CN104165555A

CN104165555A - Intercept-prevention missile

Info

Publication number: CN104165555A
Application number: CN201310201756.8A
Authority: CN
Inventors: 刘祖学
Original assignee: Individual
Current assignee: Individual
Priority date: 2013-05-19
Filing date: 2013-05-19
Publication date: 2014-11-26

Abstract

The invention discloses an intercept-prevention missile. According to the technical scheme, after the missile is launched, the flight track and flight speed are changed continually and unpredictably for an early warning system of the other party, the flight rule can not be found out, and intercept can not be performed. In order to solve the technical problems, in detail, multiple track changing cannons are arranged randomly on the left side and the right side of the tail basically in a horizontal flight state in a staggered mode when the missile flies at the middle section, when the missile flies at the middle section, the track changing cannons are sequentially detonated, the flight track of the missile is randomly changed, speed changing is achieved through slightly changing the amount of supplied propellant, in this way, the early warning system of the other party can not find out the flight rule, and the missile can not be intercepted and hit.

Description

Anti-interception guided missile

Technical field:

The present invention relates to a kind of guided missile, be specifically related to can prevent after a kind of transmitting the anti-interception guided missile of interception.

Background technology:

To at present, the guided missile of every batch of production, flying speed and track after transmitting all determine, indeclinable, thus its in-flight key property easily by early warning system, grasped, thereby cause being easily blocked and smashing, cause happy mistake opportunity of combat and massive losses.

Summary of the invention:

Object of the present invention is in order to overcome above-mentioned deficiency of the prior art, and the guided missile that can prevent interception after a kind of transmitting is provided.

To achieve these goals, the technical scheme that the present invention takes is: make after MISSILE LAUNCHING, track and the speed of flight constantly change, allow the other side's the early warning system unpredictable on aerial and ground, cannot find flight rule, when it has just measured relevant data, while preparing interception, this guided missile has changed again heading and speed, makes enemy cannot implement interception.The object of the invention is to realize by following measure, specifically: a kind of anti-interception guided missile, by conventional missile with change rail big gun and form, is characterized by: the propellant feed amount of described conventional missile engine changes at random, makes flying speed change at random; The described heat insulation both sides that are arranged on anti-interception guided missile horizontal flight attitude afterbody of rail big gun that change, it is little big gun body corresponding and dislocation, after ignition, track that can randomly changing flight.While launching this guided missile, farther sooner for same large missile flight is obtained, can adopt the dynamically method of transmitting (it is 201210202017.6 files that the method and device can be consulted the patent No.) of cumulative.

The present invention compared with prior art has following advantage:

(1) arranging simply of change of flight track and speed, cost is little, the light emblem of increasing weight.

(2) track and the speed of flight are randomly changings, at all unpredictable and grasp moving law;

Below by drawings and Examples, technical scheme of the present invention is described in further detail.

Accompanying drawing explanation:

Fig. 1 is that to change rail big gun position view Fig. 2 be the longitudinal stroke schematic diagram that anti-interception guided missile correspondence changes rail to anti-interception guided missile

Description of reference numerals:

1A changes rail big gun 2A left and changes rail big gun 3A to the right and change rail big gun to the right

1B changes rail big gun 2B to the right and changes rail big gun 3B left and change rail big gun left

1A ' moves to right front to right front motion 3A ' to left front motion 2A '

1B ' moves to left front to left front motion 3B ' to right front motion 2B '

The specific embodiment:

Anti-interception guided missile as shown in Figure 1, by conventional guided missile He Gai rail battery, become, the propellant of its engine has change at random for amount, make flying speed change at random, the described rail big gun that changes is for the little big gun body of corresponding dislocation, its can be made to anti-interception guided missile randomly changing flight track after igniting, and its concrete structure and enforcement changes rail, it is as follows to change fast mode:

1, concrete structure

Change the heat insulation anti-interception guided missile horizontal flight attitude afterbody left and right sides that is positioned on of rail big gun, its relative and dislocation, the charge weight of every relative two big guns is roughly the same, and every two adjacent big gun charge weights are different, the horizontal amplitude that so just makes it at every turn change in-flight rail is different, and distance is different longitudinally.

2, change rail and change fast mode:

When interception guided missile enters the basic horizontal mission phase in stage casing, first ignite 1A big gun, now guided missile is 1A ' to left front flight track, ignite again 1B big gun, guided missile is 1B ' to right front flight track, then ignites 2A big gun, and guided missile is 2A ' to right front flight track again, ignite again 2B big gun, guided missile is 2B ' to left front flight track, then ignites 3A big gun, and guided missile is 3A ' to right front flight path, ignite 3B big gun, guided missile is 3B ' to left front flight track; By the method changing for engine propellant, realize speed change simultaneously, FH section is slack-off, F ' H ' section accelerates, so randomly changing flight track and speed make enemy's early warning system cannot obtain regular data, anti-interception guided missile is by set target-seeking method, fly to the ignition guided missile that struck target, complete and strike target.

From finding out that above anti-interception guided missile has been set up, change rail and speed change setting, its structure is also uncomplicated, increases weight small, make missile flight change rail and speed change all has randomness, make enemy's early warning system intangible, therefore, cannot obtain regularity, just cannot implement interception, realize the effect of anti-interception.

Claims

1. an anti-interception guided missile, it is become by guided missile He Gai rail battery, it is characterized by: described guided missile is conventional missile, its engine propellant feed amount change at random; The described heat insulation two sides of tail that is positioned on anti-interception guided missile horizontal flight attitude of rail big gun that changes.

2. according to a kind of anti-interception guided missile claimed in claim 1, it is characterized by: described in change rail big gun for little big gun body corresponding and dislocation, after its is ignited, can make anti-interception guided missile randomly changing flight track.

3. according to anti-interception guided missile claimed in claim 1, it is characterized by: it changes speed is for amount change at random, to produce speed change by engine propellant.