RU2355601C2 - 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. The said surface transport-boosting platform represents an aircraft sufficient operating hours, adapted for accommodation and surface transportation of rocket-carrier.

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

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 with the aim of launching spacecraft (SC), for example, a satellite in orbit.

A known analogue of the ARC with a heavy launch vehicle (LV) located outside the fuselage of the aircraft, presented in the information issues No. 20, 21, 31, 32, 38-41, 45, 46 of 1988, "Rocket and Space Technology" based on foreign press, express information, series 1, edition of the Central Scientific Research Institute of Mechanical Engineering, Moscow on the ARC with the Pegasus launcher (LV) (USA).

The specified analogue, as the closest in technical essence, can be taken as a prototype.

The main disadvantages of the prototype including:

- the need to carry out large volumes of research and development work (R&D) to create a ground-based vehicle (NS) that provides take-off of a launch vehicle equipped with a wing, stabilizer and, for example, vertical tail, by towing it by plane;

- large financial costs and timelines required to create the aforementioned SB.

- low efficiency of using the technical capabilities of aircraft-towing launch vehicles (LV);

- low reliability and safety of the ARC during its creation and regular operation, including 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, including the following:

- a decrease in the volume of R&D on the creation of the aforementioned National Assembly (hereinafter, read: “transport-booster platform (TRP)”) and, therefore, the ARC as a whole;

- improving the safety of the crew during take-off;

- improving the safety and reliability of the aircraft during take-off;

- a significant reduction in the cost of creating the ARC as a whole;

- a significant reduction in technical and other risks during the creation of the ARC and during its operation, as well as the timing of the development of the ARC.

This is achieved, including due to:

- the use of ground-based TRP, on which the LV is mounted;

- the use of the launch vehicle, on the body of which a cowl with a wing mounted on it is additionally installed, the cowls of the front (nose) and tail fairings with stabilizing surfaces with the possibility of separation from the body of the launch vehicle;

- execution of a ground-based TRP based on an existing used aircraft accepted for flight operation, for example, an IL-76MT (MD, MF) aircraft with residual life and service life, modified for placement and ground transportation of LV on it, as well as for ensuring its operation as part of the ARC, while this base aircraft is being finalized for placing on it a launch vehicle (LV) in a minimum volume and with maximum use of all its standard units, components and systems (landing gear, engines, fuselage, control systems, electric power, communication, etc.).

The invention is illustrated figure 1-3, which shows a General view of the placement of the launch vehicle on the ground TRP and its interface with aircraft that perform the functions of towing.

RN 1 with a fairing 2 mounted on its body with a wing 3, a front (nose) fairing 4, a tail fairing 5 is placed on the ground TRP 6. Wing 3 is mounted on the housing of the PH 1 with its center section 7 and fairing 2 and the tow rope 8 connected to the center wing 7 of wing 3 of PH 1 and aircraft 9. The front fairing 4 and the tail fairing 5 are mounted on the front and tail parts of the PH 1, respectively. A stabilizing surface is mounted on the tail fairing 5, forming a controlled stabilizer 10 and, for example, a vertical tail unit 11. The wing 3 is equipped with ailerons 12, the stabilizer 10, for example, elevators 13, and the tail 11, for example, rudders 14. In wing 3 and its center section 7, in fairings 2, 4, 5, if necessary, cavities can be made for placing elements of control systems, power supply for wing 3, stabilizer 10, tail unit 11, PH 1 and other systems that ensure the functioning of the ARC (not shown).

The interconnected cable-rope 8, wing 3, center wing 7 of wing 3, fairing 2 of wing 3 form a device for interfacing PH1 with aircraft 9, which acts as a towing aircraft.

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, not filled with fuel components, with the aforementioned elements mounted on it.

After loading the equipped launch vehicle 1 onto the ground TRP 6, the RN 1 is refueled and its systems, as well as the TRP 6 systems are checked for operation.

After the completion of all work on preparing the aircraft missile system for launching the spacecraft, the equipped TRP 6 is towed to the runway (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 engaged with the center section 7 wing 3 PH 1 with the help of a towing rope-hitch 8. As a result, 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.

On command from the ARC control system, engines are launched simultaneously on aircraft 9 and TRP 6 to take off to the launch site of PH 1 (for accelerating TRP 6, for example, engines 16 from the aforementioned base aircraft, for example, IL-76MT (MD, MF), are installed on it ) The thrusts of the engines of the aircraft 9 and TRP 6 provide equal acceleration when moving along runway 15.

Upon reaching the specified levels of engine thrusts of the towing aircraft 9 and TRP 6, a take-off command is issued (the start of their movement along runway 15).

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

When aircraft 9 and TRP 6 move along runway 15, lift forces act on aircraft 10 and PH 1, which ensure separation of airplane 9 from runway 15 and curb PH 1 from TRP 6 when they reach a specified speed (~ 280-300 km / h) .

When the aircraft 9 is separated from runway 15 simultaneously from TRP 6, PH 1 is separated by command, for example, from the ARC control system (PH 1 or TRP 6) and the flight of airplane 9 starts to the launch area of PH 1. At the same time, launch of PH 1 is performed by command ARC control system after separation of a cowl 2 mounted on its body with a wing 3, a front cowl 4 and a tail cowl 5 by using, for example, elongated detonating charges mounted in a cowl 2, 4, 5.

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, to increase its effectiveness;

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

- to 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 (3)

1. Aircraft missile system, including an airplane, an air launch vehicle, a device for interfacing a launch vehicle with an aircraft, systems for ensuring their operation, characterized in that it further comprises a cowl mounted on the body of the launch vehicle, on which a wing with a center wing is mounted, equipped with ailerons, nose and tail fairings, on which stabilizing surfaces are mounted, forming a controlled stabilizer and, for example, a vertical tail unit, with a fairing made with the possibility of separating them from the body of the launch vehicle, a ground transport and booster platform equipped with engines, on which the launch vehicle is mounted with fairings mounted on its body, a cable tether, while a cable tether, a wing, a wing center section are interconnected and its fairing form a device for interfacing the launch vehicle with the aircraft, and the ground transportation and booster platform is an aircraft with a residual life and service life, modified for placement and ground transported ie it launcher. 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 energy 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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