CN103673785A

CN103673785A - Antimissile preventing missile having stealth function and flying in moth-type deflecting mode

Info

Publication number: CN103673785A
Application number: CN201210378543.8A
Authority: CN
Inventors: 王正铉
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-09-20
Filing date: 2012-09-20
Publication date: 2014-03-26

Abstract

The invention provides an antimissile preventing missile having a stealth function and flying in a moth-type deflecting mode. By the adoption of a plurality of small turning and jet rockets designed originally and arranged at the tail of the missile, the flying direction of the missile is changed continuously and suddenly, namely, the moth-type deflecting flying mode is adopted and a plurality of small concave pits or a plurality of small convex points are designed on the total surfaces, allowing to be designed, of the missile or the conical surface of the head of the missile so as to reduce relative friction force and relative viscous force of the air. The antimissile preventing missile has the advantages that the missile does not need to always pursue high-speed flying; reflection of the missile on radar waves is reduced by the adoption of the technology that anti-interception is carried out through the moth-type deflecting flying mode, and by the adoption of the small concave pits or the small convex points originally designed on the surface of the missile, missile stealth is facilitated, the flying speed and firing range of the missile is improved, and the interception of an antimissile system of the enemy can be effectively broken through. The antimissile preventing missile is simple in manufacturing process, low in cost, easy to implement and applicable to various self-propelled missiles including torpedoes.

Description

Adopt the break-in of moth formula to fly and there is the anti-anti-ballistic guided missile of hidden function

Technical field: the present invention relates to a kind of " adopt the break-in of moth formula fly and have hidden function anti-anti-ballistic guided missile ".

Background technology: current, in military field, long-range, the rapid, precise strike of guided missile determine one of principal element of victory or defeat in war beyond doubt.To this, between various countries, in the research and development of guided missile, to direct and anti-ballistic antagonism and competition, contending with of this lance and shield is growing more intense with trial of strength.Therefore, how to break above-mentioned equilibrium to take the good opportunity, the target place that various countries competitively research and develop beyond doubt.

In addition, direct with anti-ballistic antagonism in, the cost of the establishment of anti-missile system is too high, technical sophistication.In contrast, the R&D costs of directing technology are relatively cheap, and guidance technology itself is also relatively easy to implement, are easy to progress and improve.Therefore, how to improve the technology of directing of guided missile to break through anti-missile system to the interception of directing, lance is defeated shield, and just day is aobvious important and urgent.

In addition, the surface of guided missile is all made smooth.Smooth surface has increased radar wave reflection, is unfavorable for stealth.Particularly, ganoid guided missile, in the process of whole high-speed flight, is that air is being carried out pushing and pushing open air to advance, until finally hit the mark always.According to relative motion principle, what high-speed flight guided missile pushed is exactly highdensity air, thereby has produced huge relative friction and viscous force.This huge relative friction has consumed the kinetic energy that guided missile advances, and has finally converted useless heat energy to.The guided missile of high-speed flight simultaneously, its place ahead has a higher-pressure region.Air stream can be separated with body when the leading edge of body flows to rear again.Like this, at the rear of body, have a turbulent wake zone.In this region, air-flow fluctuating disturbance, and then cause the pressure at guided missile rear lower, thus after having been produced to one, body drags power.Its result is all that the range that has shortened guided missile has also affected the accuracy that guided missile advances along correct trajectory simultaneously, affected the degree of accuracy that guided missile is hit target.

The present invention can improve the hidden function of guided missile, improves flying speed and the range of guided missile, effectively completes anti-missile system to the interception of directing the attack degree of accuracy that improves guided missile.

Summary of the invention: the object of this invention is to provide a kind of " adopt the break-in of moth formula fly and have hidden function anti-anti-ballistic guided missile "; it is that a kind of utilization is designed with; a plurality of small-sized tuning that is arranged on missile tail is sprayed constantly flip-flop guided missile direct of travel of rocket; allow this guided missile adopt moth formula break-in flight (at occurring in nature; often can fly a kind of slight moth at us around.That although it flies and unhappy, it is caught than more difficult the flutterring of its faster other insect than flying speed.Trace it to its cause, be just this slight moth be in a kind of special mode in flight, constantly flip-flop heading is broken away to be flutterred and is caught, moth flight theory that Here it is.), anti-ballistic to carry out; And according to golf principle, (that is, at golf ball surface, be designed with many small ruts.Because the small rut of golf ball surface can destroy the viscous effect to golf ball surface of the air layer that contacts with golf ball surface effectively, and then reduce the resistance of air to ball, increase the lift of ball, allow golf fly fartherly sooner.) on the bullet nose circle cone surface of guided missile or on all surfaces of guided missile permission design, according to the large little science of body, design, meet aerodynamics requirement, to reduce relative friction, the viscous force to air, after acquisition minimum, drag many small ruts or small salient point that power and maximum hoist capacity are final purpose, and then the flying speed that is improved guided missile is with stealthy, get rid of the interception guided missile that enemy attacks, the attack degree of accuracy that effectively breaks through enemy's anti-missile system and improve guided missile, and target of attack is destroyed the most at last.

Owing to adopting moth formula break-in flight to direct technology, with constantly fast break-in fly to break through anti-ballistic, so this guided missile both can do supersonic flight and also can do subsonic speed cruising flight, needn't pursue simply the high speed of flight.The anti-interception mode of technology is directed in the moth formula break-in flight adopting, even if enemy's early warning radar is just found the whereabouts of this guided missile in early days, also also launches in time interception guided missile, also will be difficult to smash this guided missile.The R&D costs that technology is directed in this moth formula break-in flight are relatively cheap, and guidance technology itself is also relatively easily implemented.What be designed with both can reduce guided missile at the lip-deep many small ruts of guided missile or small salient point radar wave reflection had been beneficial to stealth, can improve again flying speed and the range of guided missile.In guided missile manufacture, needn't carry out large change, manufacturing process is simple, cheap for manufacturing cost.The present invention can be used for comprising the various self-propelled type guided missiles of torpedo.

Accompanying drawing explanation: accompanying drawing 1 is the structural representation of facing of the present invention.

Accompanying drawing 2 is left TV structure schematic diagram of the present invention.

Accompanying drawing 3 is the schematic diagram of the present invention along trajectory flight.

The specific embodiment: the present invention includes: guided missile 1, design and installation is sprayed rocket A in the small-sized tuning of guided missile 1 afterbody, small-sized tuning is sprayed rocket B, small-sized tuning is sprayed rocket C, small-sized tuning is sprayed rocket D, flight guide controller 2, design is at the lip-deep many small ruts of guided missile 1 or small salient point 3, trajectory 4, the flight condition 5 of guided missile 1, the flight condition 6 of guided missile 1, the flight condition 7 of guided missile 1, the flight condition 8 of guided missile 1, the flight condition 9 of guided missile 1, the flight condition 10 of guided missile 1.Small-sized tuning sprays rocket A and small-sized tuning is sprayed rocket B symmetry, and small-sized tuning sprays rocket C and small-sized tuning injection rocket D is symmetrical.

After guided missile 1 transmitting, in safe spatial domain, along trajectory 4, carry out normal flight with fast-closing attack target, now guided missile 1 is in missile flight situation 5.When guided missile 1 approaches enemy war spatial domain or meets with anti-missile interception threat, flight guide controller 2 sprays rocket A to small-sized tuning and sends tuning jeting instruction, small-sized tuning is sprayed rocket A and is carried out at once tuning injection, guided missile 1 departs from trajectory 4 fast upward, and now guided missile 1 is in missile flight situation 6.Then, flight guide controller 2 sprays rocket B to small-sized tuning and sends tuning jeting instruction, and small-sized tuning is sprayed rocket B and carried out at once tuning injection, and guided missile 1 departs from trajectory 4 fast downwards, and now guided missile 1 is in missile flight situation 7.Then, flight guide controller 2 sprays rocket C to small-sized tuning and sends tuning jeting instruction, and small-sized tuning is sprayed rocket C and carried out at once tuning injection, and guided missile 1 departs from trajectory 4 to left fast, and now guided missile 1 is in missile flight situation 8.Then, flight guide controller 2 sprays rocket D to small-sized tuning and sends tuning jeting instruction, and small-sized tuning is sprayed rocket D and carried out at once tuning injection, and guided missile 1 is fast to the right-hand trajectory 4 that departs from, and now guided missile 1 is in missile flight situation 9.Break away from enemy missile interception or successfully enter after firing area, flight guide controller 2 sprays rocket A to small-sized tuning simultaneously, small-sized tuning is sprayed rocket B, small-sized tuning is sprayed rocket C, small-sized tuning is sprayed rocket D and is sent tuning jeting instruction, small-sized tuning is sprayed rocket A, small-sized tuning injection rocket B, small-sized tuning injection rocket C, small-sized tuning injection rocket D carry out tuning injection at once, rapidly the heading of guided missile 1 is called in along bullet trajectory 4 and flies and also help fast injection simultaneously.And then the guided missile 1 finishing after tuning initiates to attack at full speed along trajectory 4, in missile flight situation 10.The software program on adding in the robot control system(RCS) that flight guide controller 2 maybe can be designed with guided missile Central Plains with flight guide controller (2) function completes., needn't be designed with separately again flight guide controller 2.Because design is at the lip-deep many small ruts of guided missile 1 or small salient point 3, reduced by 1 pair of radar wave reflection of guided missile, be beneficial to the stealthy of guided missile 1 and improved flying speed and the range of guided missile 1.

Claims

1. adopt the break-in of moth formula fly and have hidden function an anti-anti-ballistic guided missile, its feature mainly includes guided missile (1), design and installation and in the small-sized tuning of guided missile (1) afterbody, sprays rocket (A), small-sized tuning and spray that rocket (B), small-sized tuning spray rocket (C), small-sized tuning is sprayed rocket (D); Small-sized tuning is sprayed rocket (A) and is sprayed rocket (B) symmetry with small-sized tuning, and small-sized tuning is sprayed rocket (C) and sprayed rocket (D) symmetry with small-sized tuning; Flight guide controller (2), design in the lip-deep many small ruts of guided missile (1) or small salient point (3), trajectory (4), the flight condition (5) of guided missile (1), the flight condition (7) of the flight condition (6) of guided missile (1), guided missile (1), the flight condition (9) of the flight condition (8) of guided missile (1), guided missile (1), the flight condition (10) of guided missile (1); The software program on adding in the robot control system(RCS) that flight guide controller (2) maybe can be designed with guided missile (1) Central Plains with flight guide controller (2) function completes, and needn't be designed with separately flight guide controller (2) again; The present invention can be used for comprising the various self-propelled type guided missiles of torpedo.