RU2790478C1 - Reusable space aircraft - Google Patents

Abstract

FIELD: space technology.

SUBSTANCE: invention relates to reusable space aircraft (RSA) flying in space both around the Earth and in interplanetary space. The RSA contains three stages, each of which consists of eight modules, twelve lifting propeller power plants (LSPP) with in-flight folding propellers located in the upper part of the power modules, the rotation of the blades of which from vertical to horizontal position and vice versa is carried out by mechanisms, solid-fuel rocket engines (SFRE), including acceleration and braking, eight turbofan engines (TFE) with fuel tanks installed at the bottom of the power modules of stage I, aerodynamic surfaces installed on all stages to create lifting power with diving rudders and aerodynamic surfaces with jaw rudders, docking devices for connecting the stages to each other and access through the door hatch of the retractable telescopic tube from the lower stage I to the upper stage III when getting through an access tube installed in each central module, landing devices of stage I and landing devices of stages II and III, which are installed on each stage from the bottom of power modules equipped with LSPP.

EFFECT: expansion of the range of solutions to build reusable space aircraft.

1 cl, 7 dwg

Description

Technical field

SUBSTANCE: invention relates to reusable spacecraft (SCV) flying in space both around the Earth and in interplanetary space.

Prior Art

MKLA are known, in particular, the Falcon9 space launch vehicle of the American company SpaceX, the first stage of which (possibly the second) can be used several times to launch spacecraft, as well as the Roton C - 9 spacecraft with a turboprop landing system, authored by American engineer Gary Hudson. The main disadvantage of the above-mentioned SCLAs is the impossibility, due to the high temperatures and speeds of the jets from the engine nozzles, to take off and land without the use of special ground equipment and launch pads, although the Roton spacecraft is provided for landing due to the turboprop system.

In addition, due to the large longitudinal dimensions of the steps during a vertical landing, they may overturn, which reduces the reliability of the SMAC.

Also, significant disadvantages of these reusable manned launch vehicles, for example, the Falcon type, designed to deliver people, for example, to the planet Mars, is that the problems of a long-term stay of a person in outer space, including the problem of weightlessness, have not been solved.

These shortcomings, in particular, ensuring a sufficiently reliable landing, long-term stay in space due to the creation of artificial gravity, are resolved in the application for the issuance of a Russian patent for the invention of a manned spacecraft (PCLA) No. 2020142840 dated 12/23/2020.

The main disadvantage of PCLA is the following.

Its design, consisting of modules, is assembled in space in near-Earth orbit. At the same time, the delivery of each module into orbit using launch vehicles is accompanied by huge costs associated with high fuel consumption, the use of a large number of launch vehicles, and the loss of its stages. In addition, to launch launch vehicles, it is necessary to use expensive ground equipment: launch pads, service masts, etc.

These and other above-mentioned shortcomings are eliminated in the design of the proposed MKLA.

Disclosure of invention

The objective of the present invention is to develop a design of a multi-stage SMAC with improved performance, where a set of parallel modules in the amount of nine pieces (for example) eight of which are evenly located in a circle and which are connected with one (ninth) module in the center of the circle are used as steps (central module) according to the PKLA type.

The objective of the invention is also to ensure the mode of operation of the SCLA, including reusable landing and takeoff of stages from unprepared surfaces of the Earth and other planets, using air gas turbine engines for flight in the atmosphere.

In addition, the objective of the invention is to develop structures for the stages of the SCLA, capable of autonomous assembly (docking) with each other both on Earth (and on another planet) and in space flight. In this case, the assembly (manufacturing) of the step modules is carried out in terrestrial conditions.

To solve these problems, the SCLA, containing two, three or more stages of a longitudinal arrangement, each of which is a set of interconnected modules, liquid or solid propellant rocket engines mounted on stage modules, universal landing devices, docking devices according to the invention:

- made of two, three or more universal steps, consisting of a set of parallel modules arranged in a circle, connected by radial connections with the central module of the step;

- SCLA stages are assembled together by means of docking devices located at the ends of the central modules;

- part of the stage modules arranged in a circle are equipped with lifting propeller power plants (PVPU) with lightly loaded propellers folding in flight;

- turboprop engines (TVD) or lifting propellers with a jet drive from a hydrogen peroxide gas generator (steam gas generator) similar to the turboprop system of the Roton-9 spacecraft can be used as PVSU;

- modules of the first stage, in addition to PVSU, have air gas turbine engines of the turbofan type (TVLD);

- radial links in each stage are aerodynamic surfaces with elevators and rudders, as well as streamlined airfoils.

Such a device for the MCLA makes it possible to significantly simplify its design due to the use of universal stages.

At the same time, stages with parallel interconnected modules, which make it possible to reduce the height of the SLBM structure by 3–4 times compared to rockets with longitudinal arrangement of stages, and increase its width (diameter) by the same amount and, as a result, ensure stability during takeoff and landing.

In addition, in connection with the use of PVSU, the need to use ground equipment for launching space launch vehicles (launch pads, service masts, etc.) is eliminated. SMSC launch can be carried out from any natural site, which will allow several times to reduce the cost of launching launch vehicles, including reusable ones.

The loss of stages is also excluded, since each of them can be reliably and safely returned to Earth due to the use of TVLD and PVSU.

The use of aviation air gas turbine engines will allow several times to reduce the cost of launch, and increase the weight return on payload up to 20% (instead of 3 ... 5% for currently used launch vehicles).

The use of aerodynamic surfaces installed at each stage will provide additional lift during takeoff and controlled flight in atmospheric conditions.

The design of the MCLA makes it possible to create near-Earth orbital stations with large volumes of living space, providing artificial gravity and radiation protection.

And, finally, the manned version of the MCLA can provide reliable and safe delivery of people to other planets, in particular to Mars, with their subsequent development by humans for habitation.

According to the information available to the applicant, the totality of the essential features of the claimed MCLA are not known from the prior art, which allows us to conclude that the invention meets the criterion of "novelty".

According to the applicant, the essence of the claimed invention does not follow mainly from the prior art, since it does not reveal the above effect on the achieved technical result - new properties of the object - a set of features that differ from the known space aircraft (PCLA, Roton spacecraft) , which allows us to conclude that it meets the criterion of "inventive step".

The set of essential features that characterize the essence of the invention can be reused in the production of small-scale aircraft, the design of which is made of several stages, the modules of which, in addition to rocket engines, are additionally equipped with aircraft air bypass gas turbine engines of the TVLD type and low-load propellers PVSU with obtaining a technical result consisting in the simplification of the design of the SLAV, the reliable and safe delivery of a person to other planets, a significant reduction in the operating costs of the SLV compared to existing space LA, which allows us to conclude that the MKLA meets the criterion of "industrial applicability".

The invention is illustrated by drawings, which show:

In FIG. 1 - MKLA, side view in section. A-A;

In FIG. 2 - MKLA, plan view;

In FIG. 3 - modules of stage I MKLA:

a) power module equipped with PVSU and TVLD;

b) power module equipped with solid propellant rocket motor and TVLD;

c) central module, equipped with solid propellant rocket motor;

In FIG. 4 - MKLA modules of stage II MKLA:

a) power module equipped with PVSU and solid propellant rocket motor;

b) power module equipped with PVSU and solid propellant rocket motor;

c) central module equipped with solid propellant rocket motor;

In FIG. 5 - MKLA stage III module converted into a toroid:

In FIG. 6 - stage III MKLA power module, equipped with solid propellant rocket motor and PVSU with a jet propeller drive, also characteristic of PVSU I and II stages;

In FIG. 7 - take-off and landing flight paths of the MKLA and its stages.

A three-stage SMSC is considered as an example, the configuration of the stages of which are identical to each other with the difference that stage I, in addition to PVSU and rocket engines, like the rest of the stages, is equipped with TVLD-type air gas turbine bypass engines.

MKLA contains stages I, II and III, each of which consists of eight modules, including power modules 1 and household modules 2 with their parallel arrangement in a circle, a central multifunctional module 3, radial connections 4 in the form of streamlined profiles connecting each circular module with the central module with the help of docking devices 5, which additionally at stage III ensure the rotation of the modules from a vertical to a horizontal position until the modules come into contact with each other to form a toroid (Fig. 5), twelve PVSU 6 with propellers 7 folding in flight, located in the upper parts of the power modules 1, the rotation of the blades of which from vertical to horizontal and vice versa is carried out by means of mechanisms 8, solid propellant rocket engines (SSRM), including accelerating 9 and brake 10, eight TVLD 11 with fuel tanks 12 installed below the power modules 1 stage I, 13 aerodynamic surfaces installed on all stages to create lift force with rudders 14 and aerodynamic surfaces 15 with rudders 16, docking devices 17 for connecting the steps to each other and access through the door hatch 18 of the retractable telescopic tube 19 from the lower stage I to the upper stage III when landing through a pipe - manhole 20, installed in each central module 3, landing devices 21 of stage I and landing devices 22 of stages II and III, which are installed on each stage from below the power modules 1 equipped with PVSU, removable in flight fairings 23 power modules 1 and removable or folding fairings 24 of the central modules 3.

In FIG. 6 (for example) shows the stage III power module (also typical for stages I and II) with an elevating screw 7 PVSU with a jet drive, which includes a sleeve 25, nozzles 26, a gas generator 27, a fuel tank 28 with hydrogen peroxide.

In FIG. 7 shows the takeoff and landing flight paths of the SMV as a whole and its stages.

Flight paths 29 and 30 are take-off, 31 are the stage III orbital near-Earth flight path, and trajectories 32, 33 and 34 are landing stages I, II, and III separately to Earth 35.

The operation of MCLA with reusable use of both stages and their modules is carried out as follows.

The command crew and other cosmonauts are boarded in a completely ready-to-flight SCV, filled with fuel to ensure the operation of the PVSU and TVLD and equipped with solid propellant rocket motors, through the door hatch 18, which are taken in turn through the pipe - manhole 20 using an elevator (not shown) to the stage III cabin . This is done if the MKLA is manned.

In this case, the MCLA relies on four landing devices of the 21st stage I.

The take-off of the SMAC is carried out vertically from any platform due to the thrust of all lifting screws 7 PVSU 6 and the thrust of all TVLD 11. Before takeoff, the PVSU is first turned on, the propeller blades of which are set from the folded position to the open operating position due to the mechanisms 8. Then using the thrust of the nozzles 26 , into which gas is supplied under pressure from the gas generator 28, running on hydrogen peroxide, located in the fuel tank 27, the propellers 7 are spinning up with the formation of the necessary lifting thrust. After that, the TVLD is switched on with the formation of lifting thrust as well. The incoming air flow from the PVSU is mixed with the gas-air flow from the TVLD, reducing the speed and temperature impact on the take-off area to an acceptable level.

At an altitude of 100...200 meters, the SCLA changes from a vertical position to a horizontal one with an aircraft climb, while the vertical component of the thrust of the TVLD and propellers 7 PVSU is added to the lift from the aerodynamic surfaces of 13 steps I, II III. At the same time, the control of the MKLA in height and direction is carried out, respectively, due to the rudders 14 and 16.

Upon reaching the flight speed of 150...200 km/h, the PVSU is switched off and the propeller blades are folded along the power modules 1 at all stages.

At the next stage, at an altitude of 10 ... 15 km, TVLDs are switched off with the simultaneous switching on of upper stage solid propellant rocket engines 9 of stage I, although they can be switched on earlier when flying in the atmosphere. In this case, a part of the stage II booster solid propellant rocket motors can also be included. Upon reaching a flight altitude of 100 km, stage I is undocked. Further flight is carried out due to the thrust of upper stage solid propellant rocket engines of stage II with its launch together with stage III into a near-Earth orbit, where stage II is undocked and stage III is flown.

After stages I and II are undocked, they are controlled to descend to the earth's surface (Fig. 7).

Stage I after undocking turns on braking solid propellant motors 10 and at a speed of 1000…1500 km/h and an altitude of 10…15 km solid propellant motors are turned off and TVLD 11 is switched on with a decrease in altitude and speed with the direction of landing to a given point. Upon reaching a flight speed of 150...200 km/h, the PVSU is switched on with simultaneous disconnection of the TVLD, and from a height of 50...100 m, the vertical landing of the SCLA stage occurs due to the thrust of the PVSU propellers to a given site using landing devices 21 (Fig. 3).

Stage II after undocking also includes braking solid propellant rocket motors 10 and performs a controlled descent, preventing overheating of the structure in dense layers of the atmosphere. Also, upon reaching the flight speed of 150...200 km/h and from a height of 50...100 m, the landing of the SCLA stage is performed due to the thrust of the PVSU propellers using the landing legs 22 (Fig. 4).

After returning to Earth, stages I and II are refueled, they are also equipped with new solid propellant rocket motors and docked with a new stage III. After assembling all the stages, checking all the systems, the MKLA is ready for a restart.

Docking stages of SCLA in terrestrial conditions using docking devices 17 can be carried out both by means of lifting means and by using lifting screws 7 PVSU 6.

While in low-Earth orbit or making long-term flights to other planets, stage III, due to the rotation of the modules around the axes of radial bonds and their docking with each other due to docking devices, 5 are converted into a toroidal structure - a toroid, which is then driven into rotation around the central module in order to create the necessary artificial gravity (similar to the PCLA), if the UCLA is in the manned flight mode.

Thus, stage III is a spacecraft and can act as an orbiting Earth space station or an interplanetary spacecraft and can also independently land on Earth, as well as land and take off on other planets in the solar system. Of the eight modules of the toroid, four pieces are power units, which are equipped with lifting PVSU and LRM, and four pieces are designed to accommodate astronauts, equipment for life support, etc. In the central module of stage III, a rotating capsule with a command crew (similar to the PCLA) is located in the upper part and in the lower part - solid propellant rocket motor.

The proposed MKLA, the stages of which are made of universal modules arranged in parallel for the most part, interconnected and equipped, in addition to rocket engines, additionally with aircraft air gas turbine engines and lifting propellers, can perform multiple takeoffs and landings both in terrestrial and extraterrestrial conditions without using expensive launch equipment, also ensure reliable and safe long-term flights both in near-Earth orbit and in space interplanetary space, which allows us to draw a conclusion about the "industrial applicability" of MKLA.

Claims (1)

A reusable spacecraft (SCV) containing two, three or more stages of a longitudinal arrangement, each of which is a set of interconnected modules, liquid or solid propellant rocket engines mounted on stage modules, universal landing and docking devices, characterized in that MKLA contains three stages, each of which consists of eight modules, including power modules and household modules with their parallel arrangement in a circle, a central multifunctional module, radial connections in the form of streamlined profiles connecting each circular module with the central module using docking devices that provide additionally, at the third stage III, the modules are rotated from a vertical to a horizontal position until the modules come into contact with each other to form a toroid; th modules, the rotation of the blades of which from a vertical to a horizontal position and vice versa is carried out by mechanisms, solid propellant rocket engines (SSRM), including accelerating and braking, eight turbofan engines (TVLD) with fuel tanks installed below the stage I power modules, installed on all airfoils for creating lift with elevators and airfoils with rudders, docking devices for connecting the steps to each other and access through the door hatch of the retractable telescopic tube from the lower stage I to the upper stage III when landing through a manhole pipe installed in each the central module, stage I landing gears and stage II and III landing gears, which are installed on each stage from below the power modules equipped with PVSU, removable power module fairings in flight and removable or folding central module fairings.

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