RU2317920C1 - Aircraft missile complex - Google Patents

Abstract

FIELD: aeronautical and space engineering; space aircraft missile complexes.

SUBSTANCE: invention deals with heavy ballistic missiles (more than 100 tons in mass) equipped with liquid-propellant engines and launched in air for injection of spacecraft into orbits. Proposed aircraft missile complex includes aircraft, launch vehicle, device for mating the launch vehicle with aircraft used as towing vehicle, systems ensuring their proper functioning and ground transportation and acceleration platform equipped with acceleration engines. Mounted additionally on launch vehicle body are fairing with wing mounted on it and nose and tail fairings. Stabilizer and vertical tail unit are mounted on tail fairing. Fairings may be separated from launch vehicle. Area of launch vehicle wing may be changed after aircraft takeoff due to availability of separately attached parts of wing which are equidimensional and symmetrical relative to longitudinal axis of wing; they are interconnected and may be separated with the aid of detonating elongated charges located over perimeter of separable parts of wing.

EFFECT: increased flight range and altitude due to reduced mass and drag of wing; increased mass 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 aeronautical missile complexes (ARC) for space purposes, mainly with heavy ballistic missiles (weighing 100 tons or more), equipped with, for example, liquid rocket engines (LRE) and launched in the air to launch spacecraft (SC), for example , Satellite in orbit.

The analogue of the ARC with a launch rocket 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, edition "Central Scientific Research Institute of Mechanical Engineering", Moscow, on the ARC with a Pegasus launcher (LV) (USA). The specified analogue, as the closest in technical essence, is taken as a prototype.

The disadvantages of the prototype are including:

- restrictions on the maximum mass of the launch vehicle and its spacecraft orbits;

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

The tasks to which this application for an invention is directed, including the following:

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

- improving the safety of the crew of the aircraft, the aircraft and its reliability during flight to the launch point of the launch vehicle and at its launch.

This is achieved, including due to:

- execution of the LV wing with a variable area when it is towed by an airplane to the launch point;

- reducing drag and excess lift generated by the launch vehicle wing when towing it to the launch point;

- the possibility of increasing the range and flight altitude of aircraft with a towed launch vehicle by reducing the weight and drag of its wing and, as a consequence, increasing the mass of spacecraft launched into orbits;

- application of the ground transportation and booster platform (TRP).

The invention is illustrated in Fig.1-3, which shows a General view of the placement of the PH on the ground transport and boarding platform and its interface with the aircraft, performing the functions of the aircraft towing the PH.

RN 1 with additional fairing 2 mounted on its body, on which a wing 3 with ailerons 4 is mounted, front (nose) 5 and tail 6 fairings are located on the ground TRP 7. Wing 3 is mounted on the RN 1 body through its center section 8, the cable-rope 9 is associated with the center section 8 of wing 3 of PH 1 and aircraft 10. Aircraft 10 performs the functions of a towing aircraft.

The front fairing 5 and the tail fairing 6 are mounted on the front and tail parts of the pH 1, respectively. Stabilizing surfaces are mounted on the tail fairing 6, forming a controlled stabilizer 11 and a vertical tail unit 12. The wing 3 is equipped with ailerons 4, the stabilizer 11 is equipped with elevators 13, and the tail 12 is equipped with rudders 14. In wing 3 and its center section 8, in fairings 2 , 5, 6, if necessary, cavities can be made for placing elements of control systems PH1, wing 3, stabilizer 11, for example, vertical tail unit 12, other systems that ensure the functioning of the ARC, for example, power supply (not shown ).

To the central part of the wing 3, to zone B, in which the ailerons 4 are installed, the bearing parts of the wing 3 are attached, for example, six pieces pairwise equal and symmetrically located relative to the longitudinal axis of the wing 3. These two parts 15 are the consoles of the wing 3, two parts 16 are central to the right and left wings, two parts 17 are adjacent to zone B of wing 3.

Parts 15, 16, 17 are separated after take-off of aircraft 10 when towing PH1. This achieves the regulation of the values of the lifting force of the wing 3 and the reduction of the drag of the wing 3 mounted on the body of the PH 1, when flying into the launch zone.

The separation of parts 15, 16, 17 from the wing 3 is carried out on command from the control system of the PH 1 sequentially in pairs: first two parts 15, then two parts 16 and two parts 17, for example, using elongated detonating charges placed around the perimeters of the profiles of parts 15, 16, 17 of wing 3 (not shown in the drawing).

The interconnected cable-fall 9, wing 2, center wing 8 of wing 3, fairing 2 of wing 3 form a device for pairing PH1 with aircraft 10, which acts as a towing vehicle.

This system, including the launch vehicle 1, wing 3 and other aforementioned elements, operates as follows.

Before launching the spacecraft, the TRP 7 is fed to the technical position of the aviation missile complex, where it is loaded with an equipped launch vehicle 1, for example, not charged with fuel components with the above-mentioned elements mounted on it.

After loading the equipped RN 1 to the TRP 7, the PH 1 is refueled and its systems, as well as the TRP 7 systems are checked for operation.

After completing all the work on preparing the aviation missile system for launching the spacecraft, the equipped TRP 7 is towed to the runway 18 to the starting point of the TRP 7 when take off aircraft 10 to launch RN 1, where the aircraft 10 is coupled with the wing center section 8 3 PH 1 with the help of a cable-rope (TF) 9. As a result, aircraft 10 and TRP 7 are brought to the starting position on runway 18.

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

At the command of the ARC control system, the engines are launched on the aircraft 10 and TRP 7 to take off to the launch area of launch vehicle 1 (engines 19 are installed on it to disperse the TRP 7). The thrust of the aircraft engines 10 and TRP 7 provide equal acceleration when moving along runway 18.

Upon reaching the specified levels of engine thrusts of the towing aircraft 10 and TRP 7, a take-off command is issued (the start of their movement along runway 18).

At the same time, the thrust levels of the aircraft engines 10 and TRP 7 are provided, excluding the sagging of the cable-rope 9 to an unacceptable level.

During the movement of aircraft 10 and TRP 7 along runway 18, lift forces act on planes 10 and curb launcher 1, which ensure separation of airplane 10 from runway 18 and curb PH 1 from TRP 7 when the desired speed is reached (~ 280-300 km / hour).

When the aircraft 10 is separated from runway 18 at the same time from TRP 7, the equipped RN 1 is separated on command from the RN 1 control system (TRP 7) and the flight of aircraft 10 starts to the launch area of RN 1.

At the same time, during the flight of the aircraft 10 from the launch vehicle 1 to the launch area, the lifting force and drag of the wing 3 are regulated by separating parts 15, 16, 17 from it by commands from the control system PH1.

Upon arrival of the aircraft 10 in the launch area, the aircraft 10 and the loaded PH 1 occupy the specified design positions in space in height, direction and flight speed, angular parameters (roll, pitch, course), ensuring the launch of PH 1.

On command from the ARC control system to launch the launch vehicle 1, commands are issued to start the engine of the first stage of the launch vehicle 1, the separation of the cowls 2, 5, 6 from the housing of the launch vehicle 1, for example, by using pyro locks and detonating cords placed on these detachable elements (on the drawing is not shown) for the destruction of their power relations with the pH 1.

After separation from the body of the launch vehicle 1 of all the above-mentioned parts mounted on it and starting the engine of the first stage, it is flown 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, including allows you to:

- increase the efficiency of the ARC, including increasing the masses of the spacecraft launched into orbits or the altitudes of their orbits, expanding the launch areas of missiles relative to the locations of the ARC

- increase the safety of the crew and aircraft, the 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. Aviation missile system, including an airplane, an air launch launcher, a device for interfacing a launch vehicle with an airplane, systems for ensuring their operation, characterized in that it comprises a cable tether, a ground transport and booster platform equipped with engines, on which it is mounted a booster rocket, additionally mounted on the body of the booster rocket, on which a wing with a center wing is mounted, equipped with ailerons, nose and tail fairings, on which are stabilized surfaces forming a controlled stabilizer and, for example, vertical tail, all fairings are made with the possibility of separation from the body of the launch vehicle, while the mating cable, wing, center wing and its fairing form a device for interfacing the launch vehicle with the plane, and the wing of the launch vehicle is made with the possibility of changing its area, to the central part of which are attached the individual bearing parts of the wing, pairwise equal and symmetrically located relative to Aulnay axis wing interconnected with the possibility of separation, e.g., using elongated detonating charges placed along the perimeter profiles detachable carrying portions of the wing. 2. The aviation missile system according to claim 1, characterized in that in the cavities mounted on the carrier rocket of the nose and tail fairings, the fairing of the wing and its center section there are elements of the control systems of the launch vehicle, wing, stabilizing surfaces and their power supply, for example, electric accumulators . 3. The aviation missile system according to claim 1, characterized in that the ground transport and booster platform is equipped with a control system.

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