RU2323856C2 - Aircraft missile system - Google Patents

Abstract

FIELD: engines and pipes.

SUBSTANCE: aircraft missile system contains airplanes, airframe, in the fuselage of which it is disposed the booster rocket of airborne device of mating the booster rocket with the airplane, making the function of the towing vehicle, and systems providing their functioning, and surface-mounted transport-booster platform, equipped with engines for its boosting. On the rocket fuselage it is additionally installed the cowling with additional wing on it, and brad with tail cowling. On the tail cowling it is installed the stabilization device and rudder unit. The cowlings are made with possibility of being removed from the rocket. The surface-mounted transport-booster platform is made on the base of airplane, which has the remaining life expectancy and mechanical life.

EFFECT: it is achieved the exceeding of the distance of flight and it is arisen the cargo mass of space objects bringing to the 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 Satellite in orbit.

A known analogue of the ARC with a heavy launch vehicle (LV) of an air launch towed by several aircraft is presented in the description of RF patent No. 2130879 (1999).

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 facility (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);

- the complexity of the device for interfacing the LV with the towing aircraft and the implemented method of launching the LV;

- the complexity of the technologies for developing the ARC systems during its creation and regular operation;

- low reliability and safety of the ARC during its creation and regular operation.

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

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

- increasing the safety of aircraft crews during take-off;

- improving the safety and reliability of aircraft 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, among other things, by:

- 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;

- two hitch ropes and two towing aircraft for towing the launch vehicle to the launch area;

- the possibility of using a more simple in design device for interfacing a LV with towing aircraft;

- 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 the maximum use of all its standard units, components and systems (landing gear, engines, fuselage, control systems, electric power, communication, etc.). The invention is illustrated by drawings, where:

- figure 1 shows a General view of the side of the airport, placed on the runway, containing in series connected by cable ropes two aircraft towing and LV mounted on the TRP;

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

- 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 mounted on its body 2 fairing 3 with wing 4, front (nose) fairing 5, tail fairing 6 is placed on the ground TRP 7. Wing 4 through its center section 8 is mounted on housing 2 PH 1, the tow rope 9 is connected to center wing 8 wing 4 PH 1 and aircraft 10, the tow rope 11 is connected to the aircraft 10, 12. The front fairing 5 and the tail fairing 6 are mounted on the front and rear parts of the PH 1, respectively. Stabilizing surfaces are mounted on the tail fairing 6, forming a controlled stabilizer 13 and, for example, a vertical tail unit 14. The fairings 3, 5 and 6 are made with the possibility of separating them from the body 2 of the PH 1, for example, using detonating elongated charges or pirozamok, mounted on these fairings, for the destruction of their power connections with the housing 2 PH 1 (not shown). The wing 3 is equipped with ailerons 15, a stabilizer 13, for example elevators, and a plumage 14, for example rudders. In the wing 4 and its center section 8, in the fairings 3, 5, 6, if necessary, cavities can be made for the placement of elements of control systems, power supply for the wing 4, stabilizer 13, tail unit 14, PH 1 and other systems that ensure the functioning of the ARC (on not shown).

Tether cables 9, 11, aircraft 10, center wing 8 of wing 4, fairing 3 of wing 4 form a device for coupling PH1 with a towing aircraft 12.

This system, including the pH 1, aircraft 10, 12 and other aforementioned elements, operates as follows.

Before the launch of the spacecraft, the ground-based TRP 7 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 above-mentioned elements mounted on it.

After loading the equipped carrier rocket 1 on the ground TRP 7, the RN 1 is refueled and its systems, as well as the TRP 7 systems are checked for operation.

After completing all work on preparing the aviation missile system for launching the spacecraft, the equipped TRP 7 is towed to the runway (runway) 16 to the point where TRP 7 starts to take off when take off aircraft 10, 12 to launch PH 1, where aircraft 10 are coupled with the center section 8 wing 4 PH 1 using tow rope 9 and from airplane 10 with airplane 12 using tow rope 11. As a result, aircraft 10, 12 and TRP 7 are brought to the starting position on runway 16.

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

At the command of the ARC control system, the engines are launched simultaneously on aircraft 10, 12 and TRP 7 to take off to the launch site of RN 1 (for accelerating TRP 7, for example, engines 17 from the aforementioned base aircraft, for example, IL-76MT (MD, MF)). The thrusts of the engines of aircraft 10, 12 and TRP 7 provide equal acceleration when moving along runway 16.

Upon reaching the specified levels of thrust of the engines of aircraft towing aircraft 10, 12 and TRP 7, a take-off command is given (the start of their movement along runway 16).

At the same time, the thrust levels of the engines of aircraft 10, 12, engines 17 of the TRP 7 are provided, excluding the sagging of the hitch cables 9 and 11 to unacceptable levels.

During the movement of aircraft 10, 12 and TRP 7 along runway 16, lift forces act on planes 10, 12 and PH 1, which ensure separation of planes 10 and 12 from runway 16 and curb PH 1 from TRP 7 when they reach a given speed (~ 280 -300 km / h).

When aircraft 10 and 12 are separated from runway 16 simultaneously from TRP 7, PH 1 is separated by command, for example, from the ARC control system (PH 1 or TRP 7) and the flight of 10, 12 aircraft begins to the launch area of PH 1. Upon arrival in the area launch planes 10, 12 and equipped with a launch vehicle 1 occupy the specified design positions in space in terms of altitude, direction and flight speed, angular parameters (roll, pitch, course) ensuring launch of the launch vehicle 1. Launch of the launch vehicle PH1 is carried out after separation of the 2 fairings mounted on its body for 3 s wing 4 front fairing 5 and tail fairing 6 of Tell.

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;

- 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. Aviation missile system, including airplanes, an air launch vehicle, a device for interfacing a launch vehicle with airplanes that perform the functions of a launch vehicle tow, systems that ensure their operation, characterized in that it contains a ground transport and booster platform equipped with engines, on which the launch vehicle is mounted, a fairing additionally mounted on the launch vehicle body, on which a wing with a center wing, equipped with ailerons, is mounted, nose and hv cowls a skeleton on which stabilizing surfaces are mounted, forming a controlled stabilizer and, for example, a vertical tail unit, while all fairings are made with the possibility of separation from the body of the launch vehicle, the first and second planes are sequentially paired with the first halyard cable, while the second plane with the help of the second hitch rope, it is interfaced with the wing center wing mounted on a fairing mounted on the carrier rocket body, while both the hitch rope and the second aircraft together with the wing, the center wing ohms of the wing and its fairing form a device for interfacing a carrier rocket with a towing aircraft, and the ground transport and booster platform is an aircraft with residual life and service life, modified for placement and ground transportation of a carrier rocket on it. 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, control elements of the launch vehicle, wing, stabilizing surfaces and their power supply are placed, 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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