RU2722633C1 - Vertical air missile launching method - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: invention relates to aerospace engineering, particularly, to rocket launching. Proposed method comprises vertical launching of rocket from launching container arranged on air carrier. "Cold" start of the missile is used with the help of a catapulting or obturator device. Delayed start of gas-dynamic system of transverse stabilization and declination of missile for time sufficient for output of nozzle device of gas-dynamic transverse system of stabilization and declination of missile from launching container into air. Delayed launching of sustainer rocket engine.EFFECT: simplified design of carrier.1 cl, 1 dwg

Description

The technical field to which the invention relates.

The invention relates to methods for launching missiles from an airborne carrier and may find application for launching guided missiles, anti-missiles and ballistic missiles.

The level of technology.

1) Known analogues of the invention having a purpose that coincides with the purpose of the invention: methods of launching missiles intended for use on air carriers:

- A method of putting payload into near-Earth space using an aircraft rocket and space complex and an aircraft rocket and space complex, RF Patent No. 2265558, B64G 1/00, publication date: September 6, 2005;

- Method for launching a multi-stage space launch vehicle using a carrier aircraft and multi-stage launch vehicle, RF Patent No. 2265559, B64G 1/00, publication date: 09/06/2005.

A common drawback of these inventions, in our opinion, is the placement and launch of missiles coaxially with the carrier axis of the carrier, which either limits the angle of the missile’s throwing, or forces the aircraft to perform a cabling maneuver to launch the missile, which causes a drop in the velocity of the missile’s throwing at the moment of uncoupling and reduces Thus, the effect of applying an air start.

As a prototype of the invention, which is closest in essence to the invention and which has a set of features that is closest to the set of essential features of the invention, the method proposed in US Patent No. 2012/0024136 A1, date is considered. Publications - 02.02.2012.

The proposed method for air launching of missiles involves launching a rocket using a rocket from a launch tube placed vertically (or almost vertically) in the fuselage of the aircraft to start the mid-flight engine, and further includes:

- self-aligning starting sliding guide rails with a mechanical limiter on one side, along which a block attached to the rocket moves and moves along the remaining rail length until the rocket leaves the aircraft, thereby eliminating lateral vibrations (vibrations) of the launching rocket;

- a deflector in each launch tube attached to the launch sliding guide rails and extendable together with the guide rails, providing a deviation of the surrounding air flow around the rocket, until the rocket is disconnected from the guide rails after exiting the launch tube;

- engines or hydraulic actuators providing expansion of the deflector during rocket launch;

- high-speed gas burners mounted on a carrier or on the upper part of the deflector, providing an extension of the protected starting zone in height;

- returning the rails and deflector back to the launch tube, turning off the gas burners, which reduces the lateral loading of the carrier and the resulting tipping forces acting on the carrier.

According to the developers of this method, an airborne missile-based method using vertical (or almost vertical) missile launch provides all-round target firing and is an effective measure for organizing air defense and missile defense, launching shock ballistic and aeroballistic missiles in offensive ground operations, installing minefields, satellite launch, etc.

2) Technical problem. The main problem of providing a vertical (or almost vertical) launch from a moving carrier is the strong aerodynamic effect of the incoming air flow on the side surface of the rocket, which prevents the shockless exit of the rocket from the fuselage of the carrier, a significant moment of the rotation of the rocket in the pitch plane when leaving the carrier body with uneven impact of the incoming flow air. The method (method) proposed by the prototype offers a solution to this problem, however, the proposed solution has significant drawbacks, the main of which are:

- “hot” launch of the rocket on its own engine, requiring the use of a through hole in the carrier for launching rockets from the launch tube and the need for substantial strengthening of the carrier body, as well as thermal protection of the launch tube and upper surface of the carrier from the action of a high-temperature gas jet of the launch rocket engine, the inability to launch rockets when the carrier moves at low altitude due to the interceptor action of the gas jet of the launching rocket on the carrier body, causing the carrier to dive, which at low altitude leads to a collision with the ground;

- the presence in the launch tube of a system of extendable launch sliding guide rails to ensure coaxial shockless extension of the rocket from the launch tube, which limit the space for opening the aerodynamic surfaces of the rocket and require significant reinforcement of the carrier body and the guides themselves to hold the mass of the rocket in combination with the mass of the deflector attached to to rails, as well as to counter significant lateral aerodynamic loading of the rocket-rails-deflector complex under conditions of alternating vibrational loads caused by Carnot air vortices flowing around a cylindrical body;

- the presence on the rocket of special pads for the movement of the rocket on the launcher sliding sliding guide rails of the launcher, increasing its mass and aerodynamic drag in flight.

Disclosure of the invention.

The essence of the proposed method of vertical air launch of a rocket from the side of the carrier is alternative to the well-known solution of the same purpose (US patent No. US 2012/0024136 A1) and provides a solution to the same problem and achieve the same technical result with simpler technical means. The proposed technical solution is based on the use of a new set of essential features sufficient to realize the purpose of the invention:

- the implementation of the "cold" launch of the rocket using a catapult or obturator device from the launch container (launch tube);

- the use of a gas-dynamic system of lateral stabilization and declination on the rocket to counter the aerodynamic effects of the incoming air flow and the moment of rotation of the rocket in the pitch plane when leaving the carrier body and, thus, ensuring coaxial shock-free rocket exit from the launch container (launch tube).

- delayed launch of the gas-dynamic system of lateral stabilization and rocket inclination relative to the moment of operation of the gas generator of the ejection device for a time sufficient for the nozzle apparatus of the gas-dynamic transverse stabilization system and rocket inclination from the launch container to air;

- delayed launch of the rocket propulsion engine for a time sufficient for the rocket to take off to a height safe for the carrier;

The technical result (effect of application) of the proposed method is:

- there is no need to take measures to ensure thermal protection of the launch tube (container) and the upper surface of the carrier;

- there is no need to take measures to increase the strength and shape stability of the carrier when using a through pipe to launch missiles and a rail system for unstressed output of a rocket into the air;

- ensuring the safe launch of the rocket from the carrier’s side even in the parking lot (airfield, basing place) without running;

- the absence of the need to use a complex design of extendable starting sliding guide rails to ensure coaxial shockless rocket movement when leaving the launch tube, requiring a complex design and technological solution to ensure their strength and bending stiffness;

- the absence of the need to further strengthen the design of the rails for advancing on them an individual deflector expandable design;

- no need to use powerful rocket engines ("gas burners") on the carrier or deflector housing, creating a vertical gas barrier to the incoming air flow.

The implementation of the invention.

For the implementation of the invention, means may be used that are known prior to the priority date of the invention and are widely used in the construction of missile launch containers and the design of missile control systems:

- a system of “cold” launch of a rocket using a catapult or obturator device from a launch container (launch tube) - “Physical Foundations of the Design and Functioning of Small Arms and Missile Weapons”, Part II, study guide for university students, ed. prof. V.V. Vetrova and prof. V.P. Strogaleva, TulSU publishing house, Tula, 2007, p. 483;

- gas-dynamic missile control system (momentary system of declination and stabilization of the angular position) - “Physical fundamentals of the device and functioning of small arms and missile weapons”, Part II, study guide for university students, ed. prof. V.V. Vetrova and pr. V.P. Strogaleva, TulSU publishing house, Tula, 2007, p. 167, 345 ... 352;

- the ignition system of the marching (starting) engine - “Physical Foundations of the Design and Functioning of Small Arms and Missile Weapons”, Part II, study guide for university students, ed. prof. V.V. Vetrova and prof. V.P. Strogaleva, TulSU publishing house, Tula, 2007, p. 244 ... 248;

For the proper implementation of the invention, the correct sequence of the means necessary for the implementation of the invention must be observed:

the launch of the gas-dynamic system of lateral stabilization and declination of the rocket is delayed relative to the moment the gas-generator of the ejection device is triggered for a time sufficient for the nozzle apparatus of the gas-dynamic transverse stabilization system and to incline the rocket from the launch container into the air;

the launch of the main engine of the rocket is delayed relative to the moment of operation of the gas generator of the ejection device for a time sufficient for the rocket to take off to a height safe for the carrier.

An example embodiment of the invention is shown in the diagram of a device that implements the proposed method of vertical air launch of missiles, where the numbers denote:

1. The media body.

2. Free air flow.

3. Gas generator (pneumocylinder, powder pressure accumulator, etc.) of the system of the "cold" launch of the rocket.

4. An obturator (ejection device) of the “cold” start system, which throws a rocket into the air stream under the action of gas generator gases.

5. The engine transverse gasdynamic control and declination of the rocket, providing parry aerodynamic loading of the launch rocket with an incoming air flow.

Claims (1)

A method of vertical air launch of missiles, based on the vertical launch of a rocket from a launch container placed on an air carrier, characterized in that they use a "cold" launch of a rocket using a catapult or obturator device, delaying the start of a gas-dynamic lateral stabilization system and rocket incline for a time sufficient for the exit of the nozzle apparatus of the gas-dynamic transverse stabilization system and the rocket inclination from the launch container into the air, and the delay in launching the rocket propulsion engine.

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