Method of injection of artificial satellites as main and accompanying payloads into geocentric orbit and device for realization of this method

FIELD: rocketry and space engineering; scientific and commercial fields.

SUBSTANCE: proposed method includes placing payloads on injection facility, launching the launch vehicle, separation of injection facility from launch vehicle and injection of injection facility into geocentric orbit where said payloads are separated from injection facility. Main payload is placed on injection facility directly of body of accompanying payload; this body combines its functions with functions of main load-bearing member of adapter system for placing the main payload. After separation of injection facility from launch vehicle, additional acceleration of injection facility is performed and injection facility is injected into reference orbit and then it is shifted to geocentric orbit where main and accompanying payloads are separated. Accompanying payload is separated from injection facility after main payload is at safe distance without waiting for complete turn of main payload. Spacecraft in facility injecting the artificial satellites into geocentric orbit are placed in succession on injection facility beginning with lower one. Main payload in form of one or several spacecraft is placed on body of lower spacecraft through separation device. Body of lower spacecraft combines its functions with functions of adapter load-bearing member for placing the main payload.

EFFECT: increased mass ratio of launch vehicle and injection facility; extended functional capabilities.

3 cl, 2 dwg

 



 

Same patents:

The invention relates to space technology, and in particular to methods of filming the earth's surface from space

The invention relates to the field of space technology, and in particular to methods of filming the earth's surface from space

The invention relates to satellite information systems and, in particular, to systems management communication and relay satellites

The invention relates to satellite systems, mainly regional, communications

The invention relates to a method of implementation of the orbital transfer maneuvers artificial satellites simultaneously to the orbit of one LV

The invention relates to methods for implementation of active-gravity maneuvers artificial satellites simultaneously displayed on the initial orbit one booster

The invention relates to a television technician, and in it - see TV dimensions

The invention relates to satellite information systems and can be used in the construction of telecommunications systems (CTX) wide purpose: to organize or global broadband radio and television broadcasting, collecting, converting and relaying different information in the environment sources and consumers of these data, ground-based or space-based, monitoring of the planet and the near-earth space

The invention relates to space technology, and in particular to inflatable devices passive braking system of the final stages of launch vehicles (LV)

The invention relates to methods of constructing satellite systems, and more particularly to the deployment of geostationary telecommunication systems

FIELD: manufacture of heat control systems of communication, TV broadcasting and retransmission systems.

SUBSTANCE: proposed method includes manufacture of at least three similar thermal load simulators 2 at width of contact surface equal to width of web of heat-transfer agent collector. Heat transfer factors (K1,K2, K3) are determined at similar forces of pressing the contact plate of simulators 2 to skin surface of panel 1. Heat-transfer temperature at collector inlet is maintained equal to surrounding temperature. Said heat transfer factors are determined as follows: for simulator (K1) separately mounted on panel; for simulator (K2) mounted between two adjacent simulators in way of motion of heat-transfer agent; for simulator under conditions when other simulators (K3) are mounted opposite web of adjacent turns symmetrically relative to it. Quality of construction and technology of manufacture is judged from the following relationship: K2+K3-K1-ΔKj ≥ [K], where ΔKj is factor of influence of thermal resistance of joint between simulator contact surfaces and skin on heat-transfer factor; [K] is permissible magnitude of heat-transfer factor.

EFFECT: simplified procedure of check of honeycomb panel quality; low cost of manufacture of panels.

3 dwg

FIELD: communication, TV broadcasting and information retransmission satellites and their heat control systems.

SUBSTANCE: on-board device with concentrated heat source is placed inside inner cavity of heat-insulated closed liquid-radiation heat exchanger and excessive heat from this device is removed to circulating water supply line. Inlet and outlet of liquid cavity of said heat exchanger are connected with delivery and discharge lines of circulating water supply system. Connecting pipe lines are provided with drainage and cutoff valves mounted before inlet and outlet of said liquid cavity below heat exchanger level. Parameters of pipe line running from delivery main of circulating water supply system to inlet of said liquid cavity are selected according to special condition. Box-shaped liquid-radiation heat exchanger consists of two sections with double wall: base and hood; their liquid cavities are communicated with atmosphere through drainage holes provided with shut-off members.

EFFECT: facilitated procedure; reduction of expenses.

3 cl, 5 dwg

FIELD: spacecraft attitude control and mass motion systems.

SUBSTANCE: proposed method includes maintenance of spacecraft attitude by means of powered gyroscopes in the course of correction of orbit by means of jet attitude-control jet engines. Prediction is made for estimation of position of vector of spacecraft momentum of momentum in region of its magnitudes for present and final moments of correction time. Deviation of measured magnitude of this vector from predicted value is maintained within limits of preset region. In case vector does not belong to these regions center of spacecraft mass is shifted depending on configuration of spacecraft inertia tensor and control moment created by attitude-control jet engines. Upon completion of correction, spacecraft center of mass is restored. Proposed method makes it possible to form preset vector of spacecraft moment of momentum at the moment of completion of correction and to minimize number of starts of attitude-control engines in performing the flight program which is necessary for relief of load of powered gyroscopes.

EFFECT: maximum rate of correction at minimum errors of control and minimum consumption of propulsive mass of jet engines.

2 dwg

FIELD: spacecraft attitude control and mass motion systems.

SUBSTANCE: proposed method includes maintenance of spacecraft attitude by means of powered gyroscopes in the course of correction of orbit by means of jet attitude-control jet engines. Prediction is made for estimation of position of vector of spacecraft momentum of momentum in region of its magnitudes for present and final moments of correction time. Deviation of measured magnitude of this vector from predicted value is maintained within limits of preset region. In case vector does not belong to these regions center of spacecraft mass is shifted depending on configuration of spacecraft inertia tensor and control moment created by attitude-control jet engines. Upon completion of correction, spacecraft center of mass is restored. Proposed method makes it possible to form preset vector of spacecraft moment of momentum at the moment of completion of correction and to minimize number of starts of attitude-control engines in performing the flight program which is necessary for relief of load of powered gyroscopes.

EFFECT: maximum rate of correction at minimum errors of control and minimum consumption of propulsive mass of jet engines.

2 dwg

FIELD: optimization and testing of equipment for grouped and associated launches of satellites.

SUBSTANCE: proposed method includes ground experimental optimization of turntable for action of operational loads followed by check of turning system for serviceability and flight and design tests. Ground optimization of turntable is performed together with flight model of adapter. For testing the turntable for action of operational loads on vibration table, use is made of satellite mock-up. Tests for separation of mock-up (in weightlessness state) from turntable fixed in initial position, use is made of standard satellite separation system. Then mock-up is again mounted on turntable and is subjected to test for operation of turning system together with mock-up (in weightlessness state of mock-up and turntable). Flight and design tests of turntable are performed during individual launch of satellite with the use of adapter and turntable after ground experimental optimization. Mass and moment and centering characteristics of satellite correspond to mass and moment and centering characteristics of mock-up for performing ground optimization of turntable. Turn of turntable on adapter is performed after separation of satellite from turntable secured in initial position.

EFFECT: reduction of economical expenses (by 65-70%) and optimization time.

2 dwg

FIELD: space engineering; manufacture and ground servicing of spacecraft temperature control systems.

SUBSTANCE: proposed method includes filling the evacuated hydraulic main of temperature control system with de-aerated heat-transfer agent by forcing it out of filling truck tank by pressure. First, pressure is built up in gas chamber of hydro-pneumatic compensator; this pressure exceeds pressure of pressurizing gas of filling truck tank. After forcing the heat-transfer agent into hydraulic main of temperature control system, gas chamber of hydro-pneumatic compensator is brought into communication with surrounding atmosphere and its liquid chamber is filled with heat-transfer agent. Then, maximum permissible pressure created above heat-transfer agent in filling truck tank is applied to system, after which minimum free volume of gas chamber of hydro-pneumatic compensator is measured and if measured volume coincides with specified magnitude, decision is made on complete filling of hydro-pneumatic compensator and temperature control system as a whole. Device proposed for realization of this method includes on-board valves and the following ground servicing facilities: filling truck with drain and filling mains, valve control units, vacuum unit, gas pressure source etc. Filling truck is provided with drainage tank connected with on-board and ground components by means of definite fittings. Ground servicing equipment includes reference reservoir fitted with absolute pressure gauge and communicated with atmosphere and on-board vent valve of gas chamber of hydro-pneumatic compensator by means of definite fittings.

EFFECT: improved quality of filling due to separate filling of hydraulic main of temperature control system and liquid chamber of hydro-pneumatic compensator.

3 cl, 1 dwg

FIELD: space craft.

SUBSTANCE: proposed engine unit includes two equal-thrust solid propellant brake engines and system of their starting. Solid propellant brake engines are arranged diametrically opposite on cryogenic stage of carrier and are made with equal nozzles and equal diameter chambers. Sizes of grains for each brake engine are related by (D+d2)·L2=(D+d1)·L1 and 1.2·(D-d1)≤(D-d2)≤2.0·(D-d1) where D is outer diameter of grains; d1,d2 are diameters of channels of grains of 1st and 2nd engines, respectively;L1,L2 are lengths of grains of 1st and 2nd engines, respectively.

EFFECT: provision of minimum dynamic disturbances at separation of air space set from cryogenic stage of carrier by means of two brake engines.

2 dwg

Cosmic apparatus // 2252178

FIELD: the invention refers to means of temperature control of cosmic apparatus working on geostationary or high elliptical orbits.

SUBSTANCE: the proposed apparatus has an instrument container, located in a heat-insulation shield fulfilled in the form of a cylindrical sleeve with a cut. One butt-end of the instrument container is connected with the bottom of the sleeve with possibility of turning the shield relatively to the instrument container and a purpose sampling apparatus is installed at the other butt-end of the instrument container. A cylindrical radiator-refrigerant with thermal screen is installed axially to the instrument container through thermal outcome. The cosmic apparatus has a thermo buffer filled with heat-accumulating substance with the melting temperature on the level of the working temperature of the purpose sampling apparatus. The radiator-refrigerant is formed with several heat-insulating one from another sectors. Every part is connected with the butt-end of the element of the instrument container with low thermal conductivity and with the thermo buffet by the way of a thermo diode. The thermo duffer is connected with the purpose sampling apparatus by a thermal tube. A labyrinth seal may be fulfilled in the gap between the radiator-refrigerant and its thermal shield.

EFFECT: increases effectiveness of maintaining of the two-level temperature regime of optical systems of remote probe of the EARTH at voluntary orientations relatively to the Sun.

2 cl, 2 dwg

Cosmic apparatus // 2252178

FIELD: the invention refers to means of temperature control of cosmic apparatus working on geostationary or high elliptical orbits.

SUBSTANCE: the proposed apparatus has an instrument container, located in a heat-insulation shield fulfilled in the form of a cylindrical sleeve with a cut. One butt-end of the instrument container is connected with the bottom of the sleeve with possibility of turning the shield relatively to the instrument container and a purpose sampling apparatus is installed at the other butt-end of the instrument container. A cylindrical radiator-refrigerant with thermal screen is installed axially to the instrument container through thermal outcome. The cosmic apparatus has a thermo buffer filled with heat-accumulating substance with the melting temperature on the level of the working temperature of the purpose sampling apparatus. The radiator-refrigerant is formed with several heat-insulating one from another sectors. Every part is connected with the butt-end of the element of the instrument container with low thermal conductivity and with the thermo buffet by the way of a thermo diode. The thermo duffer is connected with the purpose sampling apparatus by a thermal tube. A labyrinth seal may be fulfilled in the gap between the radiator-refrigerant and its thermal shield.

EFFECT: increases effectiveness of maintaining of the two-level temperature regime of optical systems of remote probe of the EARTH at voluntary orientations relatively to the Sun.

2 cl, 2 dwg

FIELD: locks for developed position of swivel structural members of satellite, solar battery panels or antennae.

SUBSTANCE: proposed device includes articulation with leaf spring secured on its part; spring has hole in its free end; secured as cantilever on other part is rod whose free end may be engageable with hole of leaf spring. Parts are provided with two stops for their engagement in fixed position; one stop is rigid for limitation of relative rotation of parts during opposite motion; other stop is spring-loaded for avoidance of backlash in joints of articulation unit due to elastic forces. As a result, damage of leaf spring is excluded at autonomous opening of swivel structural members at high rotational speeds.

EFFECT: avoidance of backlash in joints of articulation unit.

2 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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