Settlement in space

FIELD: construction of large-sized structures in space; space engineering.

SUBSTANCE: proposed settlement includes production, living and auxiliary rooms built from lightened modules which are combined in single complex of cylindrical shape with tunnel located along its main longitudinal axis. Said tunnel is embraced by three bodies: main body, body of communication chambers and body of transfer chamber. Pressurized passages are provided between these chambers. Gravitational drive mounted on tunnel is used for rotating the complex in order to form artificial gravity in all rooms. Facing secured on outer surface of guards is used for protection against adverse effect of space. Guards of main body are made from torous members assembled from enlarged space building modules. Main body may be provided with hollow longitudinal and radial stiffening members fastened together and secured to said torous members and to tunnel.

EFFECT: reduced labor consumption and time required for assembly of space structure.

2 cl, 8 dwg

 

The invention relates to a construction in space with the creation of large objects, constructed of large prefabricated elements /special modules, sections, details and so on. prefabrication/United partly on the mounting ukrupnennom in tore Assembly unit.

In STC conditions were provided close to the "earth", is suitable for permanent stay in space humans and animals with the location of housing, services, industries with unique technology and others with providing artificial gravity and protection from the harmful effects of space and areas for a variety of landscape gardening.

It provides the opportunity structures of STC in earth orbit in outer space, using the achievements of cosmonautics General of the Russian high technical level.

For STC for the basis of the adopted technical solution for the application of EN No. 2002102150/11, in which when the guardrail Assembly of the main body instead of separate blocks KSB used made of them enlarged mounting units of the Torah.

In the torus circumference KSB are rigidly United by their ends, as indicated in the patent RU 2088489 registered by Rospatent 27.08.1997,

When this is achieved: reduction of construction time due TO the industrial process by applying the escalation of mounting elements of the torus sleeve forms of estco United KSB.

STC made in the form of a large cylindrical space object-complex /TO/in which United three buildings - the main /GST/body cameras messages /CCF/, the body of the camera transition /MMR/, along the longitudinal main axis of which is omitted tunnel, seized by the actuator artificial gravity, capable of rotating STC and due to the rigid connection of all its elements, to create in all areas of artificial gravity.

In STC, the total resistance provided by the releasing tori longitudinal and radial elements, and protection from the harmful effects of space - facing outer surfaces.

Housing, services, production, etc. posted in STC using the space inside the ISS, and can fit with wykorzystaniem necessary spaces in the internal volume of the complex the application is not included, the message to them is ensured without going into space, mostly hollow structural elements of rigidity, and to interact with arriving ships provided by a temporary disconnection of the hull of the PAC from the case of CCF.

To illustrate the composition and decisions of the STC attached drawings:

Figure 1 is a longitudinal section through 1-1 STC,

figure 2 is a transverse section through 2-2,

figure 3 is a transverse section through 3-3,

4 is a transverse section through 4-4 show ring actuator, mounted n the tunnel - 5,

5 is a transverse section through 5-5,

6 - node And gravitational drive,

Fig.7 is a detail of the drive section 6-6,

Fig - item drive - P, section 7-7.

Description solutions for buildings that comprise the complex STC:

The GST is the main body of STC cylindrical shape composed of:

- enclosing portion of the cylindrical space located in the torus elements made from KSB rigidly produkowany around and the whole lashing hollow longitudinal stiffening elements 3, and a radial hollow elements 4 attached thereto, and the tunnel 5 with the ends together from KSB small diameter 2 attached to items 1, 3, 5, secured to jump in CCF sealed openings 21 and cameras 8;

CCF - body cameras messages cylindrical shape with walls and ceilings collected from KSB small diameter, equipped with sealed openings 21 for transitions within and for the transition in housing - PAC, for rotation which has the engine 10 and the outer circular perimeter /gap Δ/ roller design - 11, on which ships temporarily, PAC, rotating, acquires simultaneous mobility with regard to them;

PAC - body cameras transitions associated with the case of CCF, constantly tightly and ships temporarily disconnected from the STC, with the walls and p is the 9 floors of the cohesive KSB small diameter, features sealed openings 21 and 22 having a mounting device for vehicles;

TUNNEL-5, rigidly associated with PCOS and CCF-razkreposteni 4, 2, 9 and covering its gravitational drive - P, capable of rotating about the longitudinal axis of STC, creating the effect of artificial gravity in all areas TO having attached to it the system indicative of the device - the OS that allows you to take STC desired position in space.

General device, including the transitions within STC through the corridors between 7 by 1, the hollow elements 3, 4, 5, the cameras move in CCF 8, are composed of green areas, sports device with a swimming pool, etc. located on the ceiling, attached to the inside of the toruses 1, can communicate with the spaces in the Torah 1 items 3 and 7, through the chamber 8; P - gravitational drive attached to the tunnel 5, comprising a circular linear electric motor rigidly connected with him, capable of rotating STC around the longitudinal axis, to create artificial gravity in all its areas, and its design includes: the rotor 12 and the permanent magnet 13, a circular stator 14 with a fortified it by lining 15, which sealed the working wire winding freely on the rollers 19 in the composition is chosen to replace the th the U-17 tightened the rods 18 designs, installed in the guide 20, is attached to the tunnel 5, combined with a circular tube balance weight 16 stabilizer his immobility.

When applying the present invention can achieve efficient space exploration, building large facilities, providing a permanent human presence in space, to organize a new space industry capable in their production and services to produce products that are unique and impossible or very difficult to get in "earth", and to get from space inexhaustible amount of energy.

In addition, space exploration can bring much more, for example the production of highly effective medicines and preparations, of great importance in medicine.

It is very important that during the construction rules for settlements possible implementation of green plants /planted/necessary for their population, and the construction of sports facilities may lead, arranging them in water while ensuring the ICR, artificial gravity.

1. Settlement in space, containing industrial, residential and ancillary facilities constructed of lightweight folding space building blocks and combined into a single complex cylindrical form located on its main longitudinal axis of the tunnel, covered in Proc. of the two buildings: the main, the body of the chambers of the message and the body of the camera transition, sealed passages between the buildings, building envelope, attached to the tunnel gravitational drive capable of rotating the complex, providing artificial gravity in all areas that are protected from the harmful effects of space on all outer surfaces of the protective lining and the body of the camera move is capable of when arriving spacecraft to separate from the complex and to rotate independently to ensure immobility on these spacecraft, characterized in that the cladding of the main body is constructed of mounting elements tori performed before the General Assembly of rigidly interconnected integrated these cosmic building blocks.

2. Settlement according to claim 1, characterized in that the main body of the complex is provided with a hollow longitudinal and radial stiffening elements, bonded together, with the specified mounting components-tori and tunnel, and these stiffeners are used for internal navigation.



 

Same patents:

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The invention relates to the organization of construction in Space with the creation of large objects, constructed of large prefabricated elements (special modules, sections, details and so on

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FIELD: spacecraft temperature control systems.

SUBSTANCE: proposed method includes measurement of temperature of spacecraft structural members and onboard equipment and components of rocket propellant, heating them by celestial body heat and conversion of electrical energy into thermal energy as measured temperatures reach low limits of thermostatting range. In flight, intervals of thermal energy accumulation in propellant components (at excess of thermal energy and electric power on board) and intervals of its free liberation are determined. In case expected magnitude of accumulated energy during predetermined interval exceeds upper level for preset volume of propellant, heat of celestial bodies is accumulated till the end of this interval. Otherwise, excess of electric power generated on board is converted into heat which is delivered to propellant components. In predicting release of thermal energy from propellant components, its residual amount required for maintaining the propellant component temperature within required ranges is determined; temperature of structural members and onboard equipment is also measured. In case this temperature exceeds permissible levels, delivery of heat is discontinued. When temperature of propellant component gets beyond threshold magnitudes, removal of heat from propellant components is discontinued. Otherwise, delivery of heat to thermostattable elements and onboard equipment and/or to points of accumulation of heat for subsequent useful conversion is continued till beginning of next interval of accumulation of thermal energy. Then, thermal energy accumulation cycle is repeated.

EFFECT: enhanced efficiency of accumulation and release of thermal energy; reduced mass and overall dimensions; enhanced heat removal.

5 dwg

FIELD: spacecraft temperature control systems.

SUBSTANCE: proposed method includes measurement of temperature in areas of radiation surfaces of temperature control system, comparison of these temperatures with upper and low limiting magnitudes and delivery of heat to radiation surface when temperatures are below low magnitudes. Flight intervals at power requirement exceeding power generated by primary onboard power sources are determined. Amount of electric power consumed for temperature control of radiation surfaces is determined at the same intervals. Flight intervals for maximum possible accumulation of thermal energy on radiation surface in said zones within permissible temperatures are also determined. Expenses for radiation surface temperature control is taken into account. Before beginning of flight intervals at consumed electric power exceeding electric power generated by onboard power sources, heat is delivered to radiation surface zones which require consumption of power for their temperature control at these intervals. Delivery of heat is performed with upper limiting magnitudes of temperatures taken into account.

EFFECT: reduced loading of spacecraft power supply system due to reduced power requirement for radiation surface temperature control at retained preset temperature ranges on these surfaces.

3 dwg

FIELD: spacecraft.

SUBSTANCE: proposed method includes topping up of propellant tank with pressurizing gas and transfer of propellant components from emptied tank into receiving tank. Amount of propellant transferred from emptied tank is determined by ratio depending on pressurizing gas temperature at beginning and end of propellant transfer and temperature and pressure in gas space of emptied propellant tank at end of process.

EFFECT: improved reliability of spacecraft topping up system, simplified design of propellant tank and reliability of its sealing.

1 dwg

FIELD: spacecraft life-support systems.

SUBSTANCE: proposed system includes recoverable reservoir for drinking water whose rigid housing is provided with hermetic movable partition in form of bellows. Reservoir is connected with drinking water and gas sources and with user by means of pipe lines. Piston mounted in housing forms cavity for drinking water together with one of end plates of body and hermetic intermediate cavity with opposite end plate and said partition which is used for placing the changeable cartridges with absorbent for leakage through piston seal. Cavity between hermetic partition and said opposite end plate (interior of bellows) is communicated with gas source which is used for breathing of users. This system is used under weightlessness conditions without pressuring gas.

EFFECT: enhanced protection of reservoir walls and water against contamination with microorganisms.

2 c;, 1 dwg

FIELD: spacecraft life-support systems.

SUBSTANCE: proposed system includes recoverable reservoir for drinking water whose rigid housing is provided with hermetic movable partition in form of bellows. Reservoir is connected with drinking water and gas sources and with user by means of pipe lines. Piston mounted in housing forms cavity for drinking water together with one of end plates of body and hermetic intermediate cavity with opposite end plate and said partition which is used for placing the changeable cartridges with absorbent for leakage through piston seal. Cavity between hermetic partition and said opposite end plate (interior of bellows) is communicated with gas source which is used for breathing of users. This system is used under weightlessness conditions without pressuring gas.

EFFECT: enhanced protection of reservoir walls and water against contamination with microorganisms.

2 c;, 1 dwg

FIELD: cosmonautics.

SUBSTANCE: proposed adapter has body connected with launch vehicle, platform connected with body and provided with strengthening members, seats for micro-satellites located on platform and rigging units. Platform strengthening members are made in form of main and auxiliary beams and cylindrical envelope.

EFFECT: reduced mass of adapter.

8 dwg

FIELD: space engineering; spacecraft for descent in atmosphere of planet.

SUBSTANCE: proposed spacecraft has case with foldable wings and/or stabilizers provided with deployment mechanisms. In folded state at deceleration of spacecraft in atmosphere, said wings and/or stabilizers are covered with separable frontal heat shield which is oval in shape in projection on plane perpendicular to longitudinal axis of spacecraft. Side surfaces of tail section of spacecraft case with wings and/or stabilizers (and some other members) may be covered with separable aerodynamic flaps which form conical surface. After deceleration at initial stage of descent, shield is separated and wings (stabilizers) deploy to working position. Proposed spacecraft has high aerodynamic properties and is provided with reliable protection against aerodynamic and thermal loads at deceleration at high supersonic flight speeds.

EFFECT: low cost of servicing.

4 cl, 13 dwg

FIELD: space engineering; spacecraft for descent in atmosphere of planet.

SUBSTANCE: proposed spacecraft has case with foldable wings and/or stabilizers provided with deployment mechanisms. In folded state at deceleration of spacecraft in atmosphere, said wings and/or stabilizers are covered with separable frontal heat shield which is oval in shape in projection on plane perpendicular to longitudinal axis of spacecraft. Side surfaces of tail section of spacecraft case with wings and/or stabilizers (and some other members) may be covered with separable aerodynamic flaps which form conical surface. After deceleration at initial stage of descent, shield is separated and wings (stabilizers) deploy to working position. Proposed spacecraft has high aerodynamic properties and is provided with reliable protection against aerodynamic and thermal loads at deceleration at high supersonic flight speeds.

EFFECT: low cost of servicing.

4 cl, 13 dwg

FIELD: space engineering; spacecraft for descent in atmosphere of planet.

SUBSTANCE: proposed spacecraft has case with foldable wings and/or stabilizers provided with deployment mechanisms. In folded state at deceleration of spacecraft in atmosphere, said wings and/or stabilizers are covered with separable frontal heat shield which is oval in shape in projection on plane perpendicular to longitudinal axis of spacecraft. Side surfaces of tail section of spacecraft case with wings and/or stabilizers (and some other members) may be covered with separable aerodynamic flaps which form conical surface. After deceleration at initial stage of descent, shield is separated and wings (stabilizers) deploy to working position. Proposed spacecraft has high aerodynamic properties and is provided with reliable protection against aerodynamic and thermal loads at deceleration at high supersonic flight speeds.

EFFECT: low cost of servicing.

4 cl, 13 dwg

FIELD: devices for coupling and uncoupling spacecraft modules.

SUBSTANCE: proposed unit includes first and second parts of connector and plate. First part is secured on first compartment and second part is secured on second compartment. Plate is mounted on second compartment by means of rods; it has hole and may move in plane passing through axis of coupling of first compartment. Rods are spring-loaded relative to each other for adjustable axial motion; they are provided with travel limiters and are engageable with plate and second compartment by means of articulated bearings. First part of connector is provided with cover for closing this part on side of second part after uncoupling. Plate has hole with stops mounted on opposite sides of this hole in plane of motion of plate; these stops are engageable with second part of connector by their spherical tips. Pin and dowel are secured in this part. Pin is mounted at spaced relation in hole of plate and bearing member of pin forms clearance between its inner bearing surface and plate. End of pin projecting above second part of connector is engageable with first part lengthwise.

EFFECT: enhanced reliability of coupling and uncoupling electrical connector under operating loads.

4 dwg

Descent spacecraft // 2244665

FIELD: rocketry and space engineering; small descent spacecraft injected into orbit by ballistic missiles removed from combat duty.

SUBSTANCE: proposed descent spacecraft has case, control members for its orientation in space and units for coupling with launch vehicle. Plane of connection of descent spacecraft with launch vehicle coincides with transversal plane of symmetry of case of spacecraft and its diameter coincides in this plane with transversal diameter of launch vehicle. Descent spacecraft case is made in form of body obtained by rotation of oval around its larger axis and said plane of connection with launch vehicle coincides with plane of smaller axis of oval.

EFFECT: increased volume of descent spacecraft at limited transversal diameter of launch vehicle.

1 dwg, 1 tbl

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