RU2359870C2 - 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, and additional airplane and towing rope-halyard.

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 (LV) weighing 100 tons or more, equipped with, for example, liquid-propellant rocket engines (LRE) and launched in the air outside the aircraft, with the purpose of putting spacecraft (SC), for example, a satellite, into orbits.

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

The main disadvantage of the aforementioned aerospace missile system for space purposes is the limitation on the maximum initial launch vehicle mass and, as a result, the restrictions on the maximum mass of spacecraft launched into orbits.

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

- an increase in the mass of the spacecraft launched into orbits,

- 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 an ARC with enhanced technical characteristics, as well as the timing of its development.

This is achieved by including in the ARC additional aircraft and towing rope-halyard in comparison with the prototype. The inclusion of additional aircraft and towing rope allows you to increase the force required for transportation on a transport and boarding platform (TRP) with a LV mounted on it with an increased initial mass on the ground during take-off and flight to the launch area.

As basic aircraft, which can be taken as the basis for the development of towing aircraft and TRP, can be taken existing, spent heavy transport aircraft, for example, IL-76MT (MD, TF), modified under the conditions of their use as part of the ARC. This will significantly increase the technical and economic efficiency of the ARC (including a significant reduction in the financial costs and terms of the creation of the ARC, increasing the safety of operation and technical characteristics of the ARC).

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 and its interface with aircraft that perform the functions of towing vehicles.

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, the towing cable 9 is connected to aircraft 8, 10. The front fairing 3 and the tail fairing 4 are mounted on the front and rear parts of the launch vehicle 1, respectively. Stabilizing surfaces are mounted on the tail fairing 4, forming a controlled stabilizer 11 and, for example, a vertical tail unit 12. The wing 2 is equipped with ailerons, the stabilizer 11 is equipped with elevators, and the tail 12 is equipped with rudders. In the 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 the wing 2, stabilizer 11, for example, tail unit 12, 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, ungrounded fuel components with the aforementioned elements mounted on it.

After loading the equipped launch vehicle 1 on the TRP 5, the carrier rocket 1 is refueled and its systems, as well as the TRP 5 systems are checked for operation.

After completing all the work on preparing the aviation missile complex for launching the spacecraft, the equipped TRP 5 is towed to the runway 13 to the starting point of the TRP 5 when take off planes 8 and 10 to launch the launch vehicle 1, where the aircraft is engaged 8 with wing center section 6 of wing 2 using tow rope 7 and aircraft 10 with airplane 8 using tow rope 9. As a result, planes 8 and 10 and TRP 5 are brought to the starting position on runway 13.

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

On a command to take off to the missile launch area, engines are started simultaneously on planes 8, 10 and TRP 5 (for accelerating TRP 5, for example, engines 14 from the aforementioned base aircraft, for example, IL-76MT (MD, MF), are installed on it). The thrust of the engines of aircraft 8, 10 and TRP 5 provide equal acceleration when moving along runway 13.

Upon reaching the specified levels of engine thrusts of aircraft towing aircraft 8, 10 and TRP 5, a take-off command is given (the start of their movement along runway 13).

At the same time, thrusts of engines of aircraft 8, 10, engines 14 of TRP 5 are provided, which exclude the contact of cables, halyards 7, 9 of runway 13. When moving planes 8, 10 and TRP 5 along runway 13, lifting planes 8, 10 and launch vehicle 1 operate forces that ensure separation of aircraft 8, 10 from runway 13 and curb rocket 1 from TRP 5 when they reach a given speed (~ 280-300 km / h).

After the separation of aircraft 8 and 10 from runway 13 at the same time from TRP 5, on command, for example, from the ARC control system (RN1, TRP 5), the launch vehicle 1 is separated and the aircraft 8 and 10 begin to fly to the launch area of the launch vehicle 1. The launch vehicle 1 is launched after separation of the wing 2 mounted on it, the front fairing 3 and the tail fairing 4.

Thus, the technical appearance of the ARC presented above with new distinctive features in comparison with the prototype allows for lower financial costs and the time required to create the ARC with improved characteristics, for example, significantly increase the mass of the spacecraft launched into orbits.

The technical solution proposed in the invention opens up a new direction in the creation of means for ensuring the launch of towed carrier rockets and their delivery to the launch area.

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 section 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 contains additional aircraft and tow rope halyard.