main propellant (6) is equipped with in bottom, and tail end is equipped with sustainer (7); The top of described bullet (2) has warhead (8), secondary control system (9) is housed, and two secondary propellants (10) are equipped with at middle part, and tail end is equipped with secondary engine (11).
2. anti-ballistic attack guided missile as claimed in claim 1, it is characterized in that: the bullet inner top of described female bullet (1) is at least equipped with the micro-unmanned reconnaissance plane of three frame (3), and the bullet of female bullet (1) circumferentially at least uniform three bullet trajectory outlet (5); Three pieces of bullets (2) are at least equipped with on the body top of described female bullet (1).
3. anti-ballistic attack guided missile as claimed in claim 1 or 2, it is characterized in that: the tail end of described female bullet (1) is equipped with three sustainers (7), the tail end of described bullet (2) is equipped with a secondary engine (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420312196.3U CN204064129U (en) | 2014-06-12 | 2014-06-12 | Anti-ballistic attack guided missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420312196.3U CN204064129U (en) | 2014-06-12 | 2014-06-12 | Anti-ballistic attack guided missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204064129U true CN204064129U (en) | 2014-12-31 |
Family
ID=52205620
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420312196.3U Expired - Fee Related CN204064129U (en) | 2014-06-12 | 2014-06-12 | Anti-ballistic attack guided missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204064129U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110906795A (en) * | 2019-12-13 | 2020-03-24 | 陈忠响 | Middle section interception missile, system and method |
| CN114909959A (en) * | 2022-04-29 | 2022-08-16 | 西北工业大学 | Microminiature sub-missile multi-unit cooperative combat launching platform and method |
-
2014
- 2014-06-12 CN CN201420312196.3U patent/CN204064129U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110906795A (en) * | 2019-12-13 | 2020-03-24 | 陈忠响 | Middle section interception missile, system and method |
| CN110906795B (en) * | 2019-12-13 | 2022-07-05 | 谢勋 | Middle section interception missile, system and method |
| CN114909959A (en) * | 2022-04-29 | 2022-08-16 | 西北工业大学 | Microminiature sub-missile multi-unit cooperative combat launching platform and method |
| CN114909959B (en) * | 2022-04-29 | 2024-01-16 | 西北工业大学 | Microminiature sub-missile multi-unit cooperative combat launching platform and method |
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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: 20141231 Termination date: 20160612 |