RU2317922C1 - Aircraft missile complex - Google Patents

Abstract

FIELD: aeronautical and space engineering; aircraft missile complexes with heavy missiles (more than 100 tons in mass) equipped with liquid-propellant engines and launched in air for injection of spacecraft into orbits.

SUBSTANCE: proposed aircraft missile complex includes aircraft, airframe with air-launched missile inside its fuselage, device for mating the launch vehicle with aircraft, systems ensuring their proper functioning and ground transportation and acceleration platform equipped with acceleration engines. Airframe fuselage is separable in construction; it may be separated over horizontal plane. Area of airframe wing may be changed after aircraft takeoff due to availability of separable parts of wing which are equidimensional and symmetrical in pairs relative to longitudinal axis of wing.

EFFECT: increased overall dimensions and launch weight of launch vehicle; increased masses of spacecraft injected into orbits.

3 cl, 1 dwg

Description

The invention relates to the field of aerospace rocket and space technology. It can be used in space-based aviation missile complexes (ARCs), for example, with heavy ballistic missiles (weighing 100 tons or more) equipped, for example, with liquid-propellant rocket engines (LRE) and launched in the air outside the aircraft with the aim of launching spacecraft ( KA), for example, a satellite in orbit.

The analogue of the ARC with a launch vehicle placed outside the fuselage of the aircraft is known, presented in the information issues No. 20, 21, 31, 32, 38-41, 45, 46 of 1988 "Rocket and Space Technology" based on foreign press materials, express information , series 1, publication of the "Central Scientific Research Institute of Mechanical Engineering", Moscow on the ARC with the Pegasus launch vehicle (LV) (USA). The specified analogue, as the closest in technical essence, is taken as a prototype.

The disadvantages of the prototype, including, are:

- limitations on the mass of the launch vehicle and its spacecraft orbital masses (AES);

- low efficiency of using the technical capabilities of the aircraft, for example, in the range of LV delivery to its launch point;

- low safety of the crew and aircraft during the flight of the aircraft to the launch area of the launch vehicle and at its launch.

The tasks to which the invention is directed are, including:

- increasing the efficiency of using the technical capabilities of the aircraft and the ARC as a whole;

- improving the safety of the aircraft and the reliability of rocket launch.

This is achieved, including due to:

- use on a glider wing with a variable area in flight after takeoff;

- use of the aircraft as a towing glider, inside the fuselage of which is placed a booster;

- the use of a ground transportation and booster platform (TRP), which houses a glider equipped with LV.

The invention is illustrated by the drawing, which shows a General view of the placement of the glider with the launch vehicle on the ground TRP, pairing the glider with TRP and with the aircraft, performing the functions of a towing glider.

Glider 1 with RN 2 is located on the ground TRP 3. Glider 1 is connected via a cable-hitch 4 to aircraft 5. The upper part 6 of the fuselage of the glider 2 is configured to separate it from the lower part 7 of the fuselage of the glider 1. At the same time, the upper part 6 of the fuselage of the glider 1 and the cable-fall 5 form a device for interfacing the PH 2 with the aircraft 5, which performs the functions of a towing aircraft.

To ensure the functioning of TRP 3, glider 1 and their systems TRP 3 and glider 1 are equipped with control systems (not shown in the drawing).

To the central part of the wing 8 of the glider 1, to zone A, in which the ailerons 9 are installed, the bearing parts of the wing 8, for example, six pieces, are mounted. These are areas of equal size and symmetrically located relative to the longitudinal axis of the wing 8 of the glider 1, two parts 10 are the consoles of the wing 8, two parts 11 are central for the right and left wings, two parts 12 are adjacent to zone A of the wing 8.

This system: a glider 1 equipped with a PH 2, a plane 5 TRP 3 and a cable-rope 4, operates as follows.

Before launching the spacecraft, the TRP 3 is fed to the technical position of the aviation missile system, where it is loaded with a glider 1 equipped with PH 2, for example, with uncharged fuel components. The loading of the PH 2 is ensured by the possibility of connecting the fuselage of the glider 1 along the horizontal plane B into two parts: the lower part 7, the upper part 6.

After loading the glider 2 on the TRP 3, the PH 2 is refueled and the PH 2 systems, as well as the TRP 3 systems are checked.

After completing all the work on preparing the aviation missile system for launching the spacecraft (including glider 1, aircraft 5, RN 2, TRP 3), the equipped TRP 3 is towed to the runway (runway) 13, from which take-off and take-off take place 5 and TRP movement 3.

On runway 13, the aircraft 5 is engaged with the glider 1 using the tow rope-hitch 4. As a result, aircraft 5 and TRP 3 are brought to the starting position on runway 13.

The functioning of the complex is carried out in the following sequence.

On command from the ARC control system, the engines are launched simultaneously on aircraft 5 and TRP 3 to take off to the launch site of the launch vehicle (engines 14 are installed on it to disperse the TRP). The thrust of the aircraft engines 5 and TRP 3 provide equal acceleration when moving along the runway 13.

Upon reaching the specified thrust levels of the engines of the towing aircraft 5 and TRP 3, a take-off command is sent from the ARC control system (the start of their movement along runway 13).

This ensures the levels of the thrust of the engines of the aircraft 5 and TRP 3, eliminating the sagging of the cable-hitch 4 to an unacceptable level.

When aircraft 5 and TRP 3 are moving along runway 13, lift forces act on plane 5 and glider 1, which ensure separation of plane 5 from runway 13 and glider 1 from TRP 3 when the set speed is reached (~ 280-300 km / h).

After the separation of the aircraft 5 from the runway 13 at the same time from the TRP 3, on command from the ARC control system, separation of the loaded LV 2 of the glider 1 and the start of the flight of the aircraft 5 to the launch area of the launch vehicle 2 are carried out in order to launch the spacecraft. At the same time, during the flight of the aircraft 5 with the towed glider 1 to the launch area of the PH 2, the lifting force and drag of the wing 8 are regulated by separating the parts 10, 11, 12 from it by command from the control system of the PH 2 or glider 1 (i.e. by changing the area of the wing 8) by using, for example, elongated detonating charges placed along the perimeters of the wing profiles of 8 parts 10, 11, 12 (not shown in the drawing).

Upon arrival of aircraft 5 in the launch area of PH 2, plane 5 and glider 1 occupy the specified design positions in space in height, direction and flight speed, angular parameters (roll, pitch, course), ensuring launch of PH 2.

On command from the ARC control system to launch RN 2, the lower part 7 of the fuselage of the glider 1 is separated, for example, along the horizontal plane B (for example, by using the pyro locks and detonating cords mounted on the fuselage of the glider 1, not shown in the drawing) and after it compartment, a command is sent from the ARC control system to the PH 2 compartment from the upper part 6 of the fuselage of the airframe 1 and the launch of its I stage engines. The PH 2 is separated from the upper part 6 of the fuselage of the glider 1 under the action of gravity (i.e., falls), and the glider 1 (upper part 6) due to the presence of the lifting force created by the wing 8, rises. After separation of the launch vehicle 2 from the upper part 6 of the glider 1 and the launch of its engine of the first stage, the flight of the launch vehicle 2 is carried out according to a given program and the spacecraft is put into a given orbit.

Thus, the above technical appearance of the ARC with new distinctive features, in comparison with the prototype, allows, including:

- increase the effectiveness of the ARC;

- increase the safety and reliability of the ARC;

- reduce technical and other risks during the creation of the ARC and its operation.

The technical solution proposed in the invention opens up a promising direction for the development of the ARC.

Claims (3)

1. Aircraft missile system, including an airplane, an air launch launcher, a device for interfacing a launch vehicle with an aircraft that acts as a towing system for their operation, characterized in that it contains a glider, inside of the fuselage of which there is a launch vehicle, cable , a ground transport and booster platform equipped with engines, on which a glider is mounted, in which the lower part of the fuselage is configured to separate it from the upper part of the fuselage down, while between themselves, the cable and the upper part of the glider fuselage form a device for interfacing the launch vehicle with the aircraft, and the airframe wing is made with the possibility of changing its area, to the central part of which separate carrier parts of the wing are attached, pairwise equal and symmetrically located relative to the longitudinal axis of the wing, connected among themselves with the possibility of separating them from the wing of the glider. 2. The aviation missile system according to claim 1, characterized in that the ground transport and booster platform is equipped with a control system. 3. The aviation missile system according to claim 1, characterized in that the airframe is equipped with elements of airframe control systems, launch vehicles and their power supply, for example, batteries.