RU2355602C2 - Aerospace rocket complex - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aerospace engineering and can be incorporated with aerospace vehicles equipped with liquid propellant engines and launched from aboard the aircraft to place a spacecraft into orbit. The proposed complex comprises an aircraft, wingless rocket-carrier, rocket-carrier-to-aircraft coupling assembly, systems maintaining the complex serviceability and a surface transport-and-boosting platform furnished with engines. Note that the rocket-carrier accommodates additionally a fairing with a wing, nose and tail cones, the latter being furnished with a fin and vertical unit. Aforesaid cones can be separated from the rocket-carrier body. Integrated strap cord, wing, center wing and its fairing make a rocket-carrier-to-aircraft coupling assembly.

EFFECT: larger sizes and weight of rocket-carrier and, hence, increased weight of space apparatuses to be place into orbit.

3 cl, 3 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, 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 are, including:

- restrictions on the maximum mass of the LV launched by it into the orbits of the masses of the spacecraft;

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

The tasks to which the application for the invention is directed are:

- 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, its reliability during flight to the launch point of the launch vehicle and at its launch;

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

This is achieved through, including:

- use of the aircraft as a towing vehicle;

- use of the ground transportation and booster platform (TRP), on which the loaded LV is mounted.

The invention is illustrated graphic materials, where

- figure 1 shows a General view of the side of the airport, placed on the runway, containing a series of interconnected using a cable tether, a towing aircraft and a carrier mounted on the TRP;

- figure 2 shows the remote element I, presented in figure 1 and reflecting the placement of the launch vehicle and the TRP relative to each other and the towing aircraft;

- figure 3 shows a view A, presented in figure 2, reflecting the placement of the pH and the TRP relative to each other when viewed from above.

RN 1 with additional fairings 2 mounted on its body, with wing 3 mounted on it, front (nose) 4 and tail 5 fairings mounted on the ground TRP 6. Wing 3 with its center section 7 and fairing 2 is mounted on the PH 1 body, cable the halyard 8 is interfaced with the center wing 7 of the wing 3 and the airplane 9. The front fairing 4 and the tail fairing 5 are mounted on the front (bow) and tail parts of the body of the PH 1, respectively. Stabilizing surfaces are mounted on the tail fairing 5, forming a controlled stabilizer 10 and a vertical tail unit 11. The wing 3 is equipped with ailerons 12, the stabilizer 10 is equipped with elevators 13, and the tail 11 is equipped with rudders 14. In wing 3 of fairing 2, center section 7 of wing 3 in front and tail fairings 4, 5, if necessary, cavities can be made for placing elements of control systems PH1, wing 3, stabilizer 10, for example, vertical tail unit 11 and their power supply, for example, electric accumulator al. systems ensuring functioning ARC (not shown).

The interconnected cable-fall 8, wing 3, center wing 7 of wing 3, fairing 2 form a PH1 interface device with aircraft 9, which performs the functions of a towing aircraft. The fairing 2 of the wing 3, the fairings of the front 4 and tail 5 are made with the possibility of separating them from the body PH1.

This system, including RN 1, aircraft 9 and other aforementioned elements, operates as follows.

Before launching the spacecraft, the ground-based TRP 6 is fed to the technical position of the aviation missile complex, where it is loaded with loaded PH 1, for example, with uncharged fuel components with the aforementioned elements mounted on it.

After loading the equipped RN 1 to the TRP 6, the PH 1 is refueled and its systems, as well as the TRP 6 systems are checked for operation.

After completing all the work on preparing the aviation missile system for launching the spacecraft, the equipped TRP 6 is towed to the take-off and landing strip (runway) 15 to the starting point of the TRP 6 when take-off of airplane 9 to the launch of PH 1, where the airplane 9 is paired with the wing center section 7 3, mounted on the fairing 2, using a cable-hitch 8. As a result, the aircraft 9 and TRP 6 are brought to the starting position on runway 15.

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

At the command of the ARC control system, engines are launched simultaneously on aircraft 9 and TRP 6 to take off to the launch site of RN1 (engines 16 are installed on it to accelerate TRP 6). The thrusts of the engines of the aircraft 9 and TRP 6 provide equal acceleration when moving along runway 15.

Upon reaching the specified thrust levels of the engines of towing aircraft 9, 10 and TRP 6, a take-off command is sent from the ARC control system (beginning of their movement along runway 15).

This ensures the levels of thrust of the engines of the aircraft 9 and engines 16 TRP 6, eliminating the sagging of the cable-rope 8 to an unacceptable level.

When aircraft 9 and TRP 6 are moving along runway 15, lift forces act on plane 9 and curb launch vehicle 1, which ensure separation of airplane 9 from runway 15 and curb launch vehicle 1 from TRP 6 when the set speed is reached (~ 280-300 km / h) .

When the aircraft 9 is separated from runway 15 at the same time from the TRP 6, the equipped RN 1 is separated by command, for example, from the RN 1 control system and the start of the flight of the aircraft 9 to the launch area of RN 1.

Upon arrival of aircraft 9 to the launch area, aircraft 9 and the equipped launch vehicle 1 occupy specified design positions in space in terms of altitude, direction and flight speed, and angular parameters (roll, pitch, course), ensuring launch of the launch vehicle 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, 4, 5, wing 3 with center section 7 from the housing of the launch vehicle 1, for example, by using pyro locks and detonating cords placed on the indicated detachable elements (not shown) for the destruction of their power bonds with PH1.

After separation from the body of the PH 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, allows, including:

- increase the effectiveness of the ARC as a whole;

- increase the safety, reliability of the aircraft and the ARC as a whole;

- 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 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 the surfaces forming a controlled stabilizer and, for example, vertical tail, the fairings are made with the possibility of separating them from the body of the launch vehicle, and the interconnected cable, wing, wing center section and its fairing form a launch vehicle interface with by plane. 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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