RU2658236C1 - Electrical air start system of the space rocket - Google Patents

Abstract

FIELD: aviation; astronautics.

SUBSTANCE: invention relates to aerospace engineering. Electric air launch system of a space rocket contains a base with a control system for the launch system and batteries for its power supply. Base is made in the form of a non-rotating ring. To the ring, support rods are attached at their own ends, containing at the other ends of the heel of the support rods interacting with catapults containing the catapult rotors, stators of which are placed on the supporting bars, and heels of catapults for supporting the space rocket. Upper rotating ring with attached blades is supported by means of a magnetic suspension system, the upper part of a nonrotating ring with the electric drive of the upper rotating ring. Lower rotating ring with attached blades is supported by the magnetic suspension system by the lower part of the non-rotating ring. Power supply of the base electrical units is carried out by means of a ground power supply.

EFFECT: increase the reliability, economy and environmental safety of the launch system.

1 cl, 7 dwg

Description

The invention relates to aerospace technology, namely to air launch systems for launching space rocket carriers and aerospace aircraft, to aircraft rocket and space complexes - means for launching space objects.

The well-known "Aviation missile system", RF Patent No. 2401779, B64G 5/00, B64D 3/00, B64G 1/14, 05/04/2009, which includes a glider, cable tether, an airplane adapted to tow a glider using a cable tether , a launch vehicle for launching a spacecraft. The booster rocket contains a head fairing, inside which a spacecraft is mounted that is interfaced with the launcher body, a ground transport and booster platform equipped with a propulsion system, for loading the glider onto it, as well as for taking off the aircraft and the glider, and systems that ensure their functioning. The launch vehicle is located inside the fuselage of the airframe having a lower part, detachable from its upper part before being separated from this upper part and launching the launch vehicle. The tether cable is interfaced with the body of the head fairing of the launch vehicle. The spacecraft is interfaced with the head fairing of the launch vehicle with the possibility of separating the tether from the glider, the spacecraft and the body of the fairing from the body of the launch vehicle for subsequent retraction into the fuselage of the aircraft through the rear cargo hatch of the aircraft using a tether and winch, paired with a halyard cable installed in the fuselage of the aircraft. The advantage of this invention is the preservation of the spacecraft in case of failure to launch the launch vehicle. But the disadvantage is the need for a long time to prepare for the launch. In addition, the weight of the space rocket, which can be launched using it, is limited.

The well-known "Integrated system for launching heavy reusable aerospace aircraft in low Earth orbit, a heavy heavy amphibious jet for it (options) and a launch method", RF Patent No. 2397922, B64G 1/14, B64C 35/00, B64D 5 / 00, 07/30/2008, which relates to the field of aerospace engineering, namely to an integrated system for launching reusable heavy aerospace aircraft into low Earth orbit, to a heavy amphibious jet aircraft for an integrated system, and to a method for SIC operated comprehensive system startup heavy aerospace aircraft into orbit. The integrated system includes a lift aircraft with a detachable booster block, an aerospace plane located on it, ground-based infrastructure and support. As a lift aircraft, a heavyweight amphibious non-contact take-off and landing amphibious aircraft was used, the engines of which were converted to natural gas. Ground support infrastructure includes several coastal parking areas with hydraulic descent, located in autonomous points of the equatorial ocean coast, independent by weather conditions, near the desert land areas. Achieving a reduction in the pollution of the Earth’s ecology when launching superheavy elements of the system into space. The disadvantages of this invention are the need for a long time to prepare for launch, low reliability and complex requirements for providing a place to prepare for launch and launch of the aircraft.

The well-known "System of air launch of space rockets", RF Patent No. 2268209, B64G 5/00, 04.16.2003, which relates to the launch facilities of space launch vehicles. The proposed system contains a rigid spatial lattice, for example, consisting of several sections, simultaneously horizontally offset relative to the vertical axis of symmetry of the lattice. On the upper nodal points of the lattice, multi-blade adjustable pitch helicopter propellers with an electromechanical high-voltage drive are mounted. On the common axis with them are mounted small-bladed propellers with a jet drive, and around the perimeter of the grate there are propellers with a variable thrust direction, also equipped with an electromechanical drive. High-voltage current-supply wires are fixed to the edge from the axis of symmetry of the grating (in particular, to a separately flying grating with main rotors), and a noise-proof control cabin is mounted on the opposite edge. Slings are attached to the lower nodal points of the lattice, the lower ends of which are attached with the possibility of separation to the device for holding the space rocket. The technical result of the invention is aimed at improving the reliability of launching heavy and superheavy space rockets from the estimated height of their rise in the troposphere. However, the disadvantage of such a system is the need for a long time to prepare for the launch, its complexity, which leads to a decrease in its reliability and economy in operation.

The aim of the present invention is to increase the reliability, safety, efficiency, environmental friendliness of launching a space rocket. The goal is achieved by the simplicity of the technical solution, the cost-effectiveness of its implementation and the time to prepare the launch system for launching a space rocket.

For this, the electric air launch system of a space rocket contains a base with a control system for the electric air launch system of a space rocket and a battery for its power supply. The base is made of a non-rotating ring, to which support rods are fastened at one of their ends, containing at their other ends heels of support rods interacting with catapults containing catapult rotors, the stators of which are placed on support rods, and catapult heels for supporting a space rocket. The upper part of the non-rotating ring with the electric drive of the upper rotating ring is supported on the upper rotating ring with the blades attached to it by means of a magnetic suspension system. The lower part of the non-rotating ring with the electric drive of the lower rotating ring is supported on the lower rotating ring with the blades attached to it by means of a magnetic suspension system. Power supply of the base electrical units is carried out through pantographs, interacting through skids with contact wires attached to balloons, through insulators to the concrete base of the ground platform and connected to the ground power source.

The invention is illustrated by drawings:

FIG. 1 - The moving part of the electric air launch system of a space rocket with a space rocket.

FIG. 2 - Top view of the moving part of the electric air launch system of a space rocket.

FIG. 3 - Electric air launch system of a space rocket with a space rocket in the process of lifting.

FIG. 4 - Electric aerial launch system of a space rocket with a space rocket at the ground site of vertical take-off.

FIG. 5 - Front view in section of a fragment of an electric air launch system of a space rocket.

FIG. 6 - Electric air launch system of a space rocket with a space rocket catapulted from it.

FIG. 7- The movable part of the electric air launch system of a space rocket, decreasing for landing after ejecting a space rocket from it.

The list of elements in the accompanying drawings is as follows:

1 - base;

2 - blades;

3 - non-rotating ring;

4 - upper rotating ring;

5 - lower rotating ring;

6 - upper magnetic suspension of a non-rotating ring;

7 - lower magnetic suspension of a non-rotating ring;

8 - magnetic suspension of the upper rotating ring;

9 - magnetic suspension of the lower rotating ring;

10 - rotor of the electric drive of the upper rotating ring;

11 - stator of the electric drive of the upper rotating ring;

12 - rotor of the electric drive of the lower rotating ring;

13 - stator of the electric drive of the lower rotating ring;

14 - support rod with a catapult stator;

15 - the heel of the support rod;

16 - hinge of the support rod;

17 - catapult;

18 - catapult rotor;

19 - the heel of the catapult;

20 - pantograph;

21 - snake;

22 - space rocket;

23 - a rocket engine of a space rocket;

24 - farm support rocket;

25 - concrete base of the ground platform;

26 - balloon;

27 - contact wire;

28 - insulator;

29 - ground source of power supply.

The electric air launch system of a space rocket includes the following components. Base 1 with a control system for the electric air launch system of a space rocket and its battery power supply (Fig. 1). The base 1 is made of a non-rotating ring 3, an upper rotating ring 4 and a lower rotating ring 5 (Figs. 1 and 5). To the upper rotating ring 4 and the lower rotating ring 5, blades 2 are attached radially from the outside around the circumference (Fig. 2). To the non-rotating ring 3 below are attached through the hinges of the support rods 16 with their ends to the support rods with the stators of the catapults 14 (Fig. 1). At the other ends of the support rods with the stator stats of the catapults 14, the heels of the support rods 15 are made. In the initial position, the catapults 17 rest on the heels of the support rods 15 of the five catapults 19 (Fig. 4). The catapult rotors 18, built into the catapults 17, interact when power is supplied to them through sliding contacts, not shown in the figures, with the catapult stators, made on the supporting rods with the catapult stators 14. The space rocket 22 is supported on the heels of the catapult 19. The upper rotating ring 4 with the blades 2 attached to it, is supported by the upper magnetic suspension of the non-rotating ring 6, the upper part of the non-rotating ring 3 (Fig. 5). On the lower rotating ring 5 with the blades 2 attached to it, the lower part of the non-rotating ring 3 is supported by the lower magnetic suspension of the non-rotating ring 7 (Fig. 5). Pantographs 20 are attached at one end to the bottom of the non-rotating ring 3 of the base 1 (Fig. 4). At their other ends, pantographs 20 are connected through runners 21 to contact wires 27 (Fig. 3), attached to balloons 26, through insulators 28 to the concrete base of the ground platform 25 and connected to the ground power supply 29. The lifting force of the moving part of the electric air launch system of the space rockets create blades 2 rotated by electric drives, consisting of a rotor of an electric drive of an upper rotating ring 10, a stator of an electric drive of an upper rotating ring 11, a rotor of an electric lower drive the rotating ring 12 and the stator of the electric drive of the lower rotating ring 13 (Fig. 5). Moreover, the blades 2 of the upper rotating ring 4 and the lower rotating ring 5 rotate in opposite directions relative to each other. On the ground vertical take-off platform, the movable part of the electric air launch system of the space rocket is supported by the rocket support trusses 24 (Fig. 4).

The operation of the electric air launch system of a space rocket is described as follows. The movable part of the electric air launch system of the space rocket is mounted on the base 25 and is supported by the rocket support trusses 24 (Fig. 4). On balloons 26, the upper ends of the contact wires 27 are raised to a height to which the moving part of the electric air launch system of the space rocket is accelerated. The space rocket 22 is mounted vertically and filled with rocket fuel components. After performing the pre-start operations from the ground-based power supply 29 through the contact wires 27, runner 21 and pantographs 20, the base 1 is supplied with electrical power from the base 1. The upper rotary ring 4 and the lower rotary ring 5 create a movable lifting force by rotating the blades 2 attached to them. parts of the electric air launch system of a space rocket together with the space rocket 22 installed on it. When moving up with acceleration under the action of lifting force the runner 21 slides along the contact wire 27 and through the pantograph 20 provide uninterrupted power from the ground source 29 of the base 1 power generating sets. 10-15 seconds before the end of the contact wire 27, the power of the rotor of the catapult 18 is turned on, which interacts with the stator of the catapult, made on the support rod with the stator of the catapult 14, the movement of the catapult 17 occurs together with the space rocket 22, based on the heels of the catapult 19 relative to the moving part of the electric air launch space rocket system (Fig. 6).

The moving part of the electric air launch system of a space rocket is affected by a force impulse, which reduces the speed of its rise and increases the flight speed of the space rocket 22. After the catapult 17 is released, together with the space rocket 22 from the support rods with the stator of the catapult 14, the catapults fall away from the space rocket 22. Through a few seconds, at a distance of about a kilometer from the space rocket 22 to the moving part of the electric air launch system of the space rocket, reactive engines of a space rocket 23, under the influence of which it continues to fly in an active section to the orbit around the Earth. The electric air launch system of a space rocket under the action of the blades 2 lands on its support rods with the stator of the catapult 14 (Fig. 7), separated to the sides for a stable landing, using its control system in the mode, for example, in the autorotation mode.

Thus, the electric air launch system of a space rocket allows reliable, with the highest degree of environmental and technical safety, economical and operational launch of a space rocket.

Claims (1)

An electric air launch system of a space rocket, characterized in that it comprises a base with a control system for the electric air launch system of a space rocket and a battery of its power supply, made of a non-rotating ring, to which support rods are fastened at one end and containing at the other ends of the heel support rods interacting with catapults containing catapult rotors, the stators of which are located on the support rods, and the heel of the catapults for supporting the space rocket, the upper a fastening ring with blades attached to it, on which the upper part of the non-rotating ring with an electric drive of the upper rotating ring is supported by a magnetic suspension system, a lower rotating ring with blades attached to it, on which the lower part of the non-rotating ring with an electric drive of the lower rotating ring is supported pantographs connected for power supply of base electric generators, interacting via skids with contact wires, fixing coming to the balloons, through insulators to the concrete base of the ground platform and connected to the ground power source.

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