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)

Casing shell of aircraft // 2642471
FIELD: aviation.SUBSTANCE: for a shell with a long generatrix L and a smooth bearing wall of thickness δ of casing of cylindrical, conical or biconical form - in the wall of the shell from one or two ends axisymmetrically blind holes of diameter d and length l1, l2 are made in the way that δ=d+2(0.5-4.0) mm, L=(l1+l2)+(2-20) mm. A heat accumulating inserts or a balancing mass is installed in one or more cavities of a blind hole. The heat-accumulating insert is made of a material with a phase transition at the temperature not lower than +70°C. In open part of the blind hole, a groove with a diameter D and a depth h is made in a way that D=ƒ+(0.1-0.8) mm, h=S+(0.1-2.0) mm, where ƒ is diameter of the edge of heat-accumulating insert cork, S is thickness of the cork edge.EFFECT: improvement of the criterion of efficiency - cost - time of creation and development.4 cl, 5 dwg

ethod of estimation of space materials stability to impact of cosmic space factors // 2642009
FIELD: testing equipment.SUBSTANCE: invention relates to the field of testing polymeric materials that are included into the structure of space crafts (SC). In the proposed method material specimens are exposed within a specified period of time on the surface of SC, then are placed in a container which, in turn, is placed in a transport container (zip lock in space) and they are return to Earth. In a vacuum chamber with a controlled inert atmosphere, the containers are opened and specimens are taken from them, each of which is placed in a separate sealed tank. Then, under laboratory conditions, changes in the properties of specimen materials are determined. The pressure of inert atmosphere in the vacuum chamber is maintained above the ambient pressure.EFFECT: increasing the reliability of test results by practical exclusion of the influence of the Earth's atmosphere on them.1 dwg
Ground unit for landing and evacuation of astronauts // 2641576
FIELD: aviation.SUBSTANCE: proposed device contains a tower (1), a lifting device (2), a gallery of evacuation (3), power supports (4), a protective structure (5), a crew boarding cabin (not shown), a rotating cabin (7), a stationary cover (8), and a hydraulic drive (9). In the initial position, the lifting device (2) is at the bottom, and the cabin (7) with the cover (8) is moved to the cabin of the space vehicle. The arrived crew is lifted to the landing level by the device (2) and through an elevator hall, a technical zone, a pre-purification zone and a purity zone passes into the space vehicle cabin. In the normal situation after the engines are started, upon the contact sensor, the rotary sections of the cover (8) close, and the cabin (7) is retracted to the extreme position. In the emergency situation, just before the start, the cabin (7) is moved by the hydraulic pneumatic drive (9) to the head part of the carrier, from which the crew from the gallery (3) is moved into the protective structure (5).EFFECT: providing protection of space vehicle cabin against unfavourable environmental factors, improved safety of astronauts' evacuation in emergency situations and improved quality of crew cleaning, calculation, portable equipment, and tooling before servicing of the space vehicle cabin.3 dwg

Device for deployment and folding of flexible structure, flexible deployable structure and satellite, equipped with such device // 2641398
FIELD: radio engineering, communication.SUBSTANCE: device contains elastically transformable tapes ("roulettes") (31a, 31b, 31c), bent U-shaped and fixed on a flexible film or bed (30). The roulette is removed and retracted using the rotor (33) installed in the stator (32). The first end (16) of the first roulette leg (31) is rigidly connected to the first fastener (36), which can be fixedly connected to the stator (32). The second end (17), passed through the clamping jaws, is wound on the rotor (33). When unwinding from the rotor, the roulette spontaneously (elastically) becomes operational.EFFECT: creation of a compact, easy-to-operate, optimally interfaced with the deployable structure of the device, providing the necessary rigidity and stability of the structure in the working position.20 cl, 16 dwg

issile upper stage // 2641022
FIELD: aviation.SUBSTANCE: missile upper stage comprises a cryogenic oxidant tank with main longitudinal partitions, additional near-bottom partitions and a sampling device, a propulsion engine and an additional autonomous propulsion plant for the orientation and starting system. The cryogenic oxidant tank is equipped with a damping horizontal annular partition placed with a clearance in relation to the shell of the cryogenic oxidant tank. The damping horizontal annular partition is made in the form of sectors, each of which is fixed to the corresponding main longitudinal partitions. Each sector has a flange towards the lower bottom of the cryogenic oxidant tank. The cryogenic oxidant tank is equipped with a near-bottom mesh partition placed between additional near-bottom partitions and the sampling device.EFFECT: reliable launch of the propulsion engine of the upper stage.4 dwg

ethod of determining ring wave source coordinates on water surface from spacecraft // 2640944
FIELD: physics.SUBSTANCE: method involves recording ring waves on the image, simultaneously with which a part of the land is recorded, selecting and identifying, at least, four characteristic objects on it, not lying on one straight line. Then orthorectification of a snapshot is performed (image transformation from the central to the orthogonal projection). At least, three points are fixed on the resulting snapshot (orthophoto) lying on the ring wave image, and the coordinates of these points are determined from this snapshot. The ring wave source coordinates are determined by the finite formulas obtained using the geometric properties of the orthophotomap.EFFECT: increasing the efficiency, reliability and accuracy of determining the ring wave source coordinates on the water surface with an unknown orientation of the survey system in advance.3 dwg

ethod for monitoring present state of solar battery panel of spacecraft // 2640943
FIELD: aviation.SUBSTANCE: method for monitoring the present state of the solar battery (SB) of the spacecraft (SC) comprises turning the SB relative to the direction to the Sun, measuring the current values from the SB, comparing the measured current values with the set values, and monitoring the present state of the SB panel based on the comparison results. In addition, for each structural group of photocells, the SB panels rotate the SB relative to the SC to the given initial position, the given initial orientation of the SC is constructed, and it is rotated about the given rotation vector until it passes the positions, in one of which all the photocells of the group are illuminated by She sun, and in the other - shaded from the Sun by the SC body. In the process of the SC turning, the current from the SB is continuously measured and the parameters of the SC orientation are determined. The SB is rotated relative to the SC to another given initial position and the above-mentioned operations are repeated. After performing the operations for all the structural groups of the SB panel photocells, the measured values of the currents from the SB are compared with their calculated values. Based on the results of the comparison, the working capacity of the photocell groups is determined.EFFECT: ensuring the determination of the working capacity of specific structural groups of the solar battery panel photocells.2 dwg

issile upper stage // 2640941
FIELD: aviation.SUBSTANCE: missile upper stage comprises a cryogenic oxidant tank with additional near-bottom partitions, a sampling device, a rod of a cryogenic fuel level sensor, a propulsion engine. The cryogenic oxidant tank is provided with a drip reflector consisting of an inner truncated cone with a bottom in a small base. Its larger base is facing towards the upper bottom of the cryogenic oxidant tank, and an outer truncated cone, the larger base of which is facing towards the lower bottom of the cryogenic oxidant tank. The outer truncated cone is faired with the larger base of the inner truncated cone with a smaller base, holes uniformly distributed along the conjugation circumference are made in the conjugation of the inner truncated cone with the outer truncated cone. In the bottom of the inner truncated cone of the drip reflector, a central hole is made, through which the rod of the cryogenic fuel level sensor passes. The drip reflector is fixed to the rod of the cryogenic fuel level sensor above the additional near-bottom partitions.EFFECT: ensuring a reliable launch of the propulsion engine of the upper stage and its subsequent operation.2 dwg
ethod of monitoring present state of solar battery panels of spacecrafts // 2640937
FIELD: aviation.SUBSTANCE: method of monitoring the present status of the solar battery panel (SB) of the spacecraft (SC) includes the orientation of the SB working surface to the Sun, the measurement of the current values from the SB, the monitoring of the present state of the SB based on the comparison of the present measured current values and current values measured in the previous flight stages. In addition, the orbital orientation of the SC is maintained, in which the axis of rotation of the SB is perpendicular to the plane of the orbit and the normal to the working surface of the SB in the given discrete position is directed to the zenith. Sequentially unfold the SB in discrete positions in which the angle value between the normal to the working surface of the SB and the direction to the Sun is less than a fixed value, the values of the angle between the direction to the Sun and the plane of the spacecraft orbit at the moments of passage of the subsolar point of the orbit passes are measured. Measure the current from the SB at the moment of passage of the subsolar point of the orbit pass, where the measured value of the angle reaches a local minimum, determine the present value of the distance from the Earth to the Sun.EFFECT: improving the efficiency of monitoring the state of the solar battery of the spacecraft.1 cl
ethod of controling present status of solar battery of a spacecraft with inertiative end organs // 2640905
FIELD: airpower.SUBSTANCE: method of controlling present status of solar battery panel (SB) of the spacecraft (SC) includes the orientation of the SB working surface to the Sun, the measurement of the current values from the SB, the monitoring of the present state of SB based on the comparison of the present measured current values and current values measured in the previous flight stages. Control of SB panel status is performed by comparing the obtained current values from SB, each of which is multiplied by the ratio of squares of the current value of the distance from the Earth to the Sun and the average distance from the Earth to the Sun determined at the time of corresponding current measurement.EFFECT: increase the accuracy of assessing the current efficiency of solar battery, providing the same conditions for measuring the current from the solar battery against the background of space flight of spacecraft in an orientation in which the total external disturbance moment for the turn reaches a minimum value.1 cl

ethod of detachment of disposable loads with account of spring pusher energy // 2640498
FIELD: airpower.SUBSTANCE: invention can be used to free up large-size power units that are detachable during operation and reusable, for example head shields, vehicle stages and compartments, external tanks of aircrafts, space vehicles and other disposable loads (DL). In the method of detaching disposable payload, the selection of spring pushers with different energies is used. Spring pushers with maximum and minimum energy are diametrically opposed to each other, determine the displacement of energy of pusher springs and the radius of displacement of pushers spring energy relative to the geometric center of mass. In order to avoid twisting of the DL relative to the longitudinal axis, the longitudinal pushers are alternately arranged with the right and left guiding.EFFECT: securing the detaching of useful payloads with a given linear speed and eliminating the twisting of useful payloads relative to the longitudinal axis.2 cl, 4 dwg

ultifunctional space craft // 2640167
FIELD: aviation.SUBSTANCE: invention relates to equipment OF multifunctional space crafts (MSC), designed for calibration and alignment of radar stations (RS) and Earth's remote sensing (ERS). The MSC contains a housing with an instrument compartment, a propulsion system, orientation and stabilization systems, a thermal conditioning system, solar batteries. The housing of MSC is made in the form of a cube or a straight prism. On one of the facets of housing there is a V-shaped groove or a recess in which a corner reflector made of two flat plates is fixed. In MSC an additional module of equipment is introduced: target, transmitting, command radio link, navigation (for GLONASS and/or GPS systems) and other service systems.EFFECT: empowerment of multifunctional spacecraft by providing it with functions of orbital platform-carrier of tools for research of reflection characteristics of the atmosphere and ionosphere of the Earth, remote sensing of the Earth in optical or infrared range, enhancing the sustainability of corner reflector to thermal deformations.9 cl, 6 dwg

Starting system for space flying vehicles by e.p. tsiganov // 2640163
FIELD: aviation.SUBSTANCE: in the starting system for space flying vehicles, launch of the flying vehicle mounted on a launch platform with electric motor is carried out from the horizontal position. The flying vehicle receives acceleration pulse when moving along guide structure having descending and ascending branches with radii of curvature providing permissible levels of overloads. The guide structure can comprise rectilinear portions, be located in tunnels and ramps. The launch platform can consist of two sections-upper and lower ones. The lower section is equipped with an electric motor, and the upper section has aircraft structure and has foldable wings.EFFECT: fuel saving at the initial flight stage of space flying vehicle.24 cl, 2 dwg
ethod for treatment of patients with erectile dysfunction // 2639457
FIELD: medicine.SUBSTANCE: for treatment of erectile dysfunction, a gravitational effect is provided for the patient in the head - lower limbs direction on a daily basis for 10-12 minutes. The rotation speed for the first two sessions is 32 revolutions per minute. With each subsequent session, the rotation speed is increased by one revolution, bringing it to 36 rpm and retaining until the end of the treatment course. The muscular load power is gradually increased individually from 10 to 50 W by the end of the treatment course. The general course of treatment is 10-15 days.EFFECT: method increases the effectiveness of treatment of patients with erectile dysfunction due to gravitational action in conjunction with active muscular work of the lower limbs, improving blood supply, microcirculation and tissue trophic.2 ex

Group of ensuring free orientation of sphere regarding external power fields // 2638583
FIELD: physics.SUBSTANCE: device comprises a supporting structure, a sphere, two locking elements acting on opposite sides of the sphere and intended to hold the sphere in the correct position during the inoperative phase of the device, at least, four means for providing drops arranged symmetrically around the sphere and configured to form drops and keeping them at the required temperature, and an insulated sealed structure designed to isolate the said devices from the environment and to prevent the deposition of dust on the surface of the sphere and four drops obtained, and cooling means for the conservation of a sphere with a temperature lower than the drop temperature.EFFECT: free orientation of the sphere with reduced vibration in the device.12 cl, 6 dwg
ethod of determining deviation of longitudinal axis of cubesat class nanosatellite from local vertical and device for its implementation (versions) // 2638402
FIELD: physics.SUBSTANCE: method is carried out by the device, which includes an optical system with photosensitive cells pitch and yaw accomplished via channels, as well as the means of determining deflections of the longitudinal axis from the vertical nanosatellite. This deviation is set by the image analysis of the horizon line of the planet (Earth) by the group of detectors placed at the sides of the nanosatellite hull.EFFECT: creating a light small builder of the local vertical with a low power consumption and precision, comparable to infrared-builders of the local vertical.3 cl, 3 dwg

ethod of operation of lithium-ion secondary battery as part of non-sealed space vehicle // 2637585
FIELD: electricity.SUBSTANCE: method includes charging-discharging and storing batteries in a charged state. Analog sensors and local heaters are mounted on the batteries. In the process of operation, current value of temperature of storage batteries is determined. If the temperature of one of the sensors has reached the limit cutoff threshold, the heater is switched off. If the temperature of one of the sensors has reached the minimum switching threshold, the heater is switched on. At that, in case the temperature of one sensor reaches the cutoff threshold, in this case, at the same time, the other sensor has reached the switch-on threshold, the priority is made for switching off the heater. The analog temperature sensors are connected via the battery control device to the information exchange channel between said voltage converter, the thermal control system and the on-board computer.EFFECT: increased usage efficiency of lithium-ion batteries and improved service life characteristics of the space vehicle.2 dwg

ethod of destruction of parts of waste spacecrafts and device for its implementation // 2637007
FIELD: aviation.SUBSTANCE: in order to destroy the parts of waste spacecraft by perforating the high-heat structural material of the spacecraft components when it falls in dense atmosphere, a pyrotechnic composition of thermite type, based on aluminium and metal oxide, capable of self-ignition at a temperature of 900-1000°C and with an exothermic effect of at least 4200 kJ/kg, is applied to the surface of the spacecraft parts. The pyrotechnic composition of thermite type is filled in a cylindrical nozzle made of titanium alloy, which is fixed on the surface of spacecraft parts. To ensure the compression of the pyrotechnic composition to the surface of the material, an elastic heat-insulating liner is installed inside the cylindrical nozzle.EFFECT: method and device provide high safety, stability and reliability and allow perforating the high-heat parts of waste spacecrafts at the stage of their uncontrolled descent in dense atmosphere.6 cl, 4 dwg, 1 tbl

Interplanetary spacecraft // 2636453
FIELD: aviation.SUBSTANCE: interplanetary spacecraft consists of the main and auxiliary modules. The auxiliary module is fixed to the main module case with the possibility of rotation around the center of the main module weight. The main module is made with accommodation inside residential and office premises, life support systems, outside its housing has solar panels, heat sink radiators, anti-radiation shields. The auxiliary module consists of a rotary frame and a propulsion unit attached to its end, containing propulsion engines and a fuel tank.EFFECT: increasing the safety, providing traffic with a fixed orientation of the main module to the sun.5 dwg
Aircraft rocket launch site formed on basis of space-mission vehicle adapted from topol-m icbm and carrier aircraft il-76mf for insertion of small spacecrafts into final orbits by inserting smv from aircraft using combined transport-launching platform and lifting-stabilizing parachute // 2636447
FIELD: aviation.SUBSTANCE: invention is designed to create modern, cost-effective means of inserting small spacecraft (SSC) with weight from 100 kg to 1000 kg into orbits with a height Hcr, from 200 km to 1500 km without limitations on the azimuths of the launch traces. The Aircraft Rocket Launch Site (ARLS) consists of a solid-propellant space-mission vehicle (SMV) on the basis of the recycled Topol-M ICBM and IL-76MF standard military-transport carrier aircraft (CA). In order to insert the SMV from a lightweight transport-launching platform, a set of parachute systems based on a lifting-stabilizing parachute is used.EFFECT: optimal mass-dimensional parameters of the rocket segment, with the maintenance of the standard operating conditions of space-mission vehicles and carrier aircraft.4 dwg

Device for rotation suppressing // 2636445
FIELD: aviation.SUBSTANCE: device (1) includes a housing (10) with a compartment (11) and a shaft (20) rotatable about the first axis (A1). The rotating assembly (30) is rotatable about the second axis (A2) with the same speed - due to the means (70) - as the shaft (20). The means (40) for target object capturing, for example, space debris (D), is fixed to the assembly (30). The brake unit (50) serves to suppress the rotation of shafts (20) and (32a), and the knob (60) (flywheel) - to suppress the reactive torque of the housing (10) rotation arising when the assembly (50) is started. The means (40) is attached to the object (D) by means of an adhesive.EFFECT: possibility to suppress rotation of a target object rotation performing arbitrary rotation in space.8 cl, 1 dwg

ethod for manufacturing spacecraft // 2636244
FIELD: aviation.SUBSTANCE: method for manufacturing a spacecraft (SC) comprises manufacturing constituent parts, assembling the spacecraft containing a power supply system, testing the SC. In addition, a simulator of the SC power supply system consisting of a ground source of stable voltage and an adjustable inductive-capacitive filter is used, the output impedance of the SC power supply system is measured, and the simulator of the SC power supply system is calibrated to the corresponding output parameters and the measured impedance of the SC power supply system. Before installing the payload module on the SC, the payload module is tested for full functioning using the simulator of the SC power supply system, in parallel with testing the performance of the support system module within the SC.EFFECT: reduced time of spacecraft manufacture.4 cl, 1 dwg

Satellite vehicle variable mechanical systems deployment device // 2636207
FIELD: aviation.SUBSTANCE: device comprises the brackets (1) and (2) that are attached to the relatively moving elements (4) and (5) (for example, to the panels) of the construction and are linked to each other with the help of the flexible elastic plates (9) in the channeled (under extension) form. On the bracket ends there are rolling cams (6) that are S-shaped covered with the tapes (7) on the outside. The tapes are attached to the cams by the screws (8). There is the rope damping unit on the end part. The elements (contacting pair) of the endpoint sensor are implemented into the interacting cams. The construction deployment is carried out due to the elastic forces that are created by the plates (9). The deployment predetermined trajectory is carried out by the relative cams (6) rolling upon its fixed contact, which is created by the tapes (7). The impact, which occurs at the end of the deployment, is partially compensated for the damping unit. The fixation in the open condition is provided by the rigidity of the plates (9). The fact of the deployment is registered by the sensor.EFFECT: providing the construction rigidity in the open condition in a simple way, deployment process informativity enhancement and impact loads reduction.4 dwg

Charge-amplifier for detonation translators of aircraft on-board automation // 2636069
FIELD: aviation.SUBSTANCE: charge-amplifier for detonation translators of aircraft on-board automation comprises the metal case in the form of the thin-walled metal cap with the explosive multicharge placed within the cap. The multicharge comprises two pressings of a different density, wherein the high-dense charge part is situated in the cap bottom part. The charge-amplifier is additionally supplied with the ring-shaped charge, which is flush-mounted on the hub made of the inert non-metallic material and which is in contact with the multicharge from its low-dense part side. The thimble axial channel is implemented in the charge-amplifier from the cap open end side. The channel depth ranges to the half of the multicharge low-dense part length, and the diameter corresponds to the outside diameter of the detonation translator. The ring-shaped charge outside diameter exceeds the detonation translator diameter in no fewer than three times, and the cap edges from its open end side are rolled inwards to the case axis with the collar formation, which provides the hard contact among all charge parts.EFFECT: detonation initiation reliability, decrease of the shockwave loads level when the charges actuating, performance improvement and enhancement of work with the device safety.2 cl, 1 dwg

Device for two-stage rocket stages separation // 2635812
FIELD: weapon and ammunition.SUBSTANCE: device for two-stage rocket stages separation is made in the form of a steering control mechanism mounted on the rocket body with a possibility of two links separation (at the time of rocket stages separation). One link is kinematically connected with the aerodynamic steering wheel shaft, which is placed on the main rocket stage. The other link is connected to the gas rudder, which is placed on the starting stage. The link, connected with the aerodynamic steering wheel shaft, contains a rocker, hingedly mounted on the main stage, at the ends of which two grooves are made. One groove is intended for placement of a finger, rigidly fixed on the lever of the aerodynamic handlebars steering wheel shaft. The other groove is intended for placement of a finger rigidly fixed to the rocker of the link connected to the gas rudder, mounted on the starting stage. At that, the rocker ends are pivotally connected to a pair of rods pivotally connected to the gas rudder rocker.EFFECT: simplified design of the device for two-stage rocket stages separation with a possibility to disengage the links of the steering control mechanism.2 dwg

Scientific research space apparatus returned from earth orbit // 2634608
FIELD: aviation.SUBSTANCE: invention relates to spacecrafts (SC) for scientific research of physical phenomena and development of various systems and elements of a spacecraft in the satellite orbit and during descent in the atmosphere. The returned spacecraft contains a laboratory compartment (1) connected to the instrument compartment body (2), a frontal aerodynamic screen (3) of a segmentally conical shape and a braking motor installation (4). The screen (3) consists of a rigid central part (5) and a peripheral part in the form of a main inflatable braking device (6), covered externally by a flexible thermal protection. Test objects, for example heat protection samples can be asrranged on the rigid part (5). To reduce the landing speed, the RSC is equipped with an additional inflatable braking device (7) of toroidal form. The device (7) is connected to the compartment body (1) by a power conical shell of a fabric material with low gas permeability. It opens at subsonic flight speeds. In the transport position, the RSC has small dimensions due to the tight packing of the sealed shells of the braking devices.EFFECT: expansion of the complex of scientific and technological problems solved by the returning research space apparatus both in orbit and during descent in the atmosphere.3 cl, 3 dwg

Fuel tank // 2634496
FIELD: transportation.SUBSTANCE: fuel tank connected to the instrument compartment of the accelerating unit comprises a first spherical bottom, a supporting frame, a cylindrical spacer and a second spherical bottom, arranged in series and connected to each other. The first bottom of the fuel tank is equipped with a circular cutout, the ends of which are connected to a flange including a cylindrical wall. In the axial aperture of the flange of the first tank bottom there is an annular cover with the cross-section in the form of a channel-shaped profile. The axial cover aperture is covered by an adapter connected to the fuel sampling fitting and fixed to the inner cover belt. The shell of the instrument compartment is equipped with a circular cutout supported by a frame. The first tank bottom is passed through the cutout of the instrument compartment shell outside the instrument compartment. The supporting frame of the fuel tank is fixed to the frame of the instrument compartment.EFFECT: weight reduction, reducing the time for the assembly and mounting of the fuel tank.7 cl, 13 dwg

ethod of controlling independent power supply system of spacecraft // 2634473
FIELD: electricity.SUBSTANCE: method of controlling an independent power supply system comprising a solar battery and n storage batteries, a voltage regulator connected between the solar batteries and the load and n charging and n discharging devices consists in controlling the voltage regulator and the charge-discharge devices depending on the input and the output system voltage, controlling the charging and discharging degree of the storage batteries, prohibiting the work of the respective charging device when the maximum charge level of said storage battery is reached, removing the prohibition upon reaching a certain discharge level of said storage battery, prohibiting the work of the respective discharge device when the maximum discharge level of said storage battery is reached, and removing this prohibition upon reaching a certain charge level of said storage battery. The load is divided into the duty and the session components, and when the maximum discharge level of any storage battery is reached, the session part of the load is disconnected, and prohibiting the work of the respective discharge device is established after disconnecting the session part of the load.EFFECT: ensuring normal disconnection of the session load in case of an abnormal situation.1 dwg

ethod of manufacture of space apparatus thermoregulating system // 2633666
FIELD: aviation.SUBSTANCE: method of manufacturing thermal control systems (TCS) for space vehicles includes checking the total leakages of the liquid path and the dual-phase circuit (DFC) before refueling with their respective coolants. In the process of manufacturing DFC, an inter-cavity leakage between the vapour cavity and the liquid cavity of the capillary pump is additionally monitored with the test gas in the vacuum chamber, reporting the evacuated liquid cavity with the leak detector, providing a test gas with a pressure equal to the maximum working pressure of ammonia in the vapour cavity of the test gas. Before launching the spacecraft into orbit with the help of special software, the work of electric heaters of the volume compensator provides an increase in the minimum pressure at the entrance to the electric pump unit (EPU) to a certain value, guaranteeing nonconvulsive operation of the EPU with high reliability under operating conditions.EFFECT: improving the reliability of the thermal control system of a spacecraft in conditions of prolonged operation in orbit.2 dwg
Spacecraft solar battery // 2632677
FIELD: physics.SUBSTANCE: spacecraft solar battery (SB) has a flexible film-honeycomb structure, the honeycombs of which are made in the form of tetrahedral or hexagonal pyramids. Pyramids are connected to each other along the edges of their imaginary bases. Photoelectric converters are placed on the side faces of pyramids, taking solar radiation from the side of the indicated bases. In the deployed position, the SB can have a spherical configuration, in which the vertices of all the pyramids converge at the center of the sphere. A protective film with special properties can be placed on the working surface of the SB. The honeycomb design of the SB in the deployed position is eliminated by heating it to the evaporation temperature of the film or higher.EFFECT: increasing the efficiency of solar batteries by increasing the absorption coefficient by increasing the number of light reflections from the photoreceiving layer inside the pyramids, reducing the dependence of the absorption coefficient on the incidence angle of solar radiation, and simplifying the technology of manufacturing and operating the solar battery.15 cl, 5 dwg

Transport launching container // 2631360
FIELD: aviation.SUBSTANCE: in the transport launching container (TLC) for launching the small spacecrafts, performed as the body with four side walls, two opposite walls of which have guides, the rear wall, the transition frame and the rotatable lid. The rotatable lid is attached to the transition frame and is equipped with at least one spring that moves the rotatable lid into the opened position, as well as the placed inside the body the starting spring and the pusher with the magnet. The rotatable lid fixing unit is installed at the transition frame of the body, by the spring-loaded stoppers, interacting with the grooves of the rotatable lid, when it is opening at the predetermined angle. The bearings are placed on the pusher, interacting with the guides of the body.EFFECT: FFECT: increase of the transport launching container reliability and the small spacecraft launching accuracy.2 cl, dwg

ethod of thermo-stabilisation of electronic equipment // 2630948
FIELD: electricity.SUBSTANCE: method for thermo-stabilisation of electronic equipment based on the passage of a pre-cooled or heated coolant through a microchannel heat exchanger installed on electronic equipment is that the heat carrier is preheated or cooled by a thermal stabilization unit based on thermoelectric modules, then it is circulated in a single hydraulic circuit with a microchannel heat exchanger.EFFECT: increasing the efficiency of heat exchange, reduction of weight and dimensions and significant energy saving for the operation of the units of the system.3 dwg

Device for connection and disconnection of electric couplings of separated aircraft stages // 2630858
FIELD: aviation.SUBSTANCE: nose cowl can serve as the first stage, and the rest of the rocket - as the second one. The proposed device includes a separation device and an electric coupling unit. This unit is installed perpendicular to the outer surface of the second stage and contains a bushing fixed in the housing with an electrical connector. On the upper part of the bushing, a lid with a groove for placing a harness is secured. The upper surface of the lid repeats the outer circumference of the rocket. The separation device is made of two parts: one is a shear mechanism and the other comprises a tube with a stopper rigidly connected to the first stage housing, parallel to the rocket axis, and a cassette for placing the folded harness. The cassette is pivotally connected to the tube and fixed to the housing of the first stage. The thrust of the shear mechanism is installed with the possibility of longitudinal movement in the tube until contact with the limiter.EFFECT: decreased dynamic loads, in particular, on the fairing during its separation, improved streamlining of the rocket.6 dwg

Inflatable heat insulation dome // 2630842
FIELD: military equipment.SUBSTANCE: inflatable heat insulation dome includes a fence made up of a connected curved cover and two end walls made of flexible, resilient material. The curved cover consists of two horizontal collector pipes, the cavity of which is connected by curved pipes on each side. The end walls consist of two horizontal collector tubes, the cavity of which is divided by a partition in half. The cavity of all fence tubes is divided in length in half by a longitudinal partition into the air and gas channels and is provided with stiffening rings. Inside the fence there is a diesel engine and a fan.EFFECT: increase of efficiency of an inflatable heat insulation dome.4 dwg

ethod of thrust developing and power-propulsion device for moving object in space // 2630275
FIELD: electricity.SUBSTANCE: on the object interacting with the physical fields of space an electric power generator (PG) is additionally created, this generator has rotors with additional peripheral massive bodies (RMB), and accelerate-decelerate units fixed on the case of two rings that are rotating mutually opposite (with zero gyroscopic moment) coaxially to the shaft of the dynamo. Inside the rings on the mounting frame blocks in the form of hollow cylinders with parallel axes of symmetry are mounted. Several pairs of RMB with axes of rotation parallel to the axis of the cylinder are mounted inside of them. All blocks are placed in a certain way with respect to the plane of symmetry of the object. Magnetic and inductive elements of the PG are located depending on the optimal (for maximum electric energy) PG rotor speed. Synchronize the passage time of the PG rotor magnets of the PG stater coils with the passage time of the massive bodies of the RMB of its decelerate area.EFFECT: possibility of autonomous operation of the object, increasing its thrust in the chosen direction, reducing energy costs and expanding the field of application.12 cl, 6 dwg

ethod of autonomous determining angular object positions with six degrees of spatial movement freedom // 2629691
FIELD: physics.SUBSTANCE: method of autonomous determining the object position is based on the formation of an informative harmonic signal of the rotation gyroscope speed with a radially magnetized magnet-rotor by inducing the emf in the spherical solenoid winding mechanically fixed on the object, electric locking the gyro rotor, aiming its rotation axis onto the external space object, and installing initial coordinate reference, unscrambling and allocating the parametres from the informative signal by two coordinates, heading and pitch. Three simultaneously pairwise biorthogonal sine-cosine signals are generated by inducing the emf of the rotor rotation frequency in the form of a hollow full or incomplete ball magnetized perpendicular to its rotation axis and placed inside or outside the sphere of a nonmagnetic material, on which three spherical solenoids are mutually spatially perpendicular, and the parametres of the three angular object positions represented by the coordinate system associated with it in the form of three pairwise biorthogonal relations between the sine-cosine signals relative to the external inertial, non-inertial space or pseudoinertial represented by the rotating ball magnet-rotor, are determined by synchronous demodulation along the three channels of the amplitudes and phases of three pairs of the defined sine-cosine signals according to the specified algorithm.EFFECT: providing the possibility of increasing the informative value of the measurement conversion, expanding the application areas for 6-power objects with unlimited angles of error, and simplifying algorithms for processing informative signals.7 dwg

ethod of solar battery panels current status control in spacecrafts // 2629647
FIELD: aviation.SUBSTANCE: method of control of the current status of a solar battery (SB) panel of a spacecraft (SC) includes rotating the SB panel to positions where the working surface of the SB is illuminated by the Sun, measuring the current values from the SB, comparing the determined parameter characterizing the current status of the SB panel, to the set values and monitoring the current status of the SB panel based on the results of the comparison. In addition, the Sun direction vector is measured in the coordinate system associated with the SC, the angle of the SB alignment to its current discrete position is determined, the current values of the incidence angle of solar radiation on the surface of the SB protective coating are determined, the SB is rotated to at least two selected SB discrete positions, the value of the current from the SB is measured. The SB status is assessed by its optical protective coating defined by the current value of its absolute refraction index, as determined by the values of the incidence angle of solar radiation on the surface of the SB protective coating and by values of current.EFFECT: providing estimation of the current value of the absolute refraction index of the protective coating of the solar battery.1 dwg

Control method for spaceships approaching cooperative space vehicle // 2629644
FIELD: aviation.SUBSTANCE: invention relates to rendezvous and docking operations of space vehicles (SV) in the near-circular orbit, for example, of a space ferry vehicle as a SV and of an international space station as a cooperative SV (CSV). After placing the SC to the reference orbit, the parameters of the approach impulses for the parameters of the orbit of the CSV, measured before the SC departure, are determined. In the absence of information on the actual orbit of the CSV, a corrective pulse is made by the CSV means. This impulse is directed along the orbit and is calculated so that by the time of the meeting, the CSV latitude argument is adjusted to the value of the SC latitude argument.EFFECT: possibility of convergence of the spacecraft with the cooperative spacecraft in the absence of information on board the spacecraft about the actual orbit of the cooperative spacecraft.2 dwg, 1 tbl

Engine system of cosmic aircraft // 2629586
FIELD: aviation.SUBSTANCE: engine system (ES) of space purpose consists of fuel tanks with a gas and fuel necks, a fuel supply system, a system of actuators including at least deflecting engines with a mixing head and engines of stabilization and orientation. According to the invention, the tanks are rigidly and hermetically connected by the fuel necks with the mixing head of the deflecting motors by means of a detachable or integral connection. At the same time, part of the connection located in the mixing head forms the fuel distribution manifold through the channels made in the mixing head to the deflecting motors, and the mixing head of the deflecting motors ensures the rigid attachment of the tanks to each other.EFFECT: reducing the mass of the propulsion system and ensuring the survivability of the design of the propulsion system and the spacecraft as a whole.6 cl, 9 dwg
ethod of creation of electrostatic protection from meteorites and space radiation charged particles // 2629461
FIELD: electricity.SUBSTANCE: method involves creation of an electrostatic high field in a cylindrical coaxial capacitor (CC). The outer plate of the CC is a folded metallized film. The capacity of a charged (for example, up to 600 kV) CC is reduced by its unwinding around the axis of the cylinder. As a result of unwinding, the film straightens out under the action of centrifugal forces, forming an outer cylindrical plate with a radius much larger than that of the inner plate. With a sharp drop in the capacitance of the CC and under the condition of conservation of its charge, the voltage and energy increase sharply, so that the potential difference between the CC plates can reach, for example, 2 GV (which is sufficient for the reflection of charged particles with energy ~ 2 GeV). In the CC field, small meteorites can be destroyed due to electric breakdown.EFFECT: reduced mass of electrostatic protection while providing centrifugal compensation of the attraction between the coaxial capacitor plates.2 dwg
ethod of implementation of running of booster rocket // 2628836
FIELD: weapon and ammunition.SUBSTANCE: during the acceleration of the launch vehicle in the active section of its trajectory, the parts of the tanks for the rocket fuel components and the excess parts of the supporting elements of the carrier rocket are excessively redundant and unnecessary for further flight, and they are dropped into the outer space. In the process of acceleration, the rocket engines are gradually shutting down, becoming - as the current mass of the launch vehicle's structure is reduced - superfluous and excessive, overlapping the leading pipelines and lines. These rocket engines are disconnected from all other communications and detach them from all mechanical connections with the structure of the launch vehicle, and then carry out their discharge (detachment) from the carrier rocket. At the same time, on the upcoming (remaining) part of the active part of its trajectory, acceleration is carried out at the expense of the remaining missiles, which have not yet been dropped, including, in turn, not dropped.EFFECT: increase in mass efficiency.2 cl

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
 
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