RU2410291C1 - Supersonic missile with powdered metallic fuel engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: ultrasonic missile contains the body where there located is guidance system equipment, control system equipment, missile warhead, starting power plant and propulsion power plant. Air-intake devices and aerodynamic surfaces are located outside the body. Propulsion power plant is performed in a form of ramjet engine that consists of pre-combustion chamber and combustion chamber connected to air-intake devices and powdered metallic fuel supply system that uses a piston.

EFFECT: increase of flight range in larger flight altitude envelope.

2 cl, 1 dwg

Description

The invention relates to rocket technology, in particular to rockets equipped with ramjet engines.

Known cruise missile (RF patent No. 2117907 from 08.20.1998, IPC F42B 15/00, F02K 7/18). A cruise missile contains a supersonic engine, in the chamber of which a launch-acceleration stage with a jet engine and an air intake with a central body can be ejected through the nozzle.

The disadvantage of the analogue is not a large flight range.

Known rocket X-31 ("Arms of Russia 2006-2007", Moscow, Military Parade, 2006, p. 689), which is closest to the invention under consideration and selected as a prototype. The X-31 missile is made according to the normal aerodynamic design with

The X-shaped arrangement of the wing consoles and rudders is equipped with a solid-propellant starting engine and a ramjet engine, in which kerosene is used as fuel.

The disadvantage of the prototype is not a large flight range.

The objective of the invention is to increase the flight range by equipping a rocket ramjet engine on a powdered metal fuel.

The problem is solved due to the fact that a supersonic missile contains a housing, guidance system equipment, control system equipment, a warhead, a starting propulsion system, air intake devices, aerodynamic surfaces, a marching propulsion system made in the form of a ramjet engine in powder form metal fuel containing a fuel supply system, a fuel tank, a piston, a preliminary combustion chamber and a final combustion chamber.

In the particular case of the implementation of the technical solution, the problem is solved due to the fact that the starting propulsion system is made in the form of a solid propellant rocket engine and is installed in the propulsion system with the ability to reset.

The present invention allows to increase the flight range while maintaining the mass-dimensional parameters of the rocket, and also allows you to use the rocket in higher layers of the atmosphere by equipping a ramjet engine with powdered metal fuel.

The drawing shows a supersonic rocket in section, side view.

A supersonic rocket with an engine on a powdered metal fuel (hereinafter referred to as a rocket), made according to the normal aerodynamic scheme, comprises a housing 1 with equipment located therein, including guidance system 2 equipment and control system equipment 3, warhead 4, and a propulsion system. On the body there are lateral air intakes 5 and aerodynamic surfaces, such as wings 6 and steering surfaces 7.

The propulsion system comprises a gas generator 8, a fuel supply system, a preliminary combustion chamber 9, a final combustion chamber 10. The fuel supply system comprises a piston 11 mounted for movement under the action of gas coming from the gas generator, and a fuel tank 12. Powder is used as fuel metal fuel, for example, from aluminum. The metal content in the fuel is 100%. The preliminary combustion chamber 9 and the final combustion chamber 10 are connected to the side air intakes 5.

The composition of the rocket includes a starting solid propellant rocket engine 13. The starting solid propellant rocket engine 13 is placed in the final burning chamber 10 of the main propulsion system.

An aircraft is used as a carrier for a rocket (for example, as for the prototype, Su-24M, MiG-29, etc.). The rocket is suspended from the carrier using an ejection device and connected to the carrier systems.

The rocket works as follows.

Reach a certain value of the speed of the medium - the minimum start speed. For the operation of the ramjet engine, it is necessary that after starting, developing and resetting the starting solid propellant rocket engine 13 at the time of the launch of the propulsion system, the flight speed of the rocket reaches the launch speed of the ramjet engine, for example 1.8 M.

Separate the rocket from the carrier using an ejection device. The starting solid propellant rocket engine is started 13. The rocket is accelerated to the speed of starting a ramjet engine, for example 1.8 M. After the fuel is developed, the starting solid propellant rocket engine 13 is reset. The marching propulsion system of the rocket is launched.

The piston 11 is moved under the action of gas from the gas generator 8, the powdered metal fuel is fed into the pre-combustion chamber 9. In the pre-combustion chamber 9, the powdered metal fuel is mixed with the air coming from the side air intakes 5 and ignited. The primary combustion products come from the preliminary combustion chamber 9 to the final combustion chamber 10, where they are mixed with air coming from the side air intakes 5, and the main combustion takes place. On the marching flight section, the rocket speed can vary in the range of 1.8-4 M.

Using the guidance system and control system perform a given flight program of the rocket.

The technical solution relates to rocket technology, in particular to rockets equipped with ramjet engines. Using a technical solution can significantly increase the flight range, as well as expand the range of heights in which the use of a rocket is possible.

Claims (2)

1. A supersonic rocket containing a housing, guidance equipment, control system equipment, warhead, air intake devices, aerodynamic surfaces, a starting propulsion system and a propulsion system made in the form of a ramjet engine, a fuel supply system and a tank with fuel, characterized in that the mid-flight propulsion system comprises a preliminary combustion chamber and a final combustion chamber connected to air intake devices by you, and uses powdered metal fuel, and the fuel supply system contains a piston. 2. The supersonic rocket according to claim 1, characterized in that the starting propulsion system is made in the form of a solid propellant rocket engine and is installed in the propulsion system with a reset possibility.