CN1525135A - Active guiding missile - Google Patents

Abstract

The invention is an active guided missile, adding the front and back vector guided thrusters, and their corresponding control device, automatic control system, servo mechanism and so on into the existing warhead of guided missile or special cartridge case structure on guided missile body, able to control the front and back vector guided thrusters and their control mechanism to work according to the preset program of automatic control system and the servo mechanism as well as the signal given by object character contrast selected precision guidance control system or the measuring and control signal given by the base, realizing the purpose of the guided missile able to flexibly fly in low-layer space and in thin-air or vacuum high-layer space. The guided missile can break existing guided missile defence system, accurately shooting the target, and also holding up various fliers.

Description

A kind of active guidance type guided missile

A kind of active guidance type guided missile, it belongs to the improvement to attack guided missile and interception type guided missile.

Attack guided missile is generally based on ballistic missile, and ballistic missile generally is after by rocket engine it being pushed to certain altitude and speed, and bullet flies to the guided missile of target along destined trajectory by its inertia.Because its flight path is similar to the track of shell, so be called ballistic missile.Ballistic missile has characteristics such as far firing range, precision height, and can carry the nuclear bomb of multiple warhead and big equivalent, is the important deterrent power of national defence, also is the object of enemy's preferential defense.Study energetically and begun to dispose ballistic missile defense system along with some superpowers,, cause the deterrent effect of ballistic missile to weaken greatly as NMD (NMD) and Theater Missile Defense(TMD) system (TND).At present, why missile defense systems can defend ballistic missile, be because ballistic missile has the accurate movement track, infrared satellite of the space-based of missile defense systems and command centre can calculate the trajectory of ballistic missile according to the infra-red radiation motion track of its booster rocket, system of defense just can the destructive bomb ballistic missile with its kinetic warhead as long as launch advanced interception guided missile.So, the attacker has developed the ballistic missile that adopts petty action amount maneuvering technique to become rail and MIRV guidance technology again, but the existing motor-driven change rail of little momentum technology adopts radially propulsion mode shown in Figure 4 usually, its mobility is unsatisfactory, its propeller has adopted the into technology that picks that can send infrared radiation simultaneously, the guided missile propulsion device of MIRV guidance also is the into technology that picks that employing can be sent infrared radiation, therefore, even if the attacker launches this class advanced person's offensive missile, detectors such as the infrared satellite of space-based of missile defense systems can find that still offensive missile becomes the situation of rail and predicts the movement locus of guided missile afterwards, and the missile defense systems of defence side still can be launched the interception guided missile that has High Explosive Warhead and be used more advanced anti-guided missile laser system of defense to weave fine and close protection net and tackle this class offensive missile.So, up to the present, do not have still that desirable method efficiently breaks through earlier and then fine and close missile defense systems (particularly added in the future anti-guided missile laser system of defense after missile defense systems).

Interception type guided missile is a kind of guided missile of motor-driven trajectory, have commonly used air to air, ground-to-air or warship is to guided missiles such as skies, usually adopt the all-wing aircraft guider of the passive-type shown in the last figure of Fig. 3, this device can't make guided missile continue to possess maneuverability at upper space.Interception guided missile in the antimissile system also adopts radially propulsion mode shown in Figure 4 to make interception guided missile do maneuvering flight at the upper space of rarefaction of air, and its mobility is also unsatisfactory.

Missile defense systems is very big to the influence of China's national defense ability, particularly after the enemy has disposed advanced missile defense systems, causes very big threat and pressure can for our national security.Therefore, how tearing the protection net of enemy missile system of defense, set up our the advanced missile defense system simultaneously, further establish our national defence confidence, is the problem that each its people is concerned about.Purpose of the present invention is exactly to propose a kind of method of tearing the enemy missile protection net and improving our strategic defensive system capability.

The object of the present invention is achieved like this:

As shown in drawings, the present invention adopts special shell case structure 2-1 on existing guided missile warhead or body, increased leading to vector propeller and controlling organization 2-4, back steering vector propeller and controlling organization 2-5, automatic control system and servo control mechanism 2-6 thereof, the target signature contrast selection Precision Guidance and Control 2-7 of system and energy holding vessel and a controlling organization 2-8 or a part wherein simultaneously.Automatic control system and servo control mechanism 2-6 thereof, contrast is selected the signal that the Precision Guidance and Control 2-7 of system provides or is carried out the base measurement and control signal and control leadingly to vector propeller and controlling organization 2-4, back steering vector propeller and controlling organization 2-5 thereof and energy holding vessel and controlling organization 2-8 work thereof according to pre-set program and target signature, realizes that guided missile still can make the purpose of maneuvering flight at the upper space of rarefaction of air or vacuum.Like this, guided missile just can be realized Figure 11 and flight path shown in Figure 12.As Fig. 2, Fig. 3, Fig. 7, Fig. 9 and shown in Figure 10, when the steering vector propeller of guiding initiatively combines with the all-wing aircraft guider of traditional passive-type, can make the present invention when reentrying, make full use of the mobility of all-wing aircraft guider in the environment of normal air density of passive-type, make the steering vector propeller that initiatively leads in the environment of upper space vacuum or rarefaction of air, bring into play maximum effect, also can in the environment of normal air density, both combinations make guided missile have more mobility.

Profile of the present invention such as Fig. 1, Fig. 2 and shown in Figure 3, wherein: the left figure among Fig. 1 is existing multistage long-range missile, the 1st, bullet; Right figure adopts multistage long-range missile of the present invention, the 2nd, bullet.Left figure among Fig. 2 is existing short-range guided missile, and right figure adopts short-range guided missile of the present invention.Last figure among Fig. 3 is air to air (motor-driven) guided missile of existing passive all-wing aircraft guidance type, and figure below is to adopt of the present inventionly can attack or tackle the guided missile of upper space target.

The structure of shell case 2-1 of the present invention, as shown in Figure 7, among the figure: 2-1-1 is coating or the reflector laser and the electromagnetic composite coating of absorption of reflection (preventing) laser, its effect is that reflector laser is cut down the effect of laser energy to body, absorbing electromagnetic wave simultaneously makes body have " stealth " effect, simultaneously, body shape can also require design according to " stealth ", like this, shape adds coating or has adhered to high temperature resistant (can produce high temperature when bullet or body are reentried) by the body of stealth design, the body of reflector laser and electromagnetic-power-absorbing composite, it is disguised better.2-1-2 adopts high strength, high heat conduction and has the shell case structure sheaf that certain thickness light material is made, and its effect is to disperse the heat of assembling on the laser beam point of irradiation and resist the impact of High Explosive Warhead blast beyond certain distance and the strike of shell fragment with the fastest speed.2-2-3 is the shell case layer of aseismatic design, and its effect is to slow down the impact that High Explosive Warhead installs in exploding to bullet beyond certain distance, and device is finished the work by predetermined scheme in the protection bullet.

Of the present invention leading to vector propeller and controlling organization 2-4 and back steering vector propeller and controlling organization 2-5 such as Fig. 6, Fig. 7, Fig. 8 and shown in Figure 9: leadingly comprise propeller radome fairing 2-4-1 to vector propeller and controlling organization 2-4 thereof, driven crank (or gear) 2-4-2, compositions such as crank axle and key 2-4-3 and crank-pin 2-4-4, when automatic control system and servo control mechanism 2-6 thereof leading during by servo crank (or gear) 2-6-2 control to vector propeller and controlling organization 2-4 thereof, the leading swing of making the α angle to vector propeller and controlling organization 2-4 thereof, when energy holding vessel and controlling organization 2-8 thereof work under automatic control system and servo control mechanism 2-6 instruction thereof simultaneously, the leading flight attitude that can regulate guided missile to vector propeller and controlling organization 2-4 thereof.The structure of back steering vector propeller and controlling organization 2-5 thereof and operation principle are with leading identical to vector propeller and controlling organization 2-4 thereof, and the pendulum angle of its work is β.Generally between 0 °～180 °, wherein the steering vector propeller of an end can be fixed on 0 ° in the angle variation of α and β, to cooperate the work of other end steering vector propeller; The steering vector propeller that also can be front-end and back-end all can be swung the two ends collaborative work between 0 °～180 °.Steering vector propeller in steering vector propeller and the controlling organization thereof can adopt the cold propeller as power such as Fig. 6 and Compressed Gas shown in Figure 7,2-5-2 among Fig. 6 is that the angle of rake pressurized tank of Compressed Gas, 2-5-3 are that nozzle, 2-5-4 are electrically-controlled valve (it are controlled by automatic control system and servo control mechanism 2-6 thereof), and the 2-4-5 among Fig. 7 is the Compressed Gas jet pipe.The steering vector propeller also can adopt liquid rocket propeller shown in Figure 8 (hot propeller), and the 2-4-5 among Fig. 8 is the liquid fuel carrier pipe; The steering vector propeller can also adopt the solid-rocket propeller (hot propeller) shown in the 2-4 and 2-5 among Fig. 9.Here special recommendation Compressed Gas etc. is as the cold propeller of power, also comprises cold propeller is applied to radially propeller among Fig. 4.Though unit volume or Unit Weight energy stored with Compressed Gas etc. are big not as good as liquid or solid fuel, but only regulate the power of usefulness as the missile flight attitude, the Compressed Gas of one constant volume can energy stored enough at the flight attitude of considerable time and the interior adjusting guided missile of distance, have during especially Compressed Gas work done (spurting gas) and can absorb heat, and can not produce thermal-radiating characteristic, so it is a kind of cold propeller, cold propeller is in conjunction with requiring the missile airframe of design and apply reflector laser or reflector laser and the electromagnetic composite coating of absorption according to " stealth ", when then guided missile is done motor-driven orbital flight, any investigation of enemy was lost efficacy, therefore, the offensive missile of can maneuvering flight and really having " stealth " function can be broken through the defence of any system of defense of enemy.

In order to make guided missile have enough energy to guarantee the flight attitude of steering vector propeller at sufficiently long time and the interior accurate adjusting guided missile of distance, energy holding vessel and controlling organization 2-8 thereof are set in body, as shown in Figure 8: energy holding vessel and controlling organization 2-8 thereof are made up of energy holding vessel 2-8-1 and electrically-controlled valve 2-8-2 etc., and wherein electrically-controlled valve 2-8-2 is subjected to automatic control system and servo control mechanism 2-6 control thereof.Wherein, according to different propellers, can stores compression gas in the energy holding vessel, also can storaging liquid fuel.

Automatic control system and servo control mechanism 2-6 thereof can contrast signal or the base measurement and control signal of selecting the Precision Guidance and Control 2-7 of system to provide by preprogram and target signature, regulate the angle of rake vector of forward and backward steering vector (thrust and angle).According to experimental result and in advance the control program of establishment can be controlled missile maneuvers and accurately hit predeterminated target; Target signature contrast selects the signal that the Precision Guidance and Control 2-7 of system provides can the accurate hit of navigate missile; Simultaneously, when guided missile only adopts the contrast of preprogram and target signature to select signal guidance that the Precision Guidance and Control 2-7 of system provides, control system in the guided missile can be placed in the container of a high shielded, like this, even global position system (GSP) lost efficacy or under the strike and interference of enemy's high-strength magnetic arteries and veins, the present invention is accurately hit still.

It is that a kind of basis obtains in advance that the Precision Guidance and Control 2-7 of system is selected in the target signature contrast, Visible Light Characteristics in differing heights and environment around the predeterminated target, infrared signature, electromagnetic radiation feature, feature data such as scene characteristic on every side, by the in-situ data of investigating at varying environment, differing heights in the computer contrast missile flight process of this system, the intelligently guiding guided missile is selected the system of target of attack.As long as have fully and accurately predeterminated target data and enough interference protection measures, this system can the accurate hit of navigate missile in certain distance.

Because adopt such scheme, the present invention can realize: maneuvering flight is also accurately attacked unfriendly target; At high level or outer space interception unfriendly target; The efficient moving target of attacking or tackling the enemy.Thereby make us can tear enemy's missile shield and set up our system of defense efficiently, pulverize enemy's the land, sea, air advantage and the blackmail of missile defense systems.

The present invention is further described below in conjunction with drawings and Examples.

Fig. 1 is the profile contrast figure that multistage long-range missile is used the present invention front and back, and left figure wherein is existing multistage long-distance ballistic missile, the 1st, and bullet; Right figure adopts multistage long-range missile of the present invention, the 2nd, bullet.

Fig. 2 is the profile contrast figure that short-range guided missile is used the present invention front and back, and wherein: left figure is existing short-range ballistic missile, and among the figure: 1-1 is that body, 1-2 are that preceding fixed-wing, 1-3 are the back fixed-wings; Right figure adopts short-range guided missile of the present invention, among the figure: 2-1 be body, 2-2 be preceding guide vane, 2-3 be back guide vane, 2-4 be leading to vector propeller, 2-5 be back steering vector propeller, α be preceding guide vane and leading be the motor-driven pivot angle of back guide vane and back guided propeller to angle of rake motor-driven pivot angle, β.

Fig. 3 is the profile contrast figure that the motor driven type guided missile is used the present invention front and back, last figure wherein is air to air (motor-driven) guided missile of existing passive all-wing aircraft guidance type, among the figure: 1-1 is that body, 1-2 are that back fixed-wing, 1-5 are that back vector propeller, β are the adjustable-angles of back vector propeller by preceding motor-driven guide vane, the 1-3 of action-oriented, β＜180 °; Figure below is to adopt the present invention and have autonomous guide function, can attack or tackle the guided missile of upper space target, among the figure: 2-1 be body, 2-2 be preceding guide vane, 2-3 be back fixed-wing, 2-4 be leading to propeller, 2-5 be back vector propeller, α be preceding guide vane and leading be the adjustable-angle of back vector propeller to angle of rake motor-driven pivot angle, β.

Fig. 4 is the structural map of existing change rail bullet, and among the figure: 1-1 is that body, 1-5 are that radially hot propeller, 1-6 are fuel tank.When 1-5 adopts cold propeller of the present invention, 1-6 then is compression gas tank, the change rail bullet of this moment will possess the stealthy condition that becomes rail.

Fig. 5 is the schematic diagram of existing long-distance ballistic missile bullet, and among the figure: 1-1 is the body of bullet.

Fig. 6 is that steering vector propeller of the present invention adopts the angle of rake warhead structure schematic diagram of Compressed Gas, among the figure: 2-1 is a body, 2-4 is leading to propeller, 2-4-1 is the hold concurrently shell of compression gas tank of the radome fairing of forward propeller, 2-4-2 is driven crank, 2-4-3 is propeller swinging axle and key, 2-4-4 is a connecting pin, 2-5 is the back guided propeller, 2-5-1 is the hold concurrently shell of compression gas tank of the radome fairing of after propeller, 2-5-2 is a compression gas tank, 2-5-3 is a propeller Compressed Gas nozzle, 2-5-4 is an electrically-controlled valve, 2-6 is automatic control system and servo control mechanism thereof, 2-6-2 is the active shift fork of automatic control system and servo control mechanism thereof, 2-7 is that the Precision Guidance and Control system is selected in the target signature contrast, α is leading to angle of rake motor-driven pivot angle, and β is the motor-driven pivot angle of back guided propeller.

Fig. 7 is steering vector propeller employing Compressed Gas propeller of the present invention and warhead structure and the shell case structural representation that has motor-driven guide vane, among the figure: 2-1 is that shell case, 2-1-1 are the coat of shell case, the safeguard structure layer that 2-1-2 is shell case, 2-2 is preceding guide vane, 2-3 is the back fixed-wing, 2-4 is leading to propeller, 2-5 is the back vector propeller, α is a preceding guide vane and leading to angle of rake motor-driven pivot angle, β is the adjustable-angle of back vector propeller, and 2-8-1 is that Compressed Gas holding vessel, 2-8-2 are electrically-controlled valve.

Fig. 8 is that steering vector propeller of the present invention adopts the liquid rocket propeller and not with the warhead structure and the shell case structural representation of motor-driven guide vane, among the figure: 2-1 is a shell case, 2-4 is leading to propeller, 2-4-5 is the liquid fuel conduit, 2-5 is the back vector propeller, α is leading to angle of rake motor-driven pivot angle, β is the adjustable-angle of back guided propeller, 2-6 is automatic control system and servo control mechanism thereof, 2-6-2 is the active shift fork of automatic control system and servo control mechanism thereof, 2-7 is that the Precision Guidance and Control system is selected in the target signature contrast, and 2-8 is liquid fuel holding vessel and controlling organization thereof, 2-8-1 is the liquid fuel holding vessel, 2-8-2 is an electrically-controlled valve.

Fig. 9 is steering vector propeller employing solid-rocket propeller of the present invention and warhead structure and the shell case structural representation that has motor-driven guide vane, among the figure: 2-4 is leading to the solid-rocket propeller, 2-5 is a back guiding solid-rocket propeller, α is a preceding guide vane and leading to the angle of rake motor-driven pivot angle of solid-rocket, and β is the adjustable-angle of back vector propeller.

Figure 10 adopts the autonomous guidance type guided missile of two-stage of the present invention, among the figure: 2-1 be one-level body, 2-2 be guide vane before the one-level, 2-3 be guide vane after the one-level, 2-4 be one-level leading before steering vector propeller, α are one-level after vector propeller, 2-5 are one-level guide vane and leading after angle of rake motor-driven pivot angle, β are one-level the motor-driven pivot angle of guide vane and back guided propeller; 2 ' the-1st, final stage body, 2 '-2nd, guide vane, 2 before the final stage '-3rd, guide vane, 2 '-4th after the final stage, final stage is leading to vector propeller, 2 '-5th, after the final stage steering vector propeller, α ' be before the final stage guide vane and leading to angle of rake motor-driven pivot angle,, β ' is the motor-driven pivot angle of guide vane and back guided propeller after the final stage.

Figure 11 is the flight path figure of guided missile, the dotted line of A → B and B → D is the flight path of ballistic missile among the figure, the A point is our missile launching base, A → B section is the rocket assist section, the dotted line of B → D is the coast period of bullet, the target that D is attacked is because the accurate flying track of ballistic missile is easy to be tackled by the interception guided missile of antimissile defence system in the phantom line segments of B → D.A → B → C and C → D, C → E and C → F are maneuverable paths of the present invention, and the A point is our missile launching base, and A → B section is the rocket assist section, and in B → C maneuvering flight stage of the present invention, D, E, F point are by target of attack; The present invention can select the Precision Guidance and Control 2-7 of system guiding accurately to hit predetermined target D, E or F by the target signature contrast, and interception guided missile can't be tackled the autonomous guidance type guided missile of doing maneuvering flight and having hidden function in the beginning of C point.Among the figure: D, E are ground targets, and F is a waterborne target.

Figure 12 is the present invention at this end under the assistance of the infrared satellite of space-based and investigation satellite, interception enemy stealth aircraft, destroys aircraft such as enemy's prior-warning plane, attacks the schematic diagram of enemy's water surface and moving target under water.Among the figure: curve is that flight path of the present invention, A point are our missile launching bases, T is our space-based infrared acquisition satellite or investigation satellite, A → B section is the rocket assist section, B → C section is the maneuvering flight stage of searching target, and C → F, C → G section is that the Precision Guidance and Control system guiding precise guidance stage is selected in the target signature contrast; C → H, C → I are that the autonomous guidance type guided missile of final stage selects the Precision Guidance and Control system to guide the accurate stage in the target signature contrast, and F is that water surface moving target, G are that moving target, H are that prior-warning plane, I are stealth aircrafts under water.

Application note of the present invention

Attack guided missile of the present invention has utilized the active guide function of the inertia of the angle of rake thrust of ballistic missile and bullet or body flight in conjunction with the vector guided propeller of the present invention's proposition, under the control of pre-set program, bullet (warhead) is done the swing (comprising straight line and direction, the uncertain curve of amplitude, pitch forward or backwards and the uncertain helix of diameter etc.) of any amplitude of three-dimensional around the main trajectory, makes the function of the kinetic warhead forfeiture expection of enemy missile system of defense interception guided missile.The cold propulsion plant if the vector of the no infra-red radiation of employing leads, in conjunction with special high strength and high heat conduction shell case material, backward-reflected laser and absorb electromagnetic coat and shockproof structure, the Reconnaissance system (detectors such as infrared satellite of space-based and early warning radar) of enemy missile system of defense can't be surveyed, follow the trail of, the interception guided missile and the laser of the band High Explosive Warhead of missile defense systems emission also can't be tackled (wherein, laser antimissile system emitted laser Shu Wufa focuses on the same point of offensive missile with time enough, simultaneously the overcoat of offensive missile can the very fast heat that illuminated laser spot is assembled distributes), thus the state-of-the-art missile defense systems of enemy also can't be produced a desired effect.Because initiatively the guidance type guided missile has good mobility, it can also come accurate guidance to ratio selection control system in conjunction with advanced person's target signature, can lose efficacy and does not have under the situation of artificial observing and controlling control automatically and guiding bullet and accurately hit unfriendly target (no matter emission back) at global position system (GSP).Simultaneously, because its control system can not receive extraneous instruction and " going one's own way ", so this system can place in the container of high shielded, and the electromagnetic pulse that causes the enemy is to strike of the present invention and disturb and lost efficacy.

When the present invention is applied in interception guided missile in the antimissile system, it utilizes the angle of rake thrust of interception guided missile and the inertia of bullet flight and the all-wing aircraft guider of passive-type, in conjunction with initiatively guide function acting in conjunction of vector propulsion device of the present invention, make the interception guided missile bullet in the environment of upper space vacuum or rarefaction of air, still have higher mobility and controllability, avoided adopting all-wing aircraft by the shortcoming of the interception guided missile of action-oriented mobility difference and poor controllability in the environment of upper space vacuum or rarefaction of air.Therefore, the present invention can make the function of interception guided missile interception upper space target improve greatly, and this interception guided missile can also be tackled enemy satellites expeditiously; When the active steering vector propeller of interception guided missile adopts radiationless vector to lead cold propeller, then tackle enemy satellites and have more disguise.

The present invention is at this end under the assistance of the infrared satellite of space-based and investigation satellite, interception enemy stealth aircraft, destroys aircraft and land, the water surface and moving target under water such as enemy's prior-warning plane.Its principle is: when the infrared satellite of our space-based is found enemy land, the water surface and moving target under water with the investigation satellite, we launches offensive missile of the present invention to the general orientation of moving target in the base, the offensive missile maneuvering flight arrives the overhead search of target, utilizes the target signature among the present invention to come precise guidance to hit land, the water surface and mobile mobile phase under water to slow target to ratio selection control system.When investigating the target of fast moving such as satellite discovery enemy stealth aircraft, prior-warning plane when us, we launches multistage autonomous guidance type guided missile shown in Figure 10 to the general orientation of these targets in the base, autonomous guidance type guided missile arrives the B-C section ferret out of the target sky in Figure 10, when autonomous guidance type guided missile after C point discovery target, the autonomous guidance type guided missile of two-stage separates, the autonomous guidance type guided missile of final stage can be under the guiding of target signature to ratio selection control system, accurately hit; This method is equivalent to our aircraft and searches enemy's aircraft in the commanding elevation, and to enemy's aircraft emission air-to-air missile; If accurately hit snugly, except that steering vector propeller of the present invention adopts the cold propeller, its main thruster also can adopt cold propeller.Especially search and tackle enemy's stealth aircraft, can only be at the infrared signal trace a little less than it just might be found in the back upper place of stealth aircraft, the target signature of autonomous guidance type guided missile also only could be followed the trail of its faint infrared signature signal in the back upper place of stealth aircraft to ratio selection control system, and just can follow the trail of the Visible Light Characteristics signal and the infrared signature signal of stealth aircraft in nearer distance, and according to the accurate hit of these characteristic signal navigate missiles, and general opportunity of combat is the commanding elevation that can't successfully arrive relative stealth aircraft; Simultaneously, be a kind of interception of non-personnel's contact with autonomous guidance type missile intercept enemy stealth aircraft, can not cause our casualties.In addition, enemy's early warning generally all is in us and has now outside the range of air-to-air missile or ground (warship) antiaircraft missile, and a powerful group of planes and missile defense systems protection are arranged, and our opportunity of combat also can't arrive in the effective range of attacking enemy's prior-warning plane smoothly.Therefore, have only the purpose of utilizing autonomous guidance type guided missile just can reach interception and destroy enemy's stealth aircraft and prior-warning plane, and all interceptions of right and wrong personnel contact.

Implement the present invention with respect to disposing NMD and setting up for the aeroamphibious strategic assets, characteristics such as simple, the reduced investment of possessing skills, instant effect, and can promote us to build complete strategic defensive system and aeroamphibious strategic assets.

In sum, every function of the present invention is enough to make us to build powerful deterrent power and effective system of defense with lower cost and fast speeds, this construction achievement, the peaceful reunification of the motherland that promotes to defendance China, and avert a war and safeguard world peace, be vital.

Claims (9)

1, a kind of active guidance type guided missile, be on existing guided missile warhead or body, to have adopted special shell case structure, steering vector propeller and controlling organization thereof have been increased simultaneously, automatic control system and servo control mechanism thereof, Precision Guidance and Control system and energy holding vessel and a controlling organization or a part are wherein selected in the target signature contrast, it is characterized in that: preceding, back steering vector propeller and controlling organization thereof are under the control of automatic control system and servo control mechanism and target signature contrast selection Precision Guidance and Control system, navigate missile can both be done maneuvering flight at the low sheaf space of normal air density and the upper space of vacuum or rarefaction of air, and accurately hit snugly.

2, active guidance type guided missile according to claim 1 is characterized in that: increased the vector propeller that play the guiding role on bullet or body.

3, active guidance type guided missile according to claim 1, it is characterized in that: automatic control system and servo control mechanism thereof are to contrast the vector that the signal of selecting the Precision Guidance and Control system to provide is controlled vector propeller according to pre-set program and target signature, and automatic control system wherein places in the container of a high shielded.

4, active guidance type guided missile according to claim 1, it is characterized in that: the target signature contrast of its configuration selects the Precision Guidance and Control system to have according to the Visible Light Characteristics around the predeterminated target that obtains in advance in differing heights and environment, infrared signature, electromagnetic radiation feature, feature data such as scene characteristic on every side, by the in-situ data of investigating at varying environment, differing heights in the computer contrast guided missile practical flight process of this system, Intelligence Selection and navigate missile are attacked the function of predeterminated target.

5, active guidance type guided missile according to claim 1, it is characterized in that: the shell case structure has the composite construction of coat, structure sheaf and shakeproof layer, apply or adhered to the material of reflector laser on the coat wherein, perhaps high temperature resistant, reflector laser and electromagnetic-power-absorbing composite, or add high temperature resistant, reflector laser and electromagnetic-power-absorbing composite by the body of stealth design in shape.

6, active guidance type guided missile according to claim 1 is characterized in that: multistage active guidance type guided missile can be combined, and unites to finish and attacks or the interception task.

7, steering vector propeller according to claim 2 is characterized in that: adopted cold Push Technology, the propeller that cold propeller also can be applicable to improve the main thruster of multiple-stage missile final stage and radially becomes rail.

8, steering vector propeller according to claim 2, it is characterized in that: can with combined by the all-wing aircraft of action-oriented, be combined into and can do maneuvering flight at the low sheaf space of normal air density and the upper space of vacuum or rarefaction of air, but the mobile missile of the reasonable disposition guided propeller energy amount of carrying again simultaneously.

9, active guidance type guided missile according to claim 1 is characterized in that: the structure sheaf of shell case structure adopts high strength, high heat conduction and has certain thickness light material manufacturing.

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