RU2619361C2 - Supersonic aircraft and method for flight thereof - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: group of inventions relates to controlled strategic weapons, particularly to supersonic aircraft and methods for implementation of flight thereof. Supersonic aircraft includes starting engine with stage separation mechanism, sustainer stage with an airframe and with functional units. Sustainer stage is placed in protective fairing, expanding during separation of engine. Airframe of sustainer is made on a low-winged aircraft scheme with elements of vertical tail, providing banking stability of airframe. Tail is pre-deformed by a protective fairing. Method of flying supersonic aircraft comprises using programmable ricochet amplitude. At stage of immersion into atmosphere change of aerodynamic force vector is performed by selecting optimum angle of attack. Aircraft start is performed at path angle from 50 to 85° to horizon. Aircraft is taken along a ballistic trajectory into rarefied atmosphere at altitude from 50 to 70 km.

EFFECT: reduced aerodynamic loads.

2 cl, 2 dwg

Description

Technical field

The proposed group of inventions relates to military equipment, to long-range systems of guided weapons and rocket technology, in particular, can be used in supersonic weapons systems.

Currently, work is underway to develop hypersonic and supersonic aircraft (LA), which have high combat capabilities due to the short flight time to the target and low vulnerability for modern missile defense systems.

State of the art

A well-known hypersonic aerospace aircraft made according to the “flying wing” scheme, integrated with the fuselage, with double swept plumage and control wheels, with a heat-protective coating applied to its surface, in which the wing is made with great sweep, and the fuselage has a spindle-shaped shape and is located in the shadow aerodynamic zone of the wing, the leading edges of the nose of the fuselage, wing and vertical tail are made blunt, RF patent No. 2393978, publication July 10, 2010, bulletin No. 19.

Known aircraft containing a starting engine with a stage separation mechanism, a marching stage with functional blocks, adopted as a prototype, RF patent No. 2184343, publication 06/27/2002, bulletin No. 18.

There is a method for implementing a flight of a hypersonic aerospace aircraft, in which at a given initial speed, flight altitude and throw angle, a programmable ricocheting amplitude is used, while at the stage of immersion in the atmosphere, the change in the aerodynamic force vector is carried out by choosing the optimal angle of attack corresponding to the maximum flight range of the vehicle, RF patent No. 2393978, publication 07/10/2010, Bulletin No. 19.

The use of a starting engine with a stage separation mechanism in the aircraft design allows the aircraft to be launched at a long range without a carrier aircraft. However, the flight is carried out without the withdrawal of the aircraft to the upper atmosphere and the design of this aircraft does not provide protection from kinetic heating of the surface that occurs at the required speed and range.

Achieving the required range and speed of the aircraft involves the implementation of the flight of the aircraft outside the dense layers of the atmosphere. To implement this method of flight of a hypersonic aerospace aircraft, it is necessary to use a carrier aircraft, which greatly complicates and increases the cost of such flights. When a hypersonic aerospace aircraft is launched from a ground-based launcher, significant kinetic heating occurs at the launch site of the flight, and protection from it by a heat-shielding coating applied to the aircraft surface is not provided.

Disclosure of invention

The objective of the proposed group of inventions is to eliminate the above disadvantages, namely reducing aerodynamic loads and thermal effects on the trajectory, providing supersonic speeds of the aircraft and long-range flight, stealth for detection tools, ease of implementation at optimal price characteristics.

In a supersonic aircraft containing a launch engine with a stage separation mechanism, a marching stage with functional blocks, the task is achieved by the fact that the marching stage is placed in a protective cowl, which opens when the starting engine is separated, and the marching stage glider is made according to the low-wing airplane scheme with elements vertical plumage, ensuring the stability of the airframe along the roll, awkward with a protective fairing and moving into working position when it opens.

In a method for realizing a flight of a supersonic aircraft using a programmable ricocheting amplitude, at the stage of immersion into the atmosphere, the aerodynamic force vector is changed by choosing the optimal angle of attack corresponding to the maximum range of the aircraft, the task is achieved by launching the aircraft with ground launcher at a trajectory angle of from 50 to 85 ° to the horizon and the aircraft take the ballistic trajectory into the rarefied layers of the atmosphere EASURES at a height of 50 to 70 km.

The technical result is ensured due to the fact that in a supersonic aircraft the marching stage is placed in a protective cowl, which opens when the starting engine is separated, and the marching stage glider is made according to the “low-wing” airplane scheme with vertical tail elements that ensure the glider’s stability along with the roll, which are not lazy with the protective cowl and moving into working position when it is opened.

The technical result is also provided due to the fact that in the method of implementing a flight of a supersonic aircraft, the aircraft is launched from the ground launcher at a trajectory angle of 50 to 85 ° to the horizon and the aircraft are driven along a ballistic trajectory into rarefied layers of the atmosphere at heights of 50 to 70 km .

This technical solution is illustrated by graphic materials.

 In FIG. 1 and FIG. 2 schematically shows the appearance of the aircraft and the marching stages of a supersonic aircraft, respectively,

where 1 is a protective fairing;

2 - vertical plumage;

3 - march stage with functional blocks;

4 - stage separation mechanism;

5 - starting engine;

6 - block stabilizers;

7 - the case of the march stage;

8 - wing;

9 - steering wheels.

Supersonic aircraft, in accordance with FIG. 1, is made bicaliber and consists of a marching stage equipped with functional blocks, a detachable starting engine and fairing. This scheme allows you to ensure minimum weight and size characteristics and increase flight range, launch from a ground launcher.

The marching stage 3 is joined to the starting engine 5 by means of a transition compartment with a separation mechanism 4, which ensures the forced separation of the starting engine 5 at the end of the active portion of the flight of the aircraft. On the nozzle block of the starting engine, a block of stabilizers 6 is installed, designed to give the aircraft longitudinal stability at the launch site of the flight. The stabilizers are made folding in the caliber corresponding to this aircraft and are four blades. Each blade by means of an axis is pivotally connected to a housing fixedly mounted on the nozzle block of the starting engine.

In FIG. 2 shows the march stage 3, equipped with functional blocks. The marching stage is made according to the “low-wing” airplane scheme with vertical tail elements 2 of wing 8, which ensure the glider stability along the roll, are lazy with the protective fairing 1 and go into working position when it is opened. The wing 8 is integrated into the main body of the march stage 7. To ensure a controlled flight, the rudders are located in the rear part of the march stage 9. The selected aerodynamic design allows achieving aerodynamic quality K = 5.5-6.0.

To ensure the secrecy and suddenness of delivering a high-precision strike at a long range from the line of contact with the enemy, a firing position with a launcher equipped with a supersonic aircraft is located.

The greatest firing range is provided by withdrawing in the initial portion of the aircraft trajectory to the maximum possible atmospheric flight altitude, and in the middle portion of the trajectory by maintaining the aircraft at flight altitude, where the aircraft’s speed loss is minimal: above dense atmospheric layers. To do this, when preparing the aircraft for launching the guns in the control panel, when obtaining the coordinates of the target, they calculate the ballistic firing settings and formulate a programmed flight mission for the aircraft, in which they determine the trajectory with flight in the stratosphere (from 15 to 70 km) that ricochets from it lower layers (from 15 to 20 km) with characteristic sections:

- ballistic - to the maximum flight altitude;

- basic, - characterized by flight with a maximum coefficient of aerodynamic quality;

- final - pointing and diving at the target.

To implement the first ballistic section of the flight path, the aircraft is launched from the ground launcher at a high trajectory angle from 50 to 85 ° to the horizon and the aircraft is driven along the ballistic path into rarefied layers of the atmosphere at heights of 50 to 70 km.

After the aircraft leaves the container, the blades of the stabilizer block 6 are opened and fixed. In order to reduce aerodynamic loads and thermal effects, a protective fairing is used in the initial section of the trajectory 1. At the end of the starting engine 5, the protective fairing 1 opening mechanism and the separation mechanism are triggered by the control system command steps 4. After separation, the marching step 3 continues the flight to the target along the programmed path.

Functional blocks of the march stage transfer flight control to the program for the middle section of the trajectory and form control commands on the aircraft's steering wheels. At the stage of immersion in the atmosphere, the change in the aerodynamic force vector is carried out by choosing the optimal angle of attack corresponding to the achievement of the maximum flight range of the device, similar to RF patent No. 2393978, publication July 10, 2010, bulletin No. 19.

When approaching the target, according to the flight task, the flight of the aircraft takes place in homing mode, which provides high-precision guidance of the aircraft to the target.

To implement the proposed method, the following devices can be used. PU with guidance drives can be performed, for example, similarly used in the anti-aircraft missile-cannon complex, RF patent No. 2321818, publication 10.04.2008, bulletin No. 10. Functional blocks of the march stage can be performed, for example, similarly contained in LA, RF patent No. 2184343, publication 06/27/2002, bulletin No. 18.

Thus, the use of the proposed supersonic aircraft and a method for implementing the flight of a supersonic aircraft allows to meet the requirements for modern weapons and to reduce aerodynamic loads and thermal effects on the aircraft on the trajectory, to launch the aircraft at a supersonic speed over a long range, stealth weapons for detection means, ease of implementation with optimal price characteristics.

Claims (2)

1. A supersonic aircraft containing a starting engine with a stage separation mechanism, a marching stage with functional blocks, characterized in that the marching stage is placed in a protective cowl that opens when the engine is separated, and the marching stage glider is made according to the low-wing airplane scheme with vertical elements plumage, ensuring the stability of the glider roll, laden with a protective fairing and moving into working position when it is opened. 2. A method for implementing a flight of a supersonic aircraft using a programmable ricocheting amplitude, while at the stage of immersion in the atmosphere, the change in the aerodynamic force vector is carried out by choosing the optimal angle of attack corresponding to the maximum range of the aircraft, characterized in that the aircraft is launched ground launcher at a trajectory angle of from 50 to 85 ° to the horizon, and the aircraft is displayed along a ballistic trajectory in the section layers of the atmosphere at heights of 50 to 70 km.

Images