RU2318700C1 - Aircraft missile complex - Google Patents

Abstract

FIELD: rocketry and space engineering.

SUBSTANCE: invention can be used in space aircraft missile complexes, mainly with heavy ballistic missiles, mass exceeding 100 tons, furnished with liquid-propellant rocket engines and launched in air for orbit injection of spacecraft. Proposed aircraft missile complex contains aircraft, airframe with air start launch vehicle located inside fuselage, device for matching launch with aircraft playing part towing tugs, system providing their functioning and ground transportation-acceleration platform with its acceleration engines. Fuselage of airframe is made for division along horizontal plane. Transportation acceleration platform is essentially aircraft with residual service life and resource and modified for arrangement and ground transportation of airframe with launch vehicle and for operation in aircraft missile complex.

EFFECT: possibility to increase overall dimensions and takeoff weight of launch vehicle and, as result, to increase orbit injected masses of spacecraft.

4 cl, 1 dwg

Description

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

A known analogue of the ARC with a heavy ballistic launch vehicle (LV) located on the upper outer surface of a glider towed by several aircraft is presented in the description of the patent of the Russian Federation No. 2130879 (1999). The specified analogue, as the closest in technical essence, is taken as a prototype.

The disadvantages of the prototype are, including:

- the need to use for towing a glider equipped with a launch vehicle (LV), aircraft with increased power of propulsion systems;

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

- the complexity of the design of the airframe, the placement of the launch vehicle and other ARC systems on it, as well as the launch method of the launch vehicle;

- big risks in the implementation of the ARC creation program.

The tasks to which this application for an 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 and reliability of rocket launch;

- reduction of technical and financial risks during the creation of the ARC KN and during its operation, as well as the timing of development.

This is achieved, including due to:

- the use of aircraft as towing a glider, inside the fuselage of which is placed a launch vehicle (LV);

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

- use of a more simple in design device for coupling a glider with towing aircraft;

- execution of a ground-based TRP based on a used aircraft accepted for flight operation, for example, an Il-76MT (MD, MF) aircraft, which has a residual life-time resource, modified for the placement and ground transportation of an airframe with LV on it, and also for ensuring its operation as part of the ARC (At the same time, this base aircraft is being finalized for placing on it a glider equipped with LV in a minimum volume and with maximum use of all its standard units, components and systems (landing gear, engines, fuselage, control systems, electric tania, communications, etc.)).

The invention is illustrated in figures 1-3, which shows a General view of the placement of the glider with the LV on the ground TRP, pairing the glider with TRP and airplanes that perform the functions of towing the glider.

Glider 1 with RN 2 is placed on the TRP 3. Glider 1 is connected via a cable-hitch 4 to an airplane 5, which is connected to a plane 7 using a cable-hitch 6, cables 4, 6, airplane 5 form a glider 1 towing aircraft 7. To ensure the functioning of the TRP 3, the glider 1 and their systems, the TRP 3 and the glider 1 are equipped with control systems (not shown in the drawing). This system: a glider 1 equipped with a PH 2, aircraft 5, 7 TRP 3 and towing ropes-halyards 4, 6 operate as follows.

Before launching the spacecraft, the TRP 3 is fed to the technical position of the aviation missile complex, where it is loaded with a glider 1 equipped with PH 2, for example, not filled with 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 8, the upper part 9. After loading the glider 2 on the TRP 3, the PH 2 is refueled and the PH 2 systems are checked, as well as the TRP 3 systems. After completion of all work on preparing an aviation missile complex for launching a spacecraft (including glider 1, aircraft 5, 7 PH 2, TRP 3) equipped with TRP 3 is towed to the runway (runway) 10, from which take-off and take-off of aircraft 5, 7 and the movement of the TRP 3.

On runway 10, the aircraft 5 are mated with the glider 1 using the towing rope-file 4 and aircraft 5, 7 sequentially (one after another) using the cable-rope 6. As a result, aircraft 5, 7 and TRP 3 are brought to the starting position at Runway 8.

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

On command from the ARC control system, engines are launched simultaneously on aircraft 5, 7 and TRP 3 to take off to the launch site of RN 2 (for accelerating TRP, for example, engines 11 from the aforementioned Il-76MT base aircraft (MD, MF) are installed on it). The thrusts of the engines of aircraft 5, 7 and TRP 3 provide equal acceleration when they move along runway 10. Upon reaching the specified levels of thrusts of the engines of aircraft towing aircraft 5, 7 and TRP 3, a take-off command is issued (the start of their movement along runway 10). At the same time, the thrust levels of the engines of aircraft 5, 7 TRP 3 are provided, excluding the sagging of the halyard cables 4, 6 to unacceptable levels.

When airplanes 5, 7 and TRP 3 are moving along runway 10, lifting forces act on planes 5, 7 and glider 1, which ensure separation of planes 5, 7 from runway 10 and glider 1 from TRP 3 when the desired speed is reached (~ 280-300 km / h).

After the separation of aircraft 5, 7 from runway 10 at the same time from TRP 3, on command of the ARC control system (glider 1 or TRP 3), the equipped LV 2 of the glider 1 is separated and the flight of aircraft 5, 7 begins to the launch area of LV 2 with the aim of launching the spacecraft.

Upon the arrival of aircraft 5 to the launch area of PH 2, planes 5, 7 and glider 1 occupy the specified design positions and in space in altitude, 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 8 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 elongated charges mounted on the upper 9 and lower 8 parts of the fuselage of glider 1 for destruction their power connections with each other, are not shown in the drawing) and after its separation, a command is sent from the ARC control system to separate the PH 2 from the upper part 9 of the fuselage of the glider 1 and start its first-stage engines. The PH 2 is separated from the upper part 9 of the fuselage of the glider 1 under the action of gravity (i.e., falls), and the glider 1 (upper part 9) due to the presence of the lifting force created by the wing 12, rises up. After separation of the launch vehicle 2 from the upper part 9 of the airframe 1 and the launch of its 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:

- at lower financial costs and the time required to create the ARC KN, to increase its effectiveness;

- increase the safety and reliability of the operation of the ARC;

- simplify the technology of manufacturing and testing of ARC systems during their creation;

- reduce technical, economic 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 (4)

1. An aviation missile system, including airplanes, a glider, an air launch vehicle, a device for interfacing an airframe with airplanes that perform the functions of airframe towers, systems that ensure their operation, characterized in that it contains a ground transport and acceleration platform equipped with engines on which mounted a glider, inside the fuselage of which is placed a booster, while the lower part of the fuselage of the glider is configured to separate it from the upper part of the fuselage down, sequentially with first and second planes are tied with the help of the first hitch rope, and the second airplane with the help of the second hitch rope is paired with the upper part of the glider fuselage, while both the hitch rope and the second airplane form a device for interfacing the glider with the towing aircraft, and the platform is an aircraft with a residual life and service life, modified for the placement and ground transportation of a glider with a booster rocket on it, as well as under its operating conditions as part of an aircraft missile complex. 2. The aviation missile system according to claim 1, characterized in that the transport and booster platform is made on the basis of the developed aircraft, adapted for its operation as part of an aircraft missile complex. 3. The aviation missile system according to claim 1, characterized in that the ground transport and booster platform is equipped with a control system. 4. The aviation missile system according to claim 1, characterized in that the glider is equipped with a control system.

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