Cosmonautic vehicles (B64G1)

B64G1/12 - anned(30)
B64G1/14 - Space shuttles(108)
B64G1/26 - Using jets(79)
B64G1/34 - Using gravity gradient(20)
B64G1/68 - Of meteorite detectors(8)

Spacecraft accomplished by a deorbit device, comprising a detonation engine // 2628549
FIELD: aviation.SUBSTANCE: spacecraft (SC) comprises at least one rocket propellant main tank, main drive motor, powered by a rocket propellant from the main tank, and a deorbit device. A deorbit device comprises a detonation engine powered by a rocket propellant from the main tank. A spacecraft launch vehicle comprises at least one stage formed by the noted spacecraft. In the spacecraft deorbit way the deorbit action is carried out after the main drive motor stoppage with the application of the detonation engine fueled by a propellant from the main tank under a pressure less than or equal to 10 bar. In the spacecraft deorbit way, that forms a deorbit device stage, the mentioned stage is detached from a launch vehicle after the main drive motor stoppage.EFFECT: guarantee of the spacecraft deorbit with the application of the propellant from the main tank and, hence, spacecraft weight-saving.12 cl, 3 dwg
ethod for protecting space apparatus against collision with intentionally appropriate active object // 2628542
FIELD: aviation.SUBSTANCE: method of protecting a spacecraft from collision with an intentionally approaching active object, according to which the screen is released when a continuous sequence of signals with an increasing amplitude is detected, and the direction of the screen is determined from the spatial orientation of the detectors with the maximum amplitude of the detected signals among the set of planar detectors on the surface Two spherical shells, which are installed on a protected spacecraft and on a small space apparatus accompanying shielded spacecraft.EFFECT: ensuring high reliability of identifying potentially dangerous situations and increasing the speed of implementation of protective measures.1 cl

ethod of space rocket movement control, while insertion space objects to the orbit // 2628412
FIELD: aviation.SUBSTANCE: method of space rocket movement control, while insertion the space objects to the orbit is, that at the given moments of time the current position of the space rocket is determined by means of the navigation system, the remaining flight path with the previous control is predicted by the on-board digital computer and determine the feasibility to provide the terminal flight conditions with the specified accuracy and, if these conditions are not feasible, choose the new control and implement it with the help of the executive bodies until the next, specified time of flight, in addition, choose the new terminal conditions, that are in the of space rocket reachability field, and the new control over the space rocket movement and realise it with the help of the executive bodies until the next, specified time of flight.EFFECT: increase of the placing space object functioning efficiency.1 dwg

Docking unit of detachable objects of aircrafts // 2628282
FIELD: aviation.SUBSTANCE: docking unit of detachable objects of aircrafts (AC) contains a body with clamps to fix the detachable element on a spherical surface. Each clamp is a sleeve containing a plunger stop, held in the sleeve by a ball lock. The plunger stop is based in the sleeve along the conjugate diameters, which form the differential area of the actuator for removing the fixation of the junction of the detachable objects. The activation of the clamps is provided by the simultaneous supply of pressure to the ball-type locks, which release the plunger stops. Detaching objects is carried out by moving the plunger stops.EFFECT: reliable docking of aircraft objects without stresses from the allowed and possible deviations of the objects to be docked.2 dwg

Rocket stage with liquid drive system // 2628272
FIELD: aviation.SUBSTANCE: in the rocket stage for launching the spacecrafts, containing at least one tank for separate storage of fuel and oxidant, the engine, the engine mount frame and the basic structure, connecting different components to each other, the engine mount frame is at least partially installed inside the tank. The fuel loading and transport devices are provided inside the tank. The engine mount frame partition inside the tank is absolutely sealed and divides the tank into separate areas with separate fuel components. The partition inside the tank is conical, it may have elliptical or hemispherical dome-shaped parts and cylindrical intermediate part.EFFECT: reduction of the weight-size characteristics of the rocket stage.26 cl, 11 dwg

ethod and device for collecting objects in space with rings and lattice surfaces and method of conclusion of objects in space with flexible, for example, mesh-membrane surfaces // 2627904
FIELD: aviation.SUBSTANCE: useful cargo (UC) in the form of ring or panel space power stations, radio telescopes with a lattice (net) surface, etc. Have significant dimensions (>100 m) And complex configuration. Such UCs are triggered with silhouette stages and rocket engines, evenly distributed on the silhouette stages or directly on the UP along the contour and/or surface of the UP. The UP is returned by atmospheric and planning braking, using, in particular, the effects of the lattice wing and the ring plane for the corresponding configurations of the UP.EFFECT: expansion of functionality and increase of effectiveness of methods and means of launching into space and return of these non-standard payloads.20 cl, 11 dwg

ethod and device for multiple launching to space and return of oversized cargo and method of use of oversized cargo on other planets // 2627902
FIELD: aviation.SUBSTANCE: output oversized cargo (OC) is girdled with steps of toroid-shaped carriers repeating the outlines of OC. The rocket motors of the stages create thrust uniformly along the equator of the tori. The fairing of the OC and other shell elements (for example, the central body of the lower part of the rocket system of the carrier) is carried out by a gas-supported circuit using (heat) strong fabrics, films or foil. When the shells are supercharged with helium, an aerostatic force is created in the flight section in the atmosphere. When using capsules in the form of a "headlight" for the descent of NG, on the surface of the celestial body, multi-dome objects with a common internal space can be created by tightly connecting the capsules to the cutouts of their side walls.EFFECT: expanding the functionality of carriers of oversized cargo and reducing the costs that are required for launching into space, operation, and return of oversized cargo.9 cl, 8 dwg
ethod of minimizing zones of detachable parts exclusion of carrier rocket // 2626797
FIELD: weapon and ammunition.SUBSTANCE: in the method of minimizing the exclusion zones for the detachable parts (DP) of the carrier rocket (CR) during the pre-flight preparation stage, the CR calculates the parameters of the motion of the DP before they fall to the ground. Based on the results of the calculations, the sections on the descent path for impact on the DP are determined, they form a signal in the process of an autonomous DP flight, and effect the design of the DP. The pyrotechnic composition is placed on the DP. During combustion, the pyrotechnic composition ensures heating of the DP to a temperature at which their combustion takes place in the incoming flow of atmospheric air, after reaching a height of 25-30 km, the ignition of the DP is carried out using an igniting composition.EFFECT: maximum reduction of areas allocated for the areas of incidence of the DP CR.6 cl, 1 tbl
ethod of payload delivery to celestial body soil, provision for soil and celestial body exploration and device for its implementation (versions) // 2626792
FIELD: aviation.SUBSTANCE: invention relates to methods of payload delivery - of a scientific package to celestial bodies (planets, asteroids, comets, etc.) for their exploration and penetrator-device with payload, separated from the main space vehicle and representing an impact penetrating probe, penetrating into the soil of the celestial body for the exploration of the body and soil parameters. The invention provides a method for delivering payloads to a celestial body and a device for its implementation, according to which a payload is placed inside a ballast serving as an additional protective body for the payload, and high-strength ice modifications, such as ice-VII or ice-VIII, or ice-X, are used as the ballast material. After the impact penetration of the penetrator into the soil, the ballast and the scientific package in it are freed out of the protective casing, the ballast is removed, releasing the payload, and the soil of the celestial body is explored.EFFECT: increased impact resistance of the payload and higher measurement accuracy of the soil and celestial body parameters.10 cl, 5 dwg

Descent tow vehicle for retrieving space objects from orbits // 2626788
FIELD: aviation.SUBSTANCE: descent tow vehicle for removing objects from the orbits of artificial earth satellites contains a cargo container having a free volume for placing the object to be retrieved, an inflatable braking device with a flexible hermetic heat-resistant shell, adapted to obtain an aerodynamic shape when it is filled with gas. In this case, the inflatable braking device has outer contours in the form of a truncated cone and is made in the form of a set of torus-shaped elements. The device also contains a device for capturing the object to be retrieved, a navigation system for searching for the object to be retrieved from the orbit and a propulsion system for maneuvering the vehicle. The device for capturing the object to be retrieved is made in the form of truncated cone sectors, and the free volume for placing the object to be retrieved is in the form of a conical flare.EFFECT: expansion of the arsenal of space technology by introducing a simple descent tow veihicle for the rapid retrieval of objects from the orbits of artificial Earth satellites.2 cl, 3 dwg
ethod of selecting grades of optical glasses for design of space equipment optical systems in long-term exposure conditions of space ionising radiation // 2626450
FIELD: physics.SUBSTANCE: method involves calculating, according to a known technique, the dose distribution of ionising radiation from outer space on the optical axis of each glass element of the optical system under operating conditions, taking into account the protective properties of the structure. Next, using computer algebra, the spectral density of these elements is calculated on the basis of the average dose rate of ionising radiation on the said optical axis and the characteristics of the kinetics (formation and relaxation) of the radiation colour of the glass of the element are calculated. The increase in the optical density of the optical system and the corresponding decrease in the spectral transmission coefficient of the optical system are determined. The reduction of this coefficient is compared with the permissible one and, if necessary, the optical glass grades are replaced in the elements with the maximum increase in the spectral optical density.EFFECT: optimisation of optical systems by preliminary estimation with the increased accuracy of decreasing their spectral transmittance during the period of active existence.1 cl
Aqua aerospace vehicle // 2626418
FIELD: aviation.SUBSTANCE: aqua aerospace vehicle includes the body in the form of the biconvex lens, covered with the bottom and the top by the hemispheres of titanium aerodynamic fairings. The body is supported by the steel frame with stiffeners, on which the power unit is mounted. This unit contains four groups of engines: four lifting cruise bypass turbojets, two main rocket engines, four rocket engines of vertical lift and two water-jet engines. The air vehicle has the landing gear legs. The sealed gateway hatch is served for docking and communication with the interplanetary space station (ISS). There are the rear hemisphere lights and the aircraft lights on the vehicle body.EFFECT: creation of the multimode multifunctional vehicle for researches and other operations in near and far space, using for its refuelling the interplanetary space station and celestial bodies.11 cl, 11 dwg

ethod of spacecraft inertial actuators kinematic momentum drop and device for the method realisation // 2625687
FIELD: aviation.SUBSTANCE: group of inventions relates to controlling the spacecraft relative motion by its interaction with the geomagnetic field. In the method, the components of the kinematic momentum accumulated by the spacecraft inertial actuators and geomagnetic induction along the X, Y, Z axes are determined. According to these data, the signals of the unloading magnetic momentums along each X, Y, Z axis are formed. The device includes the sensors of the specified components of the kinematic moment and geomagnetic induction, connected to the control unit inputs and magnetic IO for the unloading magnetic momentums formation. Three digital-to-analog converters, three comparators, three "I" elements, three electronic switches, providing the formation by the magnetic IO of optimal along the X, Y, Z components of unloading momentums geomagnetic induction are also introduced.EFFECT: reduction of power consumption and heat generation by the magnetic actuators.2 cl, 2 dwg

Adjustable constuction attaching lug with interface on slings // 2625211
FIELD: aviation.SUBSTANCE: unit contains internal and external parts and two sets of fasteners. The internal part has a composite (carbon fiber) pad with slings (17), bolted between the cover plate and the bracket. The latter are fixed together by fastening elements in the form of pins, nuts, spherical washers, external and internal threaded bushings. The external part has spacers (8) installed on the outer side of substructure body (SSB) of space vehicle (SC) (18) and by screws (10) connected to mating parts on the inner side of SSB (18). Edges of the spacers (8) and the mating parts repeat the direction of SSB edges (18). The support plate is attached to the spacers (8) with bolts (6) and spring undular washers (7).EFFECT: ensuring uniform tension of slings, increasing the range and increasing the accuracy of adjusting their tension, increasing the flexibility of attaching lug, reducing the weight and reducing the dimensions of fasteners set.6 cl, 7 dwg

Cover unit of the aircraft visual optical system // 2624973
FIELD: aviation.SUBSTANCE: unit includes the cover, provided with the electric drive with the output shaft. One end of the shaft is kinematically rigidly connected to the cover by means of two mating gear half couplings with even and odd number of teeth. The adapter is provided between the half couplings, the number of teeth of which from the half coupling side interacting with it is equal to the number of teeth of this half coupling. The half coupling with the odd number of teeth is made with ability of axial movement relatively to the output shaft, while the preflight training of the cover unit is carried out. The half coupling with the even number of teeth is rigidly attached to the cover. The other end of the electric drive shaft is connected with the cover by means of the split bushing. The inner diameter of this bushing, while loosening the clamp, is more than the shaft output end outer diameter.EFFECT: simplification of the preflight training of the mentioned cover unit by eliminating the equipment for its weightlessness.6 dwg

Adapter for way loose of useful load // 2624959
FIELD: physics.SUBSTANCE: invention relates to the structural elements of payloads (PL), in particular, microsatellites. Adapter includes a farm with two tiers of triangular lattices: the upper tier is made in the form of a cylinder, and the lower one is in the form of a truncated cone. The support nodes (4, 8) form the upper and lower belts. The layers are joined through the support units of the intermediate belt. The first means (10) for fastening passing MD (41) contain boxes in the form of boxes. Their bottom panels can be provided with projections for the installation of control units (42) by the separation of the MD (41). The second securing means (20) of associated MD (41) comprise a framework in the form of a straight triangular prism fixed to the lower tier of the truss. The securing means (10, 20) allow the separation of the MD (41) in the lateral direction relative to the axis (40).EFFECT: reducing the weight of the adapter to remove a significant number of microsatellites of the Kubsat class, in the presence of a point joint of the adapter with the accelerating unit and the main payload.5 cl, 17 dwg

System of astronaut fixation while moving along the external surface of space object (versions) and the method of its operation (versions) // 2624895
FIELD: aviation.SUBSTANCE: group of inventions refers to means of ensuring safe activity at the external surface of space object (SO), for example, an orbital station (OS). The system of astronaut fixation while moving along the external surface of the SO includes handrails, rigidly fixed on the external surface of SO body, a safety wrench fixed to the astronaut's suit with a slidewire, a free end of which is fixed on the external surface of the SO. The system incorporates brackets with flat spirals, each of which is made of conjugated concentric loops, or with rigid plates, each of which has a central hole that passes into the annular section in the form of a through slot with a slit of plate outer contour. In the method of operating the system, the slidewire is introduced, as it unwinds, between the loops of spiral or through the slot of plate outer contour with pulling the slidewire in the direction of motion of the astronaut.EFFECT: increasing the safety, reliability and speed of astronaut fixation.4 cl, 9 dwg, 1 tbl

eans and method of protection of artificial objects from effects of space factors // 2624893
FIELD: construction.SUBSTANCE: protective equipment contains a shell filled with regolith and made of a material based on fiberglass with operating temperature limits from -200C° to +550°C and a strength of 180÷400 kgf/mm2. The regolith layer has a density of 3.0±0.3 g/cm3 and thickness δ=0.5÷0.75 m. The dimensions of the shell in the form of a parallelepiped constitute δ×2δ×3δ. According to the method, the protected object is updated with a supporting structure that is covered with a metal mesh. On the surface of the mesh are laid in butt in at least two layers of shell, filled with regolith. The joints between the shells of the lower layer overlap the shells of the upper layer.EFFECT: increase in reliability, manufacturability and reduction of material consumption of means of protection of artificial objects.2 cl, 8 dwg

Cosmonaut fixation system for mobile transportation along space object external surface and method for its operation // 2624891
FIELD: personal demand items.SUBSTANCE: fixation system includes handrails fixed on the outer surface of the space object and a winch with a safety rope attached to the cosmonaut's spacesuit. The free end of the rope is fixed on the immobile element of the object structure. Brackets with cylindrical helical spirals with one full and two half-turns are mounted on the handrails. As the cosmonaut moves forward, he passes the cable through these spirals, installed at the beginning and end of the straight sections, on the corners and bends of the handrails route with an interval equal to the reach of the astronaut's outstretched hand.EFFECT: increased safety and ergonomics of safety line fixing by the astronaut to prevent uncontrolled migration.2 cl, 12 dwg, 1 tbl

ethod of space vehicle orbital movement correction action // 2624889
FIELD: aviation.SUBSTANCE: in the method of space vehicle (SV) orbital movement correction action during the application of test and corrective actions, the beginning of the engine combustion chamber wall heating steady-state conditions is fixed, the number of the solenoid valves actuations at the inlet to the pressure stabilization unit is recorded, the average rate of the solenoid valves operations and acceleration from the correction engine are determined. Based on the results of working off the correction plans, a set of reliable values of accelerations for further work with the space vehicle is obtained.EFFECT: providing reliable and operative correction of orbital movement with increasing its accuracy.1 dwg

Spacecraft solar batteries maximum output power determination method // 2624885
FIELD: aviation.SUBSTANCE: invention relates to the power supply of the spacecrafts (SC), using the solar batteries (SB). The method includes turning of the SB panel into the operating position, voltage (U) and current (I) measuring from the SB at the time, when the radiation from the Earth enters the non-working side of the SB panel, and the SB output power determination. At that the SC and SB are deployed until the minimum illumination of the SB working surface of the reflected solar radiation from the SC surface, when A < ε, where A is the angle between the normal vector to the SB working surface and the direction vector to the Sun; ε - the semiapex angle of the this working surface so-called sensitive area. Further the values of U, I and A are measured, determining the SB maximum output power as U. I/cos (A).EFFECT: reduction of the radiation effect, reflected from the spacecraft surface to the solar battery measured output power.1 dwg
Spacecraft universal platform // 2624764
FIELD: aviation.SUBSTANCE: spacecraft universal platform (SUP) is a constructively and functionally separate module for the spacecraft construction. The basis of the SUP is an autonomous power structure with honeycomb panels fixed on it for placing on them only equipment of the service system modules. The SUP consists of working fluid storage tanks for propulsion systems of the correction system and the stabilization and orientation system (SOS), SOS devices, panels and drives of solar cells and partially correction system propulsion systems and SOS. Depending on the spacecraft layout and the its center-of-gravity position, the components of the SUP parts can be located in the zone of the payload module (PLM).EFFECT: development of a spacecraft universal platform that can be designed, manufactured and tested autonomously, regardless of the spacecraft launching type, the layout of the SC PLM.1 dwg

Spacecraft solar batteries output current determination method // 2624763
FIELD: aviation.SUBSTANCE: method includes turning of the solar battery panel (SB) into the operating position and current measuring from the SB at the time, when the radiation from the Earth enters the non-working side of the SB panel. Determine the current value of the solar radiation fall angle value (α) to the SB surface. If the value is α in the given range, determining by the characteristics of the SB working surface optical protective coating and the geometric parameters of its sensitive area, then measure the current value of the current (I) from the SB. The SB output current is determined from the value of I with the correction factor, that depending on α k -SB protective coating absolute refractive index.EFFECT: recording provision of the solar radiation refraction and reflection influence by the optical protective coating to the solar battery measured output current.1 dwg

Screen for spacecraft protection from high speed impact actions of the space environment particles // 2623782
FIELD: aviation.SUBSTANCE: invention relates to the spacecraft security measures (SM) from the high speed impact actions of space environment particles. The screen contains the honeycomb structure made of the corrugated metal mesh. The mesh corrugations are arranged parallel with a pitch in 2-3 times more than the mesh wire thickness. The height of the corrugations in 3-5 times increases the minimum characteristic size of the particles colliding with the spacecraft. The screen might be double layered with the second layer corrugations oriented perpendicular to the corrugations of the first layer.EFFECT: increase of the spacecraft protection efficiency from the high speed particles by increasing the fragmentation degree of the particles without increasing the screen weight.2 cl, 10 dwg
Earth safety from the potentially dangerous space object method and its realisation system // 2623415
FIELD: aviation.SUBSTANCE: invention concerns the earth safety from the potentially dangerous space objects (PDSO) of a natural origin (asteroids, comets and fireballs) by means of the their orbits modification by virtue of the external influence on them. The PDSO fly orbit direct deflection by an atomic explosion is taken as the earth safety from the PDSO enforcement action. This action changes or excludes the PDSO orbit intercept with the Earth's orbit. One models conditions of the on-board navigation actualization when space delivery means of the nuclear explosive flying up to the PDSO after the best ballistic schemes with the minimum consumed power consumption selection. And one also models the flying up scheme with the help of which one guarantees slow approach and high-precision steering on the PDSO and realizes the safe joint flight at close range. One models the flight following and inspection the PDSO circuit after the explosion. With the help of this circuit one determines the orbit modification as the result of the atomic explosion effect fact by means of the earth-based and on-board watching facilities and measuring facilities. Then one carries out a qualitative and quantitative evaluation of this modification.EFFECT: increase in efficiency of the Earth protection against potentially dangerous space objects.5 cl, 5 dwg
Device for measuring level of fuel in tanks of vehicles // 2622730
FIELD: measurement technology.SUBSTANCE: device for measuring the fuel level in the tank rockets (TR) comprises a capacitive sensor electrodes and its fastening elements. The device is made as a tube rigidly fixed to the bottom of the tank. At the height of the tube the additional capacitive sensors are installed. Electrodes of each capacitance sensor are formed as copper plates set at a distance from each other on the studs. The even copper plates soldered to studs, located diagonally, and the odd copper plates are sent to the remaining studs. The ends of the studs are fixed in blocks fixedly mounted in the tube, and on one of the pads are made holes for electrical wires, which interact with two even and two odd copper plates whose outputs are transferred outside of the tube, which provides the electrical connection of capacitive sensors. The ends of the copper plates are rigidly fixed. Wires of telecommunications of capacitive sensors are protected by a casing, and the upper part of the tube cover.EFFECT: improving the accuracy of measuring the level of fuel in the tanks TR.3 cl, 3 dwg

ethod for control of angular motion of space rocket // 2622427
FIELD: space.SUBSTANCE: invention relates to the methods for space rocket (SR) movement control. Method for control of SR angular motion consists in control of pitch and yaw angles by deviation of the main engine combustion chamber arranged in the gimbal suspension in two mutually perpendicular planes, in control of banking angle by means of two pairs of gas nozzles and two aerodynamic rudders inclined by means of their electrohydraulic servos (EHS). Mismatch between command signal for deviation of aerodynamic rudders and actual angles of their deflection is determined. If any of two mismatch absolute values exceeds the preset maximum permissible value, an aerodynamic rudder EHS fault flag is generated. In case of EHS fault flag generation, the main engine combustion chamber is additionally deflected by pitch and aerodynamic rudder with serviceable EHS, yaw angle is additionally controlled by means of pairs of gas nozzles.EFFECT: technical result is high probability of successful completion of RS flight in case of failure of one of the actuators of control system.1 cl, 4 dwg

ethod for configuration of receiving system of geostationary spacecraft to communicate with low-orbit objects of rocket and space equipment // 2622426
FIELD: radio engineering, communication.SUBSTANCE: invention relates to onboard equipment of geostationary spacecrafts (SC) for relaying data between low-orbit SC and control centers and for receiving messages. In the antenna rod (14) close to the reflector (13) of a parabolic antenna there are two blocks (16,17), mounted with the help of mounting plates (19), of low-noise repeater amplifiers operating in the same frequency bands. When in operation, the spacecraft block (16) is placed on the north side of the rod (14) and the block (17) is on the south side. The side surfaces of the block housings are heat-insulated (from direct sun rays) and the open (upper or lower) surface serve as an emitting radiator. During equinox periods the blocks (16, 17) are equally illuminated by the Sun (mainly on the insulated side). In solstice periods mainly one of the blocks is heated by sun rays, and the other one is in the shadow of the rod (14).EFFECT: better quality of the repeater receiving system by improving the temperature operating conditions of the system elements.4 dwg

Platform power structure of the spacecraft // 2622304
FIELD: aviation.SUBSTANCE: power structure of the spacecraft platform is the carbon-plastic mesh structure in the form of the cylindrical tube, installed by one of its bases inside the rectangular parallelepiped coaxially with its axis. The parallelepiped consists of the panel-base and the top panel, connected to the cylindrical tube by means of the corners, and between each other by the support panels.EFFECT: invention allows to achieve the structure unification, high strength characteristics, reducing of the platform weight, implementation of this technical solution allows to provide simultaneous launch of several devices.4 dwg

ethod of ensuring thermal regime of the instrument compartment of aircraft // 2622173
FIELD: aviation.SUBSTANCE: method of ensuring the thermal regime of the instrument compartment of aircraft is to cool the equipment (2) with a two-circuit cooling system. The heat abstraction is carried out in the external circuit by evaporation of low-boiling refrigerant with removal of its vapors into the atmosphere. Cooling of the equipment (2) of instrument compartment in the internal circuit of cooling system is carried out by conductive transfer of heat from the instruments to evaporators built in vertical power honeycomb panels (3) of vertical heat pipes (4). In the lower part of honeycomb panels (3) cooled devices with large adiabatic heating are placed. In the direction to the top part of panels (3), devices with less adiabatic heating are placed. Condensers of heat pipes are cooled by a pipe heat exchanger (5) of external evaporative circuit.EFFECT: invention improves the heat stabilization of airborne equipment, improves reliability and reduces power consumption.2 dwg

Earth remote probing spacecraft control method // 2621933
FIELD: aviation.SUBSTANCE: method includes the construction of the inertial solar orientation of the space vehicle with a system of power gyroscopes, measurement of vectors and their kinetic moments, maintenance of this orientation with simultaneous unloading of gyroscopes. At the same time, in certain parts of the orbit, the operations of spinning the spacecraft, measuring and comparing with the maximum permissible level of the accumulator battery (AB) charge, monitoring the power balance of the spacecraft, unloading the power gyroscopes, charging the accumulator batteries from solar batteries are carried out in a certain combination with each other. These operations are linked to the processes of planned and unplanned Earth surface survey.EFFECT: increase of the spacecraft resource.6 dwg

Drainage device // 2621930
FIELD: aviation.SUBSTANCE: drainage device consists of a drainage system, which is designed as a container, the bottom of which is made with a fitting hole with a sealing surface and coaxial thread. The flange is formed of a cylindrical shape and is provided with a flap, under which radial slots are made. The housing is mounted in the fitting hole of the container with possibility to move against the surface of the container with a certain stroke. The locking assembly is integrated into the housing and designed as a plug valve, where the plug is sealingly mounted in the housing, and the nozzle for connection to the side container is provided with a plug with a hermetic seal.EFFECT: provision of opportunities to open the passageway of the descending capsule in case of force major landing of a reusable descending capsule on water.4 dwg

ethod for determining the output power of solar panels of spacecraft // 2621816
FIELD: electricity.SUBSTANCE: invention relates to a power supply of spacecraft (SC) with solar batteries (SB) having a positive power output of its back surface. The method includes measuring the height (H) near-circular orbit satellites and the angle (ε) between the direction of the Sun and the spacecraft geocentric radius vector. When ε is in a certain range depending on the H, the angles (f1, f2). The semi-zone sensitivity SB work and back surfaces and the maximum value of the angle (f1*) between the normal to the working surface SC and the direction to the sun, - SC unfold to the position at which the radiation enters the Earth Security is said zones of sensitivity. This position corresponds to the reconciliation of said normal to the plane containing the direction of the Sun and the radius vector of the spacecraft. The angle (ρ) between this normal and the radius vector of the spacecraft is in the range that depends onε, f1, f2, f1* H and the angle (γ) between the directions of the SC in the nadir and the nearest point to the spacecraft terminator. In this position, the measured voltage, current and power output SC and given angles ε and ρ.EFFECT: minimization of the impact of the Earth's radiation in determining the power output of solar cells.1 dwg

Vehicle for interplanetary communication (versions) // 2621805
FIELD: transportation.SUBSTANCE: group of inventions refers primarily to the man-rated vehicles for flights in the middle and outer space. On the vehicle framework there are modules of controlled aerostatic floatability, electric motors with screw propellers, liquid jet engines with fuel and oxidizer capacities, as well as the power supply and the traffic control systems, inhabited and technical compartments, ports for space vehicles approaching, thermal protection facilities for the inhabited compartment and vehicle equipment. The modules floatability is provided by pumping from the technical compartment tanks of the liquid helium and its gasification under the dome structures of these modules (the inverse process is also provided). The support for the missile with payload location can be installed on the vehicle, launched or descended from the space orbit.EFFECT: extension of the vehicle of this assignment functionality.5 cl, 13 dwg
Space module // 2621783
FIELD: aviation.SUBSTANCE: space module (SM) includes a power block-type housing in the form of bonded edges of a regular prism with end panels with cutouts for housing of the optical-electronic module and for fixing the jet propulsion system block. Prism housing carrier is made of n-multilayered side core panels, where n = 4, 6, 8 …, some of which are instrument with padded inside heat pipes, and the other are housing. Side panels are fixed together in alternating sequence along the perimeter. Along the perimeter of each panel side there are frame corners, fastened by detachable elements. Control panel is mounted on the outer surface of the second end panel. Fuel storage tank is attached by brackets to the control panel on the inner plane and placed in the recess of the second end panel. An optical-electronic module blind and panels and brackets for radio equipment and motion control system electromagnetic executive body are mounted on the outer side of the first end panel.EFFECT: space module weight reduction.7 dwg
ethod of lowering the spent part of space-mission vehicle submissile and the device for its implementation // 2621771
FIELD: aviation.SUBSTANCE: method of lowering the spent part (SP) of SMV submissile on the liquid components of rocket fuel to the predetermined drop region is based on stabilization and orientation of SP due to the energy of unprocessed residual liquid propellant components on the basis of their gasification and feeding to the waste nozzles of gas-reactive system. Gasification products are used to inject them into the boundary layer. The coordinates of the point, the direction of injection and the mass-flow rate of gasification products through the entry system into the boundary layer are determined from the condition for formation of maximum total control effect realized by the control nozzles of gas-reactive system and the nozzles of gas injection system into the boundary layer of SP. In device for implementing the method, nozzles of gas-reactive system and nozzles of gasification products injection into the boundary layer for each tank are introduced to the separating part of submissile, connected by lines with adjustable valves.EFFECT: increasing efficiency while lowering the SP of submissile of SMV.2 cl, 2 dwg
Spacecraft landing aid // 2621416
FIELD: aviation.SUBSTANCE: landing aid comprises landing supports with the central racks containing the master cylinder with a cell energy sink and attaching lug to the spacecraft body, telescopic rod with extension mechanism, bearing tarel pivotally connected with a telescopic rod. Landing gear is equipped with ropes made of high modulus material. Pneumatic sliding fence rod is connected to the master cylinder and the housing - with a transverse beam fixed in the recess of the landing gear.EFFECT: increased area of the spacecraft rollover stability during its landing.3 dwg

Service system module // 2621221
FIELD: aviation.SUBSTANCE: module comprises a housing with service equipment units positioned inside, a battery, a radio antenna (12), radiators-coolers (6, 9) and swing panels (8) of solar cells. The propulsion system comprises four blocks (4) of orientation and stabilization engines, two spherical fuel tanks (3) and a spherical cylinder (11) with compressed gas. There are means for fastening the module to the payload and the last stage of thelaunch vehicle. A housing in the form of an octagonal prism is designed from longitudinal struts as T channel bracket, upper (17) and similar lower transverse force elements with a profile in the form of a corner. Two pyramidical shoes (5) are mounted on opposite prism faces with their bases, two of the four propulsion units (4) are mounted on top of them. The spans between the poles are overlapped with side panels (23-27, 35).EFFECT: reduction in module weight and size, its hardening in the perception of radial forces from the payload, the increased fuel supply on its board.17 cl, 21 dwg

odular space vehicle // 2621132
FIELD: aviation.SUBSTANCE: modular space vehicle (SV) includes onboard equipment box, one of the boxes contains the SV service equipment, and the other box contains the target equipment and sensors of the control system command and control instruments. The target equipment unit is integrated with the service system unit via three hinged supports. The service system unit is attached to the system of separation through the plate, and there are three hinges between the service system unit body and the fixing plate to the separation system. The basis of the service system unit power structure is a triangular prism, hinges are located in the corners of its bases. The SV separation system is attached to the carrier rocket upper-stage rocket transitional farm at three points, lying on the rays - continuations of the lateral edges of the power prism.EFFECT: ensured minimization of mechanical stress caused by thermal expansion and narrowing in the bodies of space vehicle modules.5 cl, 3 dwg

ethod for determining orientation of space or air crafts and device for its implementation // 2620854
FIELD: aviation.SUBSTANCE: group of inventions relates to orientation control of the space (SC) and air crafts (AC) by means of sensing elements. The device comprises sensors (S) of craft orientation (gyroscopic or stellar) relative to the inertial coordinate system positioned on the base. Two or more S of angular measurement are mounted on each of the mentioned S between the orientation S and the base. S of angular measurement comprises a radiation source and a radiation receiver mounted on the base, and a reflective element - at one of the orientation S. These elements are mounted so that the planes of the incident and reflected radiation beams are not parallel. Management of mentioned angles (in the data processing unit) allows to eliminate the influence of errors in orientation S position in body-fixed coordinate axes (e.g., due to deformation of the structure) on the measured parameters of the craft orientation.EFFECT: increased orientational accuracy of the spacecraft or aircraft without increasing the rigidity of their structure.6 cl, 3 dwg
ethod and device (versions) for determining orientation of space or air crafts // 2620853
FIELD: aviation.SUBSTANCE: group of inventions relates to orientation control of the space (SC) and air crafts (AC) by means of sensing elements. The device comprises sensors (S) of SC orientation relative to the astronomical objects positioned on the base. One-dimensional or two-dimensional (or their combinations) S of angular measurement are provided for each of the mentioned S. S of angular measurement comprises a radiation source and a radiation receiver mounted on the base, and a reflective element - at one of the S of determining orientation. In a version, the radiation sources and the radiation receivers of angular measurement S can be mounted on another orientation S. These elements are mounted so that the planes of the incident and reflected radiation beams are not parallel. Management of measured angular direction S (in the data processing unit) allows to eliminate the influence of errors in orientation S position in body-fixed coordinate axes (e.g., due to deformation of the structure) on the measured parameters of the craft orientation.EFFECT: increased orientational accuracy of the spacecraft or aircraft without increasing the rigidity of their structure.10 cl, 2 dwg, 1tbl

Lightning conductor // 2620852
FIELD: physics.SUBSTANCE: lightning conductor (200) is mounted on the protected structure (100) and comprises surface coatings, several conductive elements (204) distributed over the structure, a protective coating (205). The surface coating comprises, at least, one electrically conductive ink layer (202). These elements are in contact with the electrically conductive ink layer (202). The protective coating (205) is located on the top of the surface coating and comprises a heat insulating and electrically conductive material. The protective coating (205) covers partially the conductive elements (204).EFFECT: invention provides effective protection against lightning strikes.14 cl, 13 dwg

Assembly cover of transport and launching container // 2620630
FIELD: aviation.SUBSTANCE: assembly cover of a transport and launching container (TLC), consisting of a rotatable cover fastened to the fixed TCL element, has at least one rotary anvil with projections installed on the rotation axis, one of which is flat and the other is spherical. The flat projection cooperates on one side with a fixation element disposed on the rotatable cover and, on the other side - with a small spacecraft (SSC), the spherical projection is disposed above the rotation axis of the rotary anvil and engages in the operative position with a plate mounted on the rotatable cover, wherein the plate rotational axis is offset against the rotational axis of the rotatable cover.EFFECT: SSC movement start is provided.3 cl, 9 dwg
ethod and device for determining orientation of space or air crafts // 2620448
FIELD: aviation.SUBSTANCE: group of inventions relates to orientation control of the space (SC) and air crafts (AC) by means of sensing elements. The device comprises orientation sensors (S) relative to the inertial coordinate system and relative to the astronomical objects positioned on the base. Each orientation S is equipped with at least six distance measurement S which arehingedly attached with ends to the orientation S and to the device base. Wherein parallel misalignment of measured segments is ensured. Distance S comprise mechanical length standard and a displacement S. S is connencted to their data processing unit. Management of orientation S displacements (in the data processing unit) is intended to eliminate the influence of errors in these S position in body-fixed coordinate axes of AC or SC (e.g., due to deformation of the structure) on the measured parameters of the craft orientation.EFFECT: increased orientational accuracy of the spacecraft or aircraft without increasing the rigidity and thermal stability of their structure.18 cl, 4 dwg
ethod and device for determining orientation of space or air crafts // 2620288
FIELD: aviation.SUBSTANCE: group of inventions relates to orientation control of the space (SC) and air crafts (AC) by means of sensing elements. The device comprises orientation sensors (S) relative to the inertial coordinate system and relative to the astronomical objects positioned on the base. Wherein the device is provided with one-dimensional or two-dimensional (or their combinations) S of angular measurement for each of the mentioned S. S of angular measurement comprises a radiation source and a radiation receiver mounted on the base, and a reflective element - at one of the S of determining orientation. These elements are mounted so that the planes of the incident and reflected radiation beams are not parallel. The angles are measured, for example, between the running axes of orientation S and the base. Management of these angles (in the data processing unit) is intended to eliminate the influence of errors in orientation S position in body-fixed coordinate axes (e.g., due to deformation of the structure) on the measured parameters of the craft orientation.EFFECT: increased orientational accuracy of the spacecraft or aircraft without increasing the rigidity of their structure.13 cl, 4 dwg
ethod for determining orientation of space or air crafts and device for its implementation // 2620284
FIELD: aviation.SUBSTANCE: group of inventions relates to orientation control of the space (SC) and air crafts (AC) by means of sensing elements. The device comprises sensors (S) of craft orientation (gyroscopic or stellar) relative to the inertial coordinate system positioned on the base. At least six S of point distance of orientation S from the base are mounted at each S for detemining angles between axes of orientation S and the base. The mentioned angles are determined by the indications of distance S by solving forward kinematic problem of Stewart platform for each orientation S. Management of mentioned angles (in the data processing unit) allows to eliminate the influence of errors in orientation S position in body-fixed coordinate axes (e.g., due to deformation of the structure) on the measured parameters of the craft orientation.EFFECT: increased orientational accuracy of the spacecraft or aircraft without increasing the rigidity of their structure.7 cl, 3 dwg

Space missile air-breathing launch system // 2620173
FIELD: aviation.SUBSTANCE: space missile air-breathing launch system comprises a plinth, that is made of the upper non-rotatable ring with the support shafts for the space missile attached to this ring. The upper ring comprises the guidance system of the air-breathing launch system and the batteries of its energy supply. The upper ring leans on the lower rotatory ring by virtue of a magnetic bearing system. The blades are radially attached with one end to the lower ring. These blades are designed to generate the lift capacity of the air-breathing launch system. They also comprise the propellant components tanks. And at the far end the air breathing motors are attached to the blades for the blades about an axis swiveling that is perpendicular to the floating ring surface.EFFECT: reliability and start efficiency growth.7 dwg

Space missile air-breathing launch system with the electric start // 2620172
FIELD: aviation.SUBSTANCE: space missile air-breathing launch system with the electric start comprises a plinth, that is made of the upper non-rotatable ring with the space missile support shafts ends attached to this ring. The blades are radially attached with one end to the rotatable ring. These blades are designed to generate the lift capacity of the air-breathing launch system. They also comprise the propellant components tanks. The air breathing motors are attached to the air surfaces other ends for the lift generation. The electric motor drive rotor of the rotatable ring is located on the rotatable ring. The fixed coil of the rotor is housed within the earth-based set of the space missile electric start.EFFECT: reliability and start efficiency growth.6 dwg
ethod and device (versions) for determining orientation of space or air crafts // 2620149
FIELD: aviation.SUBSTANCE: group of inventions relates to orientation control of the space (SC) and air crafts (AC) by means of sensing elements. The device comprises orientation sensors (S) relative to the inertial coordinate system and relative to the astronomical objects positioned on the base. Wherein each of the mentioned S is equipped with several S of measuring distances between this orientation S and the base (at least 6 S), as well as (in the version) between this S and another one (or several) orientation S. Hinge support of proximity S ends is carried out to provide parallel misalignment of measured segments. Proximity S comprises a mechanical length standard and a displacement S. Management of these displacements (in the data processing unit) is intended to eliminate the influence of errors in orientation S position in body-fixed coordinate axes of SC or AC (e.g., due to deformation of the structure) on the measured parameters of the craft orientation.EFFECT: increased orientational accuracy of the spacecraft or aircraft without increasing the rigidity and thermal stability of their structure.15 cl, 2 dwg

Connection joint of separating parts of aircraft // 2619611
FIELD: machine engineering.SUBSTANCE: connection joint comprises the connecting fittings arranged oppositely to each other, and fastening components. Mounting joints are designed to disintegrate and the axes are perpendicular to the plane of the mating fitting. In one fitting formed in the joint plane in the form of annular teeth of an isosceles triangle in cross section, a vertical axis, which is parallel to the axis of the mounting joint and the surface in contact with the surface of the annular recess, made by compressing the docking fittings. Fitting with an annular recess made of a material with a lower hardness than the material of the fitting with the annular tooth. The ratio of the base of an isosceles triangle cross-section of the annular tooth to its height is in the range 0.52-1.3.EFFECT: increase in shifts resistance of the connection joints with long alternating loads with the simultaneous possibility of disintegration - separation.5 cl, 2 dwg
 
2550891.
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