RU2359881C2 - Aviation rocket complex - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention is related to the field of aviation rocket-space engineering. Aviation rocket complex comprises airplane, carrier rocket for air starting, the following components installed on it - wing, front and tail fairings, on tail fairing stabilising surfaces are installed, which create controlled stabiliser and for instance vertical tail empennage. Also aviation rocket complex comprises towing rope-halyard that is connected to wing center section and airplane that performs functions of carrier rocket towing device, transport-overspeed platform with carrier rocket installed on it and systems that provide for their functioning. Transport-overspeed platform represents an airplane that has residual resource and service life and is redesigned for installation and surface transportation of carrier rocket.

EFFECT: invention is aimed at increase of carrier rocket dimensions and starting weight and therefore weights of spacecrafts put in orbit are reduced.

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 (ARC KN), for example, with heavy ballistic carrier rockets (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 launch of spacecraft (SC), for example, a satellite in orbit.

Known AR KN with a booster placed outside the fuselage of the aircraft.

The main disadvantages of the aforementioned aviation missile complex for space purposes are:

- 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.

The tasks to be solved by the invention are:

- 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 LV during take-off,

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

- a significant reduction in technical and financial 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 due to the implementation of the TRP on the basis of a 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 the LV on it, as well as to ensure its operation as part of the ARC. At the same time, this base aircraft is being finalized for placement of a launch vehicle on it in a minimum volume and with maximum use of all its standard units, components and systems (landing gear, engines, fuselage, control system, power supply, communication, etc.).

The invention is illustrated in the drawing, which shows a General view of the placement of the launch vehicle on a transport and booster platform.

The launch vehicle 1 with the wing 2 mounted on it, the front fairing 3, and the tail fairing 4 is placed on the transport and acceleration platform 5. The wing 2 is mounted on the body of the launch vehicle 1 through its center section 6, the tow cable 7 is connected to the wing center section 6 2 and aircraft 8, performing the function of a towing aircraft (not shown in the drawing). The front fairing 3 and the tail fairing 4 are mounted on the front and tail parts of the launch vehicle 1, respectively. Stabilizing surfaces are mounted on the tail fairing 4, forming a controlled stabilizer 9 and, for example, a vertical tail unit 10. The wing 2 is equipped with ailerons, the stabilizer 9 is equipped with elevators, and the tail 10 is equipped with rudders. In wing 2 and its center section 6, in the front and tail fairings 3, 4, if necessary, cavities can be made for placing elements of control systems, power supply for wing 2, stabilizer 9, for example, tail unit 10, launch vehicle 1, and other systems, ensuring the functioning of the ARC (not shown in the drawing).

This system, including the launch vehicle 1, wing 2 and other aforementioned elements, operates as follows.

Before launching the spacecraft, the TRP 5 is fed to the technical position of the aviation missile complex, where it is loaded with an equipped launch vehicle 1, for example, with uncharged fuel components, with the above-mentioned elements mounted on it.

After loading the loaded carrier rocket 1 on the TRP 5, the carrier rocket 1 is refueled and checked for its systems, as well as the TRP 5 systems for functioning.

After completing all the work on preparing the aircraft missile system for launching the spacecraft, the equipped TRP 5 is towed to the runway (runway) 11 to the starting point of the TRP 5 during take-off of aircraft 8 (not shown) to launch the launch vehicle 1, where the aircraft 8 is engaged with the center section 6 - wing 2 using the tow rope-hitch 7. As a result, aircraft 8 and TRP 5 are brought to the starting position on runway 11.

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

On a command to fly to the missile launch area, engines are launched simultaneously on aircraft 8 and TRP 5 (for accelerating TRP 5, for example, engines 12 from the aforementioned base aircraft, for example, IL-76MT (MD, MF), are installed on it). The thrust of the engines of the aircraft 8 and TRP 5 provide equal acceleration when moving along the runway 11.

Upon reaching the specified levels of engine thrusts of the towing aircraft 8 and TRP 5, a take-off command is issued (the start of their movement along runway 11).

This ensures the thrust of the engines of the aircraft 8 is slightly greater than that of the engines 12 TRP 5, with the aim of eliminating the sagging of the cable-rope 7 to an unacceptable level.

When aircraft 8 and TRP 5 move along runway 11, lifting forces act on the plane 8 and the launch vehicle 1, which ensure separation of the plane 8 from the runway 11 and the equipped rocket 1 from the TRP 5 when they reach a given speed (~ 280-300 km / hour).

After the separation of the aircraft 8 from the runway 11 at the same time from the TRP 5, a command from the control system separates the launch vehicle 1 and the start of the flight of the aircraft 8 to the launch area of the launch vehicle 1.

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

- at lower financial costs and the time required to create the ARC, significantly increase its reliability and safety during operation;

- to simplify the design of the TRP 5, to increase the safety of the crew of the towing aircraft 8 during take-off;

- 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 new direction in the creation of ARC transport-booster platforms to ensure the launch of towed launch vehicles.

Claims (1)

An aviation missile system, including an airplane, an air-launched launch vehicle, a wing mounted on it, front and tail fairings, on which stabilizing surfaces are mounted that form a controlled stabilizer and, for example, a vertical tail unit, a tow rope connected to the wing center wing and with an aircraft that performs the functions of a launch vehicle towing, a transport and booster platform with a launch vehicle mounted on it and systems that ensure their functioning, distinguishing by the fact that transport and accelerating platform is an aircraft having a residual resource and service life, modified for placement and ground transportation thereon launcher.