RU2401777C1 - Air rocket complex - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering, particularly to placing of manned spacecraft complexes with ballistic rockets weighing over 100 t in to orbit. Proposed complex comprises towing aircraft (not shown), carrier rocket 4 with nose cone 13 and spacecraft coupled therewith, transporter-launcher 3 furnished with power plant, for example solid propellant rocket engine. Carrier rocket body is provided with wings 4, front and rear fairings 15. Said fairing 15 accommodates aerodynamic control surfaces, including tail vertical fins 17. Fairings 14, 15 and wing 12 are separated from carrier rocket body in response to rocket start instruction. Rocket 4 is jointed with platform 3 by mechanical links and elements that allow simultaneous separation of rocket 4 from said platform and starting towing aircraft. Towing rope-cord is furnished with lock 10 comprising rope elements 7, 8, 9 controlled by remote means in response to spacecraft rescue instruction. First rope element 7 is jointed with towing aircraft, second rope element 8 is connected with wing center section 11 of wing 12 and third rope element is connected with nose cone 13. Note here that rope element 8 can be separated from wing center section 11 and lock 10 (in response to spacecraft rescue instruction) as well as separation and jettisoning of front fairing. Thereafter, nose cone 13 together with spacecraft 6 is separated from rocket body and pulled by rope element 7 via rear cargo door inside towing aircraft.

EFFECT: possibility of spacecraft rescue.

2 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 (SC), for example, with heavy ballistic carrier rockets (LV) (weighing 100 tons or more), equipped with, for example, liquid-propellant rocket engines (LRE) of air launch for the purpose of launching into orbits of spacecraft (SC), for example, artificial Earth satellites (AES).

A known analogue of the ARK KN with a launch vehicle placed outside the fuselage of the aircraft, presented in patent No. 2317923 RU. The specified analogue, as the closest in technical essence, is taken as a prototype.

The disadvantage of the prototype is the inability to save the spacecraft in the period of time from the moment of take-off of the aircraft until the completion of pre-launch LV equipped with a spacecraft, for example, in case of failures of the spacecraft systems.

The task to which the application for the invention is directed is to rescue the spacecraft, for example, upon detection of failures in the spacecraft systems in the period from the moment of take-off of the aircraft to the completion of pre-launch preparation of the spacecraft.

This is achieved by ensuring the rescue of the spacecraft in the aforementioned period by separating the head fairing of the launch vehicle with the spacecraft mounted inside its spacecraft from the launch vehicle and then retracting the head fairing inside the aircraft fuselage.

The invention is illustrated by drawings, where:

- figure 1 shows a General view of the location of the elements of the ARC (airplane 1, cable tether (TF) 2, transport and boarding platform (TRP) 3, PH 4 on the runway (runway) 5);

- figure 2 shows the remote element I of figure 1, which reflects the placement of the pH 4, equipped with a spacecraft 6, on the TRP 3;

- figure 3 shows a view A of figure 2, reflecting a top view of the PH 4 and TRP 3, the vertical plane of the connector B, which separates the front cowl 14 mounted on the head fairing 13 of the PH 4.

The list of items shown in figures 1, 2, 3:

1 - plane;

2 - cable tether (TF);

3 - transport and booster platform (TRP);

4 - launch vehicle (PH);

5 - runway (runway);

6 - spacecraft;

7 - the first cable element (TE);

8 - second fuel cell;

9 - the third TE;

10 - castle;

11 - center section;

12 - wing;

13 - head fairing (GO) PH 4;

14 - front fairing;

15 - tail fairing;

16 - controlled stabilizer;

17 - vertical tail;

18 - ailerons;

19 - elevator;

20 - rudder;

21 rocket solid fuel engine;

22 - cargo hatch of the aircraft;

23 - winch (not shown in the drawing).

The launch vehicle 4 with mounted on it using mechanical connections and elements (MS and E) (not shown in the drawing) wing 12, the front fairing 14, the tail fairing 15 is placed and secured with the help of MS and E (not shown) on transport and boarding platform 3. The wing 12 through its center section 11 using MC and E (not shown) is mounted on the body of the launch vehicle 4, the cable-rope 2 is connected via MC and E (not shown) to the center section 11 wing 12 and aircraft 1, performing the function of a towing aircraft. The front fairing 14 and the tail fairing 15 are mounted using MS and E (not shown in the drawing) on the front and rear parts of the launch vehicle 4, respectively. On the tail fairing 15, stabilizing surfaces are mounted with the help of MC and E (not shown), forming a controlled stabilizer 16 and a vertical tail unit 17. The wing 12 is equipped with ailerons 18, the stabilizer 16 is equipped with elevators 19, and the tail 17 with rudders 20. In the wing 12 and its center section 11, in the front and tail fairings 14, 15, if necessary, cavities can be made to accommodate elements of control systems (SU), power supply to the wing 12, stabilizer 16, for example, vertical tail unit 17, rockets- carrier 4 and other systems that ensure the functioning of the ARC (not shown in the drawing).

Generating TF 2 - several, for example, three cable elements (FC) 7, 8, 9, respectively, the first, second and third, each of which is connected with lock 10 at one end and additionally the first TE 7 is connected to airplane 1, the second TE 8 is paired with the center section 11 of the wing 12, and the third TE 9 is associated with the head fairing 13 PH 4.

RN 4 is equipped with a spacecraft 6, which is mounted and placed in its front part, inside the GO 13, and is interfaced with both the body of the GO 13 and the body of the PH 4 using MS and E (not shown in the drawing). GO 13 is paired with the third TE 9 TF 2 using MS and E (not shown in the drawing). The interconnected GO 13 and KA 6 are made with the possibility of separating them from the RN 4 when a command is sent to save the KA 6, which is formed by systems that ensure the functioning of the ARC.

TF 2 contains a remotely controlled lock 10 containing electromechanical actuators and pyrotechnic means, for example, squibs and detonating cords, controlled by a rescue team for spacecraft 6 formed by systems that ensure the functioning of the ARC (not shown), several, for example, three TEs from of which the first TE 7 is interfaced with the airplane 1 and the lock 10, the second TE 8 is interfaced with the center wing 11 of the wing 12 and the lock 10, the third TE 9 is interfaced with the GO 13 PH 4 and the lock 10 with the possibility of separation of the second TE 8 from the center 11 and the wing 12 and lock 10.

The front fairing 14, mounted using MS and E (not shown) in the front housing of the PH 4, is made with the possibility of separation from the housing of the PH 4 and its separation, for example, into two equal parts along the vertical plane B, for example , by using the pyro locks and detonating cords placed in the separation plane B (not shown in the drawing) on the command to save the spacecraft 6, formed by systems that ensure the functioning of the ARC. In this case, the front fairing 14 has a hole B in the direction of its longitudinal axis to ensure the interface GO 13 PH 4 with the lock 10 using the third cable element 9, and the locks and detonating cords are placed both on the front fairing body 14 and on the housing GO 13 PH 4 (not shown in the drawing).

This system, including a launch vehicle 4, a wing 12 and other aforementioned elements, operates as follows.

Before launching the spacecraft 6 TRP 3 is fed to the technical position of the ARC, where it is loaded with a loaded launch vehicle 4, for example, ungrounded fuel components, with the aforementioned elements mounted on it.

After loading the equipped carrier rocket 4 on the TRP 3, the carrier rocket 4 is refueled with fuel and its systems, as well as the TRP 3 systems are checked for functioning.

After the completion of all work on preparing the aircraft missile system for launching the spacecraft 6, the TRP 3 is towed to the runway 5 to the starting point of the TRP 3 during take-off of airplane 1, where the airplane 1, center section 11, GO 13 RN 4 are engaged, respectively with TE 7, 8, 9 and lock 10 with TE 7, 8, 9, forming TF 2. As a result, aircraft 1 and TRP 3 are brought to the starting position on runway 5.

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

At a command from the ARC SU (not shown), engines are launched to take off for the launch area simultaneously on aircraft 1 and TRP 3 (for accelerating TRP 3, for example, solid propellant rocket engines 21 are installed on it). The thrust of the aircraft engines 1 and TRP 3 provide equal acceleration when moving along runway 5.

Upon reaching the specified levels of engine thrusts of the towing aircraft 1 and TRP 3, a take-off command is issued (the start of their movement along runway 5).

At the same time, the movement parameters of aircraft 1 and TRP 3 are provided, excluding the sagging of the cable-rope 2 to an unacceptable level.

When aircraft 1 and TRP 3 move along runway 5, lifting force acts on the plane 1 and curb launcher 4, which ensure separation of airplane 1 from runway 5 and curb launcher 4 from TRP 3 when the desired speed is reached (~ 280 km / hour).

After the separation of the aircraft 1 from the runway 5 at the same time from the TRP 3, the carrier rocket 4 is separated and the flight of the aircraft 1 begins in the launch area of the carrier rocket 4.

In the period from the moment of take-off of airplane 1 with towed launch vehicle 4 until the start-up preparation of launch vehicle 4 for launch is completed, in systems, for example, aircraft 1, launch vehicle 4 and other ARC systems (not shown in the drawing), failures or malfunctions can be detected that do not allow make a normal launch of the pH 4 and, consequently, leading to the loss of spacecraft 6.

In this case, in order to save the spacecraft 6, the following commands are issued, formed by systems that ensure the functioning of the ARC, in the specified estimated time sequence for separating the TE 8 from the lock 10 and the center section 11, the front cowl 14 from the pH 4, to separate the front cowl 14, for example, into two equal parts along the vertical plane B, to separate the mating GO 13 and KA 6 from the RN 4 (the body of the last stage of the RN 4) by using remotely controlled electromechanical actuators and pyrotechnic means, for example pyrocartridges and detonating cords mounted on PH 4, GO 13, front fairing 14 and center section 11, lock 10 (not shown in the drawing) to ensure that GO 13 is retracted, with its spacecraft 6 inside the aircraft fuselage 1 , for example, through the rear cargo hatch of an airplane 22 using the first TE 7 and the third TE 9 and a winch 23, coupled with a lock 10, installed inside the fuselage of the airplane 1 (not shown).

Thus, the technical appearance of the ARC presented above with new distinctive features in comparison with the prototype eliminates the loss of spacecraft 6 in case of malfunctions or failures of the PH 4 and ARC systems during the period from the moment of take-off of the aircraft 1 from the towed PH 4 equipped with the spacecraft 6 to completion of pre-launch pH 4.

The technical solution proposed in the present application for the invention opens up a new direction in the development of the ARC containing the spacecraft rescue means and allows reducing the economic damage during the operation of the SC AR, caused by the loss of the SC.

Claims (2)

1. Aircraft missile system, including an airplane, an air launch vehicle containing a head fairing, a spacecraft coupled to the launcher body, a transport and booster platform equipped with a propulsion system, for example, with a solid fuel rocket engine mounted on it a launch vehicle using mechanical connections and elements, allowing simultaneous separation of the launch vehicle from the transport and booster platform and the start of the flight of the aircraft, cable, systems, both which impede the functioning of the aviation missile complex, while a wing with a center wing, a front and a tail fairing are mounted on the carrier rocket’s hull, the last of which has stabilizing surfaces forming a controlled stabilizer and, for example, a vertical tail, with the front and tail fairings and wings being separated with a center wing from the carrier rocket’s body, it is made on a command to launch the rocket, the cable-tether is connected to the wing center wing, as well as with an aircraft that performs the functions of a carrier rocket keroseneck to its launch point, characterized in that the spacecraft is interfaced with the head fairing of the launch vehicle, the cable contains a remotely controlled lock containing electromechanical actuators and pyrotechnic devices, for example, squibs and detonating cords, controlled by a command on salvation of a spacecraft formed by systems that ensure the functioning of an aircraft missile complex, several cable elements, for example three, of which the first the axial element is paired with the airplane and the lock, the second cable element is paired with the wing center section and the lock, the third cable element is paired with the head fairing of the launch vehicle and the lock, making it possible to separate the second cable element from the wing center section and the lock, interfaced to the head fairing of the rocket- carrier and spacecraft from the carrier rocket for subsequent retraction into the fuselage of the aircraft, for example, through the rear cargo hatch of the aircraft with the help of the first and third cable elements and winch mounted in the fuselage of the aircraft. 2. The aviation missile system according to claim 1, characterized in that the front fairing is made with the possibility of dividing it, for example, into two equal parts on a vertical plane, for example, using pirozamok and detonating cords placed in the plane of separation of the front fairing and involved on command to save the spacecraft, formed by systems that ensure the functioning of the aircraft missile complex, has a hole in the center in the direction of its longitudinal axis to ensure the main fairing of the launch vehicle with the lock using the third cable element, while the pyro locks and detonating cords are placed both on the front fairing body and on the main fairing body of the launch vehicle.

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