Missile

FIELD: weapons and ammunition.

SUBSTANCE: missile includes case in the form of connected separable joint units with pyrotechnical burst connection of sealed head compartment with a sequence of homing head, inertial control system, ammunition, active thermal protection system and independent fluid or paste fuel propeller containing fuel with oxidiser and liquid-propellant rocket engine set with longitudinal nozzle, four liquid-propellant rocket engines with transverse nozzles and four liquid-propellant rocket engines generating head compartment torque, and propeller compartment with aerodynamic rudders, rudder drives, double-pulse solid fuel propeller aggregate, second pulse timing unit, correction unit.

EFFECT: efficient striking of high-altitude targets.

3 cl, 4 dwg

 

The present invention relates primarily to aircraft armament, namely to the guided missile of class "air-air" medium and long range, and can be used in the creation of multi-functional missiles to intercept objects in the atmosphere and near space. It can also be used to create high-altitude anti-aircraft missiles.

Is known (see patent RF №2327949 from 25.12.2006 by CL. F42B15/00) missile, comprising a housing, a guidance system with inertial control system, the receiving unit line correction, and homing head, combat gear and two-pulse propulsion system, including the engine of the first pulse and the engine of the second pulse.

The combustion chamber of the engine of the second pulse is located in series with the combustion chamber of the engine of the first pulse, two-pulse propulsion system made with a single outlet nozzle located on the back cover of the combustion chamber of the first pulse, and the guidance system is further provided with a definition block when the second pulse condition for meeting the missiles aimed approximately 1...2 seconds before the end of the second pulse and the amendment determining the speed boost from this impulse.

This embodiment of the missile provides increased its available �of regresar in the target region at high altitudes (30 to 40 km) through the projection of the thrust of the rocket engine to the normal to its velocity vector and increasing the velocity head due to the increased speed of the missile in the target region.

A disadvantage of the known technical solution, taken as the closest analogue is the fact that at these altitudes the effectiveness of aerodynamic control surfaces is greatly reduced, resulting in delayed release of the missile to the required angles of attack and, consequently, to reduce the likelihood of hitting the target. When attacking theatmospheric goals, of course, aerodynamic rudders completely ineffective.

The present invention is directed to solving the technical challenges of creating a controlled air missiles, capable of intercepting high-altitude air (up to 30...40 km) and theatmospheric purposes.

The technical result of the invention is effective defeat high-altitude targets.

The solution of the problem with the achievement of the claimed technical result is achieved in that in the rocket, comprising a housing with an aerodynamic rudders and wings, the seeker, inertial control system, combat gear and two-pulse solid-propellant propulsion system, the body is made in the form of United shared the docking consecutive brain and motor compartments, the first of which is sealed and contains a homing head, inertial control system, combat gear, a system of active thermal protection and Autonomous engine�th installation containing fuel with an oxidant and a set of rocket engines, and in the second compartment is placed aerodynamic rudders, steering actuators, two-pulse solid-propellant propulsion system, the block defining moment of start of the second pulse, the block of amendments, and share the docking station comprises at least one pyrotechnic burst fastening that ensures the separation by a signal from the control system.

In this set LRE Autonomous propulsion system includes a rocket engine with a longitudinal nozzle, four rocket engines with transverse nozzles to create transverse-momentum and four rocket engines to generate torques of the head compartment relative to its center of mass, and the Autonomous propulsion system of the head compartment is made of a liquid or paste-like fuel, which includes an oxidizing agent.

When attacking targets in the airspace at altitudes of up to 30...40 km of the proposed technical solution allows to increase the speed control missiles at angles of attack/slides compared with the prior art, since the aerodynamic control a rocket with wheels (located on the tail section of the engine Bay) is added gasdynamic control, realized by the use of transverse nozzles Autonomous propulsion system of the brain compartment.

Before�Agaeva technical solution allows to intercept and also theatmosphere goals after full testing of two-pulse propulsion system of the second compartment are separated and the head compartment is included Autonomous propulsion system, providing additional acceleration of the head unit using its rocket engine with a longitudinal nozzle and gas-dynamic control in the aiming process by the use of rocket engines with transverse rocket engine nozzles and orientation that are used to create torques about the center of mass of the head compartment.

The invention is illustrated by drawings, where Fig. 1 shows a layout diagram of the rocket, and Fig. 2, 3, 4 shows the scheme of creation of control forces when flying missiles in the atmosphere and beyond, respectively. Fig. 2, 3, 4 the following notation:

V - velocity missiles;

P1- transverse thrust nozzle of the Autonomous propulsion system of the brain compartment;

Y1- lift aerodynamic force missiles (body and wings);

Y2- lift aerodynamic force rudders missiles;

Tg- longitudinal thrust nozzle of the Autonomous propulsion system of the brain compartment;

P2- thrust nozzles stabilization, creating a torques head compartment around its center of mass.

Head control module air missiles (see Fig. 1) contains a homing head 1, the fighting part 2, �nellalou management system (IMS) 3, fuel fuel tank 4, the fuel supply system 5, fuel tank, oxidizer 6, the detachable connector 7, the power supply unit 8, a system of independent thermal overload protection (CAT) 9, the engines stabilize the rocket around the center of mass 10, the upper stage engine of the second stage 11, the non-contact sensor target (NDC) 22, block line correction, 23, nozzles motor longitudinal control 24.

The engine compartment of the rocket comprises a device for the separation of the brain and motor compartments 12, the block determining when the second pulse motor 13, an additional bottle of coolant CAT 14, the combustion chamber of the second pulse motor 15, the combustion chamber of the first pulse motor 16, 17 wing, drives the wheels 18, wheels 19, the power supply of the actuators 20, block 21 amendments.

The operation of the rocket using a 2-pulse motor when attacking targets in the air space is as follows. After starting from the media due to the operation of the first pulse of the engine, the missile acquires the necessary speed and flies to the target in accordance with the law of proportional navigation - n=k*ω, where n is an overload missiles, k - coefficient of proportionality, ω - angular velocity of the line of sight "rocket-target".

The guidance system of the missile, getting on-line correction from the aircraft carrier information about the mutual arrangement of p�chum and goals forms in the IMS data current according to the value range of the missile to the target, the relative speed of the missile and the target, and also determines the height and speed of the missile. The transmitter 13 receives these current data from IMS 3 largest-range missiles from the target (D) and relative velocity(D)missiles and targets. Amendment 21, receiving from the IMS data current (HpVp), taking into account the temperature of the charge of the second pulse determines the estimated increase in the velocity of the rocket from the second pulse and sends the resulting value to the calculator 13. The transmitter 13 on the basis of the data obtained and the approximation of the movement of the target determines the start time of the solid-propellant motor of the second pulse 15 of the terms of the security meetings missiles aimed approximately 1...2 seconds to complete all the work specified engine and when approaching the target at the estimated time sends a signal to the igniter 25 of the second pulse, which triggers the solid-propellant motor of the second pulse 15. In this case, rotation of the missile in the desired spatial position (angles of attack and sideslip) (see Fig. 2) is provided at the same time due to deflections of the aerodynamic rudders 19 with the help of actuators 18 and actuation autonoleggioortonovo engine headunit with the expiration of the gas jet through a system of transverse nozzles 24 of the control (the correction). Thus, the performance and, consequently, the efficiency of the control system of the rocket compared with the prototype increases. When approaching the target on command NDC (POS.22) is undermining the warhead 2.

When attacking theatmosphere purpose of the initial acceleration of the rocket at the expense of the 1st pulse 16 of the engine with subsequent acceleration at the 2nd pulse 15, and then at the command of Jesus (POS. 3) made the separation of the brain and motor compartments with a dividing device 12, for example by means of an elongated detonating cord, tearing a sidewall connecting the head and motor compartments.

Further acceleration headunit by using Autonomous liquid engine headunit with the expiration of the gas jet through a longitudinal nozzle 11. This targeting is made of gas-dynamic method using a system of transverse nozzles 24. The spatial position of a block is performed by using the nozzle system stabilization 10 (see Fig. 3, 4A, 4B).

The triggering of the warhead 2 when approaching the target mode according to the NDC, as and when attacking targets in the air space.

The proposed scheme for missile guidance provide the required performance and the desired level of congestion for the effective implementation of guidance and its time�ions in the atmosphere, and beyond.

A further advantage of the invention is that due to Aero / gas dynamic stabilization and control of a rocket start, it can be done with aircraft carriers, even at extremely low speeds, when purely aerodynamic control is impossible.

1. The missile, comprising a housing with an aerodynamic rudders and wings, the seeker, inertial control system, combat gear and two-pulse solid-propellant propulsion system, characterized in that the housing is made in the form of United shared the docking consecutive brain and motor compartments, the first of which is sealed and contains a homing head, inertial control system, combat gear, a system of active thermal protection and Autonomous propulsion system containing fuel with an oxidant and a set of rocket engines, and in the second compartment is placed aerodynamic rudders, steering actuators, two-pulse solid-propellant propulsion system, the block defining moment of start of the second pulse, amendment package, and share the docking station comprises at least one pyrotechnic burst fastening that ensures the separation by a signal from the control system.

2. �according to claim aceta 1, characterized in that the set of LRE Autonomous propulsion system includes a rocket engine with a longitudinal nozzle, four rocket engines with transverse nozzles to create transverse-momentum and four rocket engines to generate torques of the head compartment relative to its center of mass.

3. Missile according to claim 1, characterized in that the Autonomous propulsion system of the head compartment is made of a liquid or paste-like fuel, which includes the oxidizing agent.



 

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