RU2682893C1 - Aerostatic rocket and space complex - Google Patents

Abstract

FIELD: aerospace engineering.

SUBSTANCE: invention relates to the field of rocket and space technology and aircraft lighter than air. Aerostatic rocket and space complex includes a transporting module and a transportable module connected to it via a connection unit. Transporting module contains shells of constant and variable volume, equipped with a buoyancy control system, helium reserves and equipment for its reverse pumping, motors with electric drives, equipped with systems for recharging their batteries, motion control system and devices for moving the transporting and transported modules on the ground. Transporting module is made in the form of a disc-shaped toroidal airship with a rigid folding structure into two identical parts. On the planes dividing the airship into two halves, controlled docking mechanisms are installed.

EFFECT: invention is aimed at expanding the arsenal of tools for launching spacecraft.

6 cl, 6 dwg

Description

The invention relates to the field of rocket and space technology and aircraft lighter than air. It can be used to launch spacecraft (SC) using modified conversion ballistic solid propellant rockets in modified transport-launch containers (TPK).

There is a method of converting military solid-propellant rockets into a solid-propellant space rocket and a space rocket (see RF patent No. 2142898, class B64G, 1999 [1]).

Known space rocket complex and a method of providing services for launching spacecraft using the space rocket complex (see RF patent No. 2179941, CL B64G 1/00, B64G 1/40, 2002 [2]).

The main disadvantage of these technical solutions is the lack of the so-called “zero stage”, which can be considered an airship or plane. The “zero stage” increases the capabilities of a space rocket by bringing it to a certain height before turning on its propulsion system, which allows you to increase the mass of the launched spacecraft or put the old spacecraft into more energy-intensive orbits.

There are known aerospace systems containing a carrier aircraft, a booster rocket (LV) carried out by it and a payload placed in the TPK, a pneumatic landing device, which enables the launch vehicle to exit the carrier aircraft (see RF patent No. 2160215, class B64G 1 / 00, 1/14; F41F 3/06, 2000 [3], RF patent No. 2385829, class B64G 1/00; B64D 5/00; F41F 3/042, 2010 [4], RF patent No. 2399561, class B64G 1/00; F42B 15/00; F17C 3/00, 2010 [5].

The disadvantages of such systems include:

- the use of a carrier aircraft implies a restriction on the mass of the LV transported by the carrier aircraft and the payload, which is due, inter alia, to the need to place a storage system and refueling with fuel components on board the carrier aircraft;

- non-optimal loading of the launch vehicle during its horizontal pneumatic landing from the carrier aircraft and the difficulty of stabilizing the launch vehicle during the free fall period before launching liquid-propellant rocket propulsion systems;

- high risk of operations for refueling and / or refueling with fuel components, including cryogenic ones, during the flight of a carrier aircraft with a crew on board.

Known aircraft missile system, a description of which with the corresponding distinguishing features is given in the patents of the Russian Federation No. 2309090, class. B64G 1/14; B64C 37/02, 2007 [6], No. 2314975, class. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [7], No. 2317920, class. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [8], No. 2317921, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [9], No. 2317923, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [10], No. 2318700, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [11], No. 2319643, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [12], No. 2319644, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [13], No. 2323854, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [14], No. 2323855, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [15], No. 2323856, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 [16], No. 2355601, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2009 [17], No. 2355602, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2009 [18].

Common to the above technical solutions is the presence of an airframe in an aviation missile system, an airplane adapted to tow an airframe using a cable, a launch vehicle for launching a spacecraft and a transport and booster platform for installing a glider on it. At the same time, the transport and booster platform is equipped with a propulsion system (rocket engine of solid fuel), or it is an aircraft with a residual life and service life, modified for the placement and ground transportation of an airframe with LV on it. The glider can be structurally combined with the launch vehicle by adding to the last detachable fairing with the wing installed on it, as well as the nose and tail fairings.

The main disadvantages of this group of technical solutions for the aviation missile system are:

- restriction on the maximum mass of the launch vehicle and the spacecraft launched into orbits;

- insufficient safety of the crew of the aircraft and the aircraft during the launch mission;

- the complexity of the design of the airframe, the placement of launchers and other systems of the aviation missile system, as well as the method of launching the launcher;

- insufficient reliability and complexity of operation of the aircraft missile system;

- the need to perform a large amount of computational and full-scale experimental work on the development of spacecraft launch technology.

The famous High Start project for launching small spacecraft using geophysical rockets and high-altitude airships is known [19]. According to experts, the mass of the launch vehicle with the rocket will be about 350 kg, and the mass of the small spacecraft launched into space will be up to 5 kg [19].

The disadvantages of this project include the insufficient mass of launch vehicles and, accordingly, the launched spacecraft, the inability to launch conversion ballistic missiles of various types with the help of the proposed airship without significant structural changes and modifications.

Also known is an airship for launching missiles, including a shell and a launch shaft. The airship shell is made in the form of a torus, with a rocket installed inside its launch shaft, while the shell and launch shaft are mounted on a rigid platform on which all the airship and rocket launch control systems are located (see RF patent for utility model No. 57239, class B64D 1/00, 2006 [20]).

The main disadvantages of the technical solutions are:

- technical complexity of implementation, insufficient reliability and safety of operations for installing TPK from the spacecraft and spacecraft to the platform inside the volumetric toroidal shell;

- vulnerability of the upper part of the shell of the airship from the thermal effects of the powder pressure accumulator (if it is used to throw the LV out of the TPK) or the products of the combustion of the fuel of the rocket engines of the LV (in case of starting the engines directly in the TPK)

A multi-purpose vehicle of increased carrying capacity (options) is known, including (in accordance with paragraph 5 of the formula (see RF patent No. 2585380, class B64B 1/30; B64D 1/22; B63G 8/14, 2016 [21] )) the transporting module and the transportable module connected to it via the connection unit, while the vehicle uses Archimedean force and engines with propeller propulsion as a propeller. The transport module of the vehicle for high vacuum medium is made in the form of a mobile launch pad. The transported module is the launched object. The transporting module contains a base made in the form of an ellipse, with several groups of shells of constant and variable volume located along its perimeter, equipped with buoyancy control systems, including helium reserves and equipment for its reverse pumping, electric motors equipped with systems for recharging their batteries from renewable energy sources on flowing electric generators, motion control and external control systems and devices for moving trans tailor means land.

The specified analogue, as the closest in technical essence, is taken as a prototype.

The disadvantages of this vehicle include:

- due to the structural complexity and difficult access to the mobile launch pad (through a specially designed dismantled dome structure) in this technical solution:

- the installation of a spacecraft with a space head part (KCH), which includes a spacecraft with an adapter and a head fairing, inside a volumetric toroidal structure using currently existing transport and installation units and docking to the spacecraft of electric and pneumohydraulic connectors is characterized by difficulties in assembling the vehicle components ;

- the safety of maintenance personnel is not ensured when performing technological operations in preparation for the launch of the launch vehicle and spacecraft, especially in conditions of wind impacts;

- in the event of failures, malfunctions, failures on the ground leading to the launch launch being canceled, it is difficult to carry out operations to return the launch vehicle to its original position for subsequent transportation to the technical complex in order to eliminate malfunctions and failures;

- the volume of the dismantled dome structure is approximately two times larger than the stationary dome structures, which can lead to a shift of the center of gravity relative to the longitudinal axis of symmetry of the vehicle, for which compensation it is necessary to apply appropriate additional technical measures;

- there is no provision for thermostating of the KGCH during the launch of the vehicle by the vehicle to the starting point, which significantly reduces the reliability of the spacecraft.

The technical task is to improve the performance (operational manufacturability, safety and reliability) of the aerostat rocket and space complex.

The problem is solved, including due to:

- performing an airship of a disk-shaped toroidal shape with a rigid structure that can be divided into two identical parts, while on the planes dividing the airship into two halves, controlled docking mechanisms are installed to connect the airship parts into a single structure, as well as to connect electrical, hydraulic and gas connectors, and inside The toroidal space of the airship has support belts with automatic assemblies for attaching the TPK to the power frame of the airship and an automatic docking device for docking to communications airship with communications TPK.

- the use of an engineered ground launch pad with a support-holding device placed on it and an airship disassembled into two identical parts;

- the possibility of carrying out operations to install a TPK with a space rocket (ILV), including LV and KGCH, to a support-holding device on the launch pad outside the airship design using standard means of installing TPK with ILV;

- the use of a modified TPK with an opening end cap in the lower part of the TPK, controlled by ILV holding devices in the TPK and supporting belts mounted on the side surface of the TPK;

- application of known means in the airship for creating adjustable aerostatic lifting force, engines with vertical and horizontal thrust propellers, which allow, among other things, maneuvering the airship from the ILV flight path, as well as equipment designed to maintain the specified heat in the TPC internal volume -moisture mode during the rise in the atmosphere to the starting point, pre-launch checks of the ILV on the airship immediately before launch, telemetry transceiver and trajectory No information

- the ability to conduct operations on the ground launch pad to bring the aerostat rocket and space complex to its original state in the event of malfunctions, malfunctions and failures in the components of the complex, including through the use of automatic assemblies for attaching the TPK to the airship’s power frame and an automatic connecting device for the airship’s communications and TPK.

The invention is illustrated by drawings in FIG. 1-6.

In FIG. 1 shows an engineered ground launch pad 1, on which a support-holding device 2 is located, designed to receive the TPK 3 from the transport and installation unit 4 and then hold the TPK in a vertical position.

In FIG. Figure 2 shows the similar positions of the aerostat rocket and space complex at the moment when, using the transport and installation unit 4, the TPK 3 containing the ILV is installed in a vertical position on the support-holding device 2 and is held thereon by means of automated fixing devices 5.

In FIG. Figure 3 shows TPK 3 and ILV as a part of PH 6, KA 7 with adapter 8 and head fairing 9. Moreover, PH 6 has support-leading belts 10 and a board 11 for mechanical uncoupling of ILV communications with TPK communications.

TPK 3 is made in the form of a shell with upper 12 and lower 13 covers and is equipped with supporting belts 14, as well as cable, hydraulic, gas networks and air ducts (not shown in the figure). The lower support belt 15 is designed to install TPK on the support-holding device 2.

The airship and TPK interface is implemented using an automatic docking device 16, which provides multiple implementation of connection-disconnection cycles of cable, hydraulic, gas networks and air ducts of the airship and TPK.

The bottom cover 13 and the controlled holding devices 17 are designed to discharge ILV from the TPK.

In FIG. 4 shows a side view of the aerostat space-rocket complex at the moment when the TPK 3 is mounted on the support-holding device 2 and is held thereon by means of automated fixing devices 5, and two symmetrical parts 18 of the airship are ready for docking with the TPK 3. B the airship includes automatic attachment points 19 of the supporting belts 14 TPK 3 on the supporting belts of the airship, controlled docking mechanisms 20 for connecting two parts of the airship in a single design, controlled docking mechanisms 21 for connecting of the electric, hydraulic and gas connectors, motors with propellers 22 changes its position from horizontal to vertical, retractable wheel chassis 23 with controlled hydraulic suspension.

In FIG. 5 shows a side view of a balloon aerospace rocket complex in the docked position of its components. In this figure, the airship 18 with TPK 3 is ready for lifting into the air, the automated fixing devices 5 (see Fig. 4) are removed.

In FIG. 6 is a sectional side view of the structure of a balloon aerospace rocket and space complex. The base of the airship is a spatial frame 24, consisting of two symmetrical parts and made, for example, in the form of trusses of light alloys. Inside the frame 24 there are soft working shells 25 and soft backup shells 26, a buoyancy control system 27, containers with liquid helium 28, compressors 29, pipelines with controlled valves (not shown), batteries 30, battery charging systems 31, system remote control of the movement of the airship 32, the remote control system for the preparation for launch and launch of the rocket launcher 33, thermostat system of the rocket launcher 34, means for receiving and transmitting telemetry and trajectory information 35, an electric power system Avgazheniya equipment designed to prepare for start-up and start-up of the rocket launcher 36, automatic docking device 16, retractable wheeled chassis 23 with controlled hydraulic suspension, TPK 3. On the outside, the frame 24 is covered with a hard shell made, for example, of light composite materials (not shown shown) and it contains automatic attachment points 19 of the support belts 14 TPK 3 on the support belts 37 of the airship, as well as electric motors with propellers 22.

The operation of the aerostat rocket and space complex is as follows.

The initial state of the aerostat rocket and space complex: a cyclogram of the preparation of spacecraft 7 for launch was carried out; KA 7 is mounted on adapter 8 and closed by the head fairing 9; KGCH is docked to RN 6, forming ILV; ILV checks carried out; ILV is located in TPK 3; TPK 3 is placed in the transport and installation unit 4 in a horizontal position (the listed operations for preparing the rocket launcher for launch are similar to those described in RF patent No. 2179941 [2]); supporting and holding device 2 is ready to receive TPK 3 from the transport and installation unit 4; two parts 18 of the airship are located on the launch pad 1 in places symmetrical relative to the support-holding device 2, prepared for flight and for the operation of docking with TPKZ.

At the command of the head of work, the transport and installation unit 4 with TPK 3 located on it drives up to the supporting and holding device 2 (see Fig. 1). Next, the TPK 3 rises to a vertical position, is mounted on the supporting and holding device 2 and fixed on it with the help of automated locking devices 5 (see Fig. 2), after which the transport and installation unit 4 moves away to such a distance so as not to interfere with subsequent operations by docking parts 18 of the airship with each other and with TPK 3.

After the transport and installation unit 4 has departed to the required distance, the symmetrical parts of the airship 18 begin to move towards each other, while the required height of the airship structure above the surface of the launch pad 1 is set, including by means of controlled hydraulic suspensions of the wheeled chassis 23. In the process of docking of the symmetrical parts 18 of the airship with each other and with the TPK 3, the landing belts 37 of the airship come under the support belts 14 of the TPK 3 and the latter are fixed on the supporting belts 37 of the airship using w automatic attachment points 19. In addition, thanks to controlled docking mechanisms 20, 21 there is a connection of the two parts into a unitary structure airship, as well as connection of electrical, hydraulic and gas connectors airship.

After the formation of a single design of the mobile part of the aerostat rocket and space complex, the automatic docking device 16 is activated (see Fig. 3, Fig. 6), providing a connection of cable, hydraulic, gas networks and air ducts of the airship and TPK.

After checking the correctness of the docking operations, the ILV 34 thermostatic control system is turned on, thereby ensuring the specified temperature and humidity conditions for the LV 6 and KA 7 when the mobile part of the aerostat rocket and space complex is at launch pad 1 and in flight to the rocket launch site.

After a set of launch readiness for the mobile part of the aerostat rocket and space complex at the launch pad 1, the automated fixing devices 5 are removed and the airship ascends (see Fig. 2, Fig. 4). To create an Archimedean force, the shells are filled with 25 or 26 gaseous helium in the amount necessary to lift the airship to a predetermined height. These shells are filled using compressors 29 (see Fig. 6), pipelines with controlled valves (not shown in the figure), tanks with liquid helium 28, and a buoyancy control system 27, which is a functionally subsystem of the airship 32’s remote control system.

Electric motors with propellers 22, changing their position from horizontal to vertical, are designed to create traction in the vertical and horizontal planes. Electric motors 22 are supplied with electric energy from rechargeable batteries 30 connected to recharge systems of rechargeable batteries 31. In addition, recharge systems of rechargeable batteries 31 provide electrical energy to the power supply system of equipment designed to prepare for launch and launch of LV 36 (see Fig. 6) .

When the airship reaches the set launch point of the rocket launcher, if necessary, the remote control system for the preparation for launch and launch of the rocket launcher 33 carries out pre-launch electrical checks of the spacecraft 7 and the launch vehicle 6. Then, the lower cover 13 of the TPK 3 is opened in succession and the controlled holding devices 17 are activated, thereby ensuring conditions ILV discharge from TPK 3 (see Fig. 3). When the ILV moves down from the TPK 3, its support-leading belts 10 are sequentially reset and the board 11 of the mechanical undocking of the ILV communications with the TPK 3 communications is disconnected.

The launch of the rocket engine on solid fuel RN is carried out after the estimated time during which the airship maneuvers from the ILV flight path and begins to return to the launch pad 1. To reduce the airship by the signals of the buoyancy control system 27, helium is taken from shells 25 or 26 and its subsequent compression by compressors 29.

Reception of telemetric and trajectory information from RN 6 and KA 7 can be carried out by measuring points of land, sea and air based, while the means of reception and transmission of telemetric and trajectory information 35 are located on the airship.

Information sources

1. RF patent No. 2142898, cl. B64G 1999

2. RF patent No. 2179941, cl. B64G 1/00; B64G 1/40, 2002

3. RF patent No. 2160215, cl. B64G 1/00, 1/14; F41F 3/06, 2000

4. RF patent No. 2385829, cl. B64G 1/00, B64D 5/00; F41F 3/042, 2010 Bull. No. 10.

5. RF patent No. 2399561, cl. B64G 1/00; F42B 15/00; F17C 3/00, 2010 Bull. No. 26.

6. RF patent No. 2309090, cl. B64G 1/14; B64C 37/02, 2007 Bull. Number 30.

7. RF patent No. 2314975, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. No. 2.

8. RF patent No. 2317920, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. No. 6.

9. RF patent No. 2317921, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. No. 6.

10. RF patent No. 2317923, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. No. 6.

11. RF patent No. 2318700, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. Number 7.

12. RF patent No. 2319643, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. Number 8.

13. RF patent No. 2319644, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. Number 8.

14. RF patent No. 2323854, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. No. 13.

15. RF patent No. 2323855, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. No. 13.

16. RF patent No. 2323856, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2008 Bull. No. 13.

17. RF patent No. 2355601, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2009 Bull. No. 14.

18. RF patent No. 2355602, cl. B64D 5/00, 3/00; F42B 15/10; B64G 1/00, 2009 Bull. No. 14.

19. Makridenko L.A., Volkov S.N., Hodenko V.P. (FSUE "NLP VNIIEM") Conceptual issues of the creation and use of small spacecraft. Questions of electromechanics T. 144. 2010, p. 15-26.

20. RF patent for utility model No. 57239, cl. B64D 1/00, 2006 bull. No. 28.

21. RF patent No. 2585380, cl. B64B 1/30; B64D 1/22; B63G 8/14, 2016 Bull. No. 15.

Claims (6)

1. Aerostat rocket and space complex, including a transporting module and a transportable module connected to it via a connection unit, the transporting module containing shells of constant and variable volume equipped with a buoyancy control system, helium reserves and equipment for its reversible pumping, electric motors, equipped with recharge systems for their batteries, a motion control system and devices for moving the transporting and transported mo beehive on the ground, characterized in that the conveying unit is configured as a disc-shaped airship toroidal shape with a rigid collapsible into two identical parts of the structure, and in the planes separating two halves airship, fitted controlled docking mechanisms. 2. The aerostat rocket and space complex according to claim 1, characterized in that an automatic docking device is installed on the inner toroidal surface of the airship connected to the cable, hydraulic, gas networks and air ducts of the airship. 3. The aerostat rocket and space complex according to claim 1, characterized in that the transported module is made in the form of a transport and launch container for a space rocket containing upper and lower covers, controlled holding devices, support belts, cable, hydraulic and gas networks, air ducts, an external acceptance board of the automatic docking device, and an internal board for the mechanical undocking of communications of a space rocket with communications of a transport and launch container, while m space rocket has supporting-leading belts. 4. Aerostat rocket and space complex according to claim 1, characterized in that the node connecting the transporting module to the transported module is made in the form of support belts located inside the toroidal space of the airship and rigidly connected to the power structure of each of their identical parts of the airship, while the support belts equipped with automatic attachment points of the supporting belts of the launch vehicle on the supporting belts of the airship. 5. Aerostat rocket and space complex according to claim 1, characterized in that the aerostat rocket and space complex includes an engineered ground launch pad, a support-holding device equipped with automated locking devices, a transport and installation unit. 6. Aerostat rocket and space complex according to claim 1, characterized in that the airship onboard equipment includes a remote control system for preparing for launch and launch of a space rocket, a temperature control system for a space rocket, means for receiving and transmitting telemetric and trajectory information, a system power supply of equipment designed to prepare for launch and launch of a space rocket, while devices for moving transporting and transported modules on the ground contain controlled hydraulic suspension wheeled chassis.

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