RU2705387C1 - Method of rocket launching from wide-body carrier - Google Patents

Abstract

FIELD: astronautics.

SUBSTANCE: invention relates to space engineering, particularly, to start-up units. With rocket launching from wide-body carrier is started from container arranged on carrier, and measures for unstressed extension of missile. Measures involve application of group action deflector arranged on carrier in area of launcher and use of gas-dynamic system of transverse stabilization and declination.

EFFECT: enabling the design simplification.

1 cl, 1 dwg

Description

FIELD OF THE INVENTION

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

State of the art

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 closest in essence to the present invention and which has an inherent set of features closest to the set of essential features of the present invention, the method proposed in US Patent No. 2012/0024136 A1, date is considered. Publications 02.02.2012.

The proposed method of missile air launch involves launching a rocket using a rocket propulsion engine from a launch tube placed vertically (or almost vertically) in the fuselage of the aircraft, 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 ambient 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;

- a system for 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:

- 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 vibration conditions onnyh alternating loads caused by air vortices Carnot, flowing around the cylindrical body;

- the presence on the rocket of special pads for the movement of the rocket on the launcher slide-out 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 use of a group action deflector placed on a carrier in the vicinity of the launcher to reduce the level of lateral aerodynamic loading immediately on all launch rockets;

- the use of a gas-dynamic system of lateral stabilization and declination on the rocket to counter the uneven aerodynamic effects of the turbulent air flow behind the group-effect deflector, which ensures coaxial shock-free exit of the rocket from the launch container (launch tube);

- delayed launch of a rocket relative to the issuance of a command to open fire for a time sufficient to open the group action deflector;

- delayed start of the gas-dynamic system of lateral stabilization and rocket inclination relative to the moment of rocket launch for a time sufficient for the nozzle apparatus of the gas-dynamic transverse stabilization system and rocket inclination from the launch container to the air.

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

- the use of 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 flexural rigidity;

- additional strengthening of the design of the rails for advancing on them an individual deflector expandable design;

- the use of powerful rocket engines ("gas burners") on the body of the carrier or deflector, creating a vertical gas barrier to the incoming air flow;

- increasing the strength and shape stability of the carrier for mounting the system of retractable starting sliding guide rails with a deflector and gas burners attached to them.

The implementation of the invention

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

- gas-dynamic missile control system (lateral stabilization and declination system) - “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. 167, 345 ... 352;

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 missile is delayed relative to the issuance of a command to open fire for a time sufficient to open the group action deflector;

- the launch of the gas-dynamic system of lateral stabilization and rocket inclination is delayed relative to the moment of rocket launch for a time sufficient for the nozzle apparatus of the gas-dynamic transverse stabilization system and rocket inclination from the launch container to air.

An example embodiment of the invention is shown in the diagram of a device that implements the proposed method of launching a rocket from a wide-body carrier, where the numbers denote:

1. The deflector on the carrier body, which reduces the aerodynamic loading of the starting rocket with a free-stream.

2. Rocket launch system.

3. The engine transverse gasdynamic control and declination of the rocket, providing parry uneven aerodynamic effects of turbulent air flow behind the deflector.

Claims (1)

A method for launching a rocket from a wide-body carrier, based on the vertical launch of a rocket from a launch container placed on the carrier, including measures to ensure unstressed coaxial extension of the rocket into the incoming air stream, characterized in that a group action deflector is used, which is placed on the carrier in the region of the rocket launcher , and a gas-dynamic stabilization and declination system mounted on a rocket.

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