RU183918U1 - Anti-aircraft guided missile - Google Patents

Abstract

The utility model relates to rocket technology, in particular to anti-aircraft guided missiles.

Anti-aircraft missile, in the form of a cone-shaped body, with a fairing included in it, a starting propulsion system, a marching propulsion system, a transition compartment, control and guidance devices, a warhead, launch and marching controls, characterized in that the fairing and transition compartment are made of heat-resistant electrically conductive material, on the surface of which an electrically conductive emission layer and a layer of perception of electrons from materials with low electron work function are deposited with the formation through a closed-circuit electric power source, while a high-speed ramjet engine is installed as a marching propulsion system.

The technical result consists in increasing the efficiency of hitting high-speed targets by ensuring the support of the movement of SAMs at high speeds while maintaining its integrity under conditions of aerodynamic heating characteristic of high speeds by installing a VVPRD as a marching engine and organizing electronic cooling during thermionic emission of the SAM shell. 1 ill.

Description

The utility model relates to rocket technology, in particular to anti-aircraft missiles.

Known anti-aircraft missile according to the patent for invention No. RU 2341762, which contains a housing, a propulsion system, control system equipment, combat equipment, four folding aerodynamic steering wheels and four folding stabilizers.

The disadvantage of this analogue is the low flight speed and inability to destroy high-speed aircraft (VLA).

Known anti-aircraft missile according to the patent for invention No. RU 2327949, which contains a housing, a guidance system with an inertial control system, a receiving unit of the radio correction line and a homing head, combat equipment and a dual-pulse propulsion system, including a dual-mode propulsion system based on solid fuel.

Known patent for utility model No. 93962 "Anti-aircraft guided missile."

The utility model includes a housing, inside which there is a marching jet engine, a fuel source for the jet engine, a warhead for hitting air attack weapons, an autopilot, an onboard power supply and an onboard computer for controlling onboard equipment and missile flight, and the marching jet engine is equipped with a jet nozzle and connected at the supply inlet to a rocket fuel source, and at the exit of rocket fuel combustion products to a rocket nozzle, the main jet engine is made in a plasma-jet engine of pulsed action, a magnetohydrodynamic (MHD) generator mounted on the rocket jet nozzle is used as an onboard power supply, and the fuel source is made in the form of a tank with compressed gas and a pulsed gas metering device for the engine or in the form of a tank with liquefied fuel and spray liquid.

The disadvantage of analogues is the low efficiency of hitting high-speed targets due to the low maximum achievable and supported flight speed.

Closest to the technical nature of the claimed utility model is the domestic anti-aircraft guided missile (SAM) 9M83 of the S-300 V military anti-aircraft complex ("Technique and Armament", No. 5-6, 1999, p. 24), containing the launch and march stages. The marching stage contains a control compartment, including guidance systems, roll stabilization and non-contact detonation, a warhead, aerodynamic controls and a starting and marching solid propellant engine.

The prototype works as follows. After the rocket leaves the transport and launch container with a vertical launch, the operation of the starting engine on solid fuel begins. After dispersal of the missiles, the starting engine is disconnected and the main engine is switched on. At the same time, homing missiles are carried out and upon reaching a predetermined distance to the target, a fragmentation warhead is undermined.

To ensure the interception of high-speed air targets, it is necessary to ensure the acceleration and movement of SAMs at high speeds. A solid fuel engine is characterized by a large mass and dimensions, which hinders the ability to disperse SAMs by the fact that it is necessary to disperse a large mass due to the presence of an oxidizer and fuel in the solid fuel, the drag increases significantly, thereby increasing aerodynamic speed loss. Therefore, movement at high speeds leads to the need to equip SAM with an additional thermal protection system from aerodynamic heating.

The disadvantage of the prototype is the low efficiency when intercepting high-speed targets due to the low speed of 1200 m / s.

The technical problem arising from criticism of the prototype and analogues is to increase the maximum flight speed and maintain it throughout the marching section without violating the integrity of the SAM design under conditions characteristic of high-speed aerodynamic heating.

The specified technical problem is solved in that a high-speed ramjet engine is used as a mid-flight engine, and the fairing and the transition compartment are made of electrically conductive heat-resistant material. In this case, an emission layer (ES) of a material with a low electron work function (RWE) is applied to the surface of the fairing, and a layer of electron perception (SVE) is applied to the surface of the transition compartment, electrically connected in series with each other through an electric power source.

In the claimed utility model for thermal protection, an emission layer of a material with low REE is applied to the fairing. When flying at high speeds, the fairing is heated to temperatures at which thermionic emission begins to occur, that is, electrons begin to come out from the surface of the emission layer and take a large amount of thermal energy with them. The fairing is cooled. The released electrons across the field from the source of electric energy are directed to the SHE, where they are perceived and redirected through the design of the transition compartment, the on-board source of electricity and the fairing to the emission layer. At the same time, the thermal energy received by the emission electrons is dissipated when the fairing is heated, and as a result the “cooled” electrons are returned to the fairing and the cooling cycle is repeated again. This ensures that the temperature of the fairing is maintained at which the durable properties of the fairing are maintained at the required level.

In a similar way, it is possible to protect controls and other heat-stressed elements of missiles.

When replacing a solid propellant solid propellant engine (solid propellant solid propellant propellant engine) with an exhaust air propellant engine, the need for an oxidizing agent on board is eliminated, which reduces the mass and dimensions of the SAM and contributes to a longer maintenance of high speeds to ensure the defeat of high-speed targets.

The inventive utility model is shown in the drawing.

SAM includes in its composition a solid propellant rocket engine (RDTT) 1, launch controls 2, marching high-speed ramjet engine 3, marching controls 4, emission layer 5, fairing 6, electron perception layer 7, transition compartment 8, building 9, control and guidance devices 10, warhead 11, power source 12.

The starting solid propellant rocket engine 1 is intended for the initial high-speed set-up, at which the marching air-propelled air propulsion system 3 is designed to maintain a high flight speed of the SAM. Launching controls 2 and marching controls 4 SAMs are designed to provide control and guidance of missiles to a high-speed target. The emission layer 5 is designed to provide high electron emission during heating of the fairing 6, designed to provide the lowest drag during flight. The transition compartment is designed for mechanical connection of the housing 9, in which there are control and guidance devices 10 and a warhead 11, and the VVRD 3. The layer of perception of electrons 7 is intended for the perception of electrons emitted from the emission layer 5. Control and guidance devices 10 are designed to control and pointing missiles at the target. Warhead 11 is designed to hit a high-speed target when approaching her missiles. The onboard electric power source 12 is intended to create an electric field between the emission layer 5 and the electron perception layer 7, which makes it possible to organize the directed movement of electrons through the flow around the SAM stream from the emission layer 5 to the electron perception layer 7 and through the conductive elements (fairing 6 and transition compartment 8) SAM from the electron perception layer 7 to the emission layer 5.

The inventive utility model works as follows.

At the initial moment of time, the starting solid propellant rocket launcher is activated, which accelerates the missile launcher to high speeds, at which it becomes operational VVRD 3. During the operation of the solid propellant rocket launcher 1, the missile is controlled by the starting controls 2. After the termination of operation of the solid propellant rocket engine 1 it is separated and the marching air guided missile 3 The control of missiles is carried out by means of marching controls 4. Control commands to launch 2 and march 4 controls are provided from control and guidance devices 10. At the same time, at high speeds, the flight and with the marching VREW 3 running, the nose fairing 6 and the emission layer 5 are heated to temperatures at which “hot” electrons start coming out from the surface of the ES 5, taking heat with them and cooling the fairing 6 and ES 5. The “hot” electrons are sent to the SVE 7 along the electric field created by the electric power source 12. When “hot” electrons hit the SVE 7, the electrons are sent to the construction of the transition compartment 8, then through the electric power source 12 and the fairing 6 to the electric power station 5. In this case, the thermal energy received emission of electrons during heating of the fairing 6 and ES 5. As a result, “cooled” electrons return to ES 5 and the cooling cycle is repeated again. When reducing the distance from missiles to high-speed targets, the warhead 11 is undermined.

Thus, the stated technical problem is solved and the technical result is achieved, which consists in increasing the efficiency of hitting high-speed targets by ensuring the achievement and maintenance of the movement of SAMs at high speeds while maintaining its integrity under conditions characteristic of high-speed aerodynamic heating by installing marching VREP and organizing electronic cooling during thermionic emission of a SAM fairing.

Claims (1)

 Antiaircraft guided missile, in the form of a cone-shaped body, with a fairing included in it, a starting propulsion system, a propulsion system, a transition compartment, control and guidance devices, a warhead, launch and marching controls, characterized in that the fairing and transition compartment are made of heat-resistant electrically conductive material, on the surface of which an electrically conductive emission layer and a layer of perception of electrons from materials with a low electron work function are deposited through a closed-circuit electric power source, while a high-speed ramjet engine is installed as a mid-flight propulsion system.

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