Aircraft and aviation and cosmonautics (B64)

B64            Aircraft; aviation; cosmonautics(13293)
ethod of orientation by laser beam // 2607723
FIELD: transportation.SUBSTANCE: invention relates to orientation during vehicles movement. Method of orienting by laser beam comprises fact, that generating laser beam elongated cross section with large and small axes lengths ratio of 2…5, turning laser beam about its lengthwise axis until establishing beam cross-section larger axis in plane, passing through beam longitudinal axis and specified path, and directing laser beam towards vehicle in parallel or at small angle to preset travel path. Vehicle deviation from preset travel path is determined according to laser beam position and additionally determining deviation value by increasing of laser beam lateral dimension.EFFECT: technical result consists in increasing of visual orientation informativity.1 cl, 3 dwg
Constant-velocity universal joint for helicopter rotor // 2607717
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering, particularly, to designs of propellers hubs on universal link. Constant-velocity universal joint consists of two concentric rings (5A and 5B), wherein first inner ring (5A) has rotary connection with driver (3) two opposite pins (31) connected with transmission shaft (1). Second outer ring (5B) has rotary connection with hub (2) two opposite pins (22). Two concentric rings are also mutually connected by pair of articulated opposite pins (542) at angle of 90° relative to pins (31) connected with transmission shaft, and relative to hub pins (22), which common axis (CA) is stably maintained in plane, called homokinetic, dividing angle between hub (2) axis of rotation and transmission shaft (1) axis of rotation in halves, by means of at least one or two devices (6). At that, bisectors are connected with transmission shaft and with hub.EFFECT: enabling continuous transmission of rotational movement between transmission shaft (1) and said hub (2), to which blades (7) are attached regardless of hub angle of inclination relative to driving shaft.10 cl, 12 dwg
Gas turbine engine pylon // 2607715
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircrafts. Pylon (30) has streamlined shape defined by two opposite side surfaces and longitudinally between leading edge (31) and trailing edge (33). On each of its side surfaces (36) pylon (30) has sequence of deflectors (40), which are transversely spaced apart from each other and which determine between each other converging and curved channels (60). Channels (60) are made so that to accelerate air flows, flowing in channels (60) during aircraft takeoff or flight so as, to deflect said air flows towards engine jet blast.EFFECT: invention reduces engine noise.10 cl, 6 dwg
Vibration weakening strips to discharge liquid for aircraft turbine engine fan housing acoustic protection // 2607688
FIELD: engines.SUBSTANCE: invention relates to aircraft gas turbine engine fan housing acoustic protection. Aircraft fuselage acoustic protection device comprises acoustic protection panel (6) with strips (10), weakening vibration. On one side strips are pressed to panel (6) outer surface (6a), and on other side is to fan housing inner surface. Each weakening strip (10) has two opposite edges (14), each of which has upstream and downstream ends, located at distance from each other along central axis (2) direction. One of two strips (10) opposite edges (14) has such shape, that liquid, present on this edge, could flow by gravity in direction of any one or both of its upstream and downstream ends.EFFECT: invention improves aircraft engine reliability.10 cl, 7 dwg
Nozzle of gas-jet helicopter control system // 2607687
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering and can be used for helicopters with jet control system. Control mechanism of flaps of tricuspid nozzle with controlled thrust vector consists of toothed sector of middle flap position control, side flaps control levers, central rocker, engaged by rods with levers of side flaps. Central rocker is engaged with toothed sector of middle flap, wherein gear ratio from middle flap to central rocker is 0.70–0.78. Arms of central rocker have length of 0.3–0.4 width of nozzle inlet section and opening angle of arms 140–150°. Levers of side flaps have arms of length of 0.3–0.35 and 0.4–0.45 of nozzle inlet cross-section width and angle of inclination 50°–55° and 55°–60° respectively, and thrusts of levers of side flaps are 0.5–0.55 and 0.4–0.45 of nozzle inlet cross-section width.EFFECT: reduced pressure losses in nozzle and improved its efficiency, providing required for each flight mode ratio of side and propulsion forces.1 cl, 7 dwg
Protective shield against impacts of ice on aircraft // 2607686
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering, particularly to a self-recovering shield protection against impacts of ice on an aircraft (AC), in particular, an AC with propeller engines. Protective shield against impacts of ice on an aircraft structures comprises layers of a composite material (CM) having microcapsules containing a recovering agent. Herewith the CM also contains microcapsules containing particles of a catalyst. Under action of the catalyst particles the recovering agent becomes a polymerized recovering agent, where the recovering agent is dicyclopentadiene. Herewith the catalyst particles are particles of tungsten hexachloride and diethylaluminium chloride (WCl6-Et2AlCl).EFFECT: provided is higher flight safety due to the use of a self-recovering material, which recovers the protective material in flight.14 cl, 7 dwg
Drip refrigerator-radiator dispersed fog collecting device // 2607685
FIELD: space.SUBSTANCE: invention relates to space engineering, namely, to heat removal devices in space power plant thermodynamic cycle. Drip refrigerator-radiator (DRR) dispersed fog collecting device comprises working medium supply and delivery units. Supply unit comprises drive and driven pulleys with belt installed on them. On belt return section electric heater is installed. Delivery unit is installed above drive pulley and includes rotor with grooves, accommodating movable blades and pushers with return springs, cam, setting required pushers movement law, and working medium residues removal shutter. Collecting of cooled down as a result of radiation cooling drops is carried out by supply unit moving belt. Liquid film is formed on belt moving together with it to delivery unit. For removal of film from belt moving blades are used. Residual working medium temperature control at belt return movement is carried out by electric heater.EFFECT: technical result of invention is enabling of DRR cooled working medium transportation to its circulation closed circuit pump input.1 cl, 2 dwg
Control system actuator // 2607490
FIELD: control systems.SUBSTANCE: invention relates to aircraft airfoils control systems. Control system actuator comprises control unit and steering drive. Steering drive comprises velocity generator, rotor position sensor, two-stage reduction gear, ball-screw pair, feedback sensor, connected in certain manner. Control unit comprises secondary power supply source, consumed current sensor, receiving-transmitting unit, microcontroller, power switches control unit, power unit, microcontroller integrity checking unit, damping and braking mode actuation unit, connected in certain manner.EFFECT: enabling expansion of electromechanical steering drive functional capabilities, increasing stability and accuracy.1 cl, 3 dwg
ethod of optimising operability of aircraft engine and main power plant to this end // 2607433
FIELD: energy.SUBSTANCE: invention relates to power engineering. Method of optimising operability of aircraft engine, comprising main engines 200 as main propulsion system, wherein by means of main source of power 1 class engine, all non-traction power Enp is output as propulsion installation, and during transient phases of operation of engines, at most, additional power (kEp, ktEpt) partially supplied to high-pressure stage VD of main engines margin of margin is increased on surge of main engines. Also disclosed is a main aircraft power plant.EFFECT: invention enables to eliminate limitation of mechanical extraction in engines during transient flight phases, which enables to optimise performance of a set of engines in said phases.10 cl, 5 dwg
Device for earth protection from space objects // 2607384
FIELD: means of protection.SUBSTANCE: invention relates to means of protection and is intended for changing orbits of massive space bodies threatening collision with the Earth. Device consists of a housing, a guidance and orientation system, a laser range finder. In the housing there is a heat-insulated composite container, detachable parts of which comprise solid paraffins and have their own guidance and orientation systems. In the head part of the housing in a barrel there is a set of impact elements (from 2 to 5) with their own guidance and orientation systems. These elements also contain solid paraffins. Device approaches a space body typically with speeds equal to or larger than the third space one. At collisions of the body with impact elements and parts of the container large inner energy is released with simultaneous formation of a sunken crater (funnel). Latter plays the role of a "nozzle" for products of explosions of the said elements and parts.EFFECT: technical result is more effective change of flight trajectory of a threatening space body.1 cl, 1 dwg
easuring device for omega shaped component position determining, computing unit and measuring method // 2607138
FIELD: measurement technology.SUBSTANCE: method of measuring for omega-shaped component (2) position determining, mounted on aircraft shell component (1), in which omega shaped component (2) actual position relative to shell component (1) is determined optically in non-contact manner, in order to later compare it with preset position. When measuring are formed several adjacent arranged spaced apart points (6; 6') of measurement on two mutually opposite sides (7a, 7b; 7a', 7b') of omega-shaped component (2) shaped cross section, through which regression lines (8a, 8b, 8a', 8b') are plotted in accordance with path measuring principle based on coordinates, point (9; 9') of intersection of which determines Omega-shaped component (2) orthogonal position relative to shell component (1). Measuring device implements method. Computing unit is included into measuring device.EFFECT: disclosed is measuring method for omega-shaped component position determining, mounted on aircraft shell component.10 cl, 3 dwg
Aircraft // 2607037
FIELD: aircraft engineering.SUBSTANCE: aircraft has a fuselage, a chassis, a wing made with the possibility to change the angle of its installation in the lengthwise plane relative to the fuselage, a means for reducing the run length at landing, for which purpose the said wing is used, which is made with the possibility of its installation on a larger angle by the absolute value than the landing angle of its installation.EFFECT: invention is aimed at reducing the run length at landing.4 cl, 4 dwg
Turbine machine propeller blade, particularly fan without fairing, and corresponding propeller and turbo machine // 2606787
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering, in particular, to propellers blades designs. Turbomachine with fan without fairing comprises two coaxial and counterrotating propellers (7, 8), having plurality of blades (11A, 11B). Input fan (11A) blades have means (16, 16A, 16B) intended for single arrangement for implementation of local disturbance during propeller (7) rotation, distribution of circulation around blades (11A). Disturbance means contain single expansion (16, 16A, 16B) made on blade (11A) front edge (17), wherein single expansion (16, 16A, 16B) position is defined by its position along width h so, that 0.75H<h<0.85H, where H is blade (11A) height. Decreased noise generated by turbomachine.EFFECT: disclosed is propellers blades design.4 cl, 5 dwg
Device for lowering of cargoes in atmosphere // 2606784
FIELD: fire safety.SUBSTANCE: invention relates to means of people evacuation from burning buildings. Device for cargo lowering in atmosphere comprises: external parachute canopy and inner parachute canopy of smaller size, connected to each other along perimeter by circular bridge to make closed cavity between them, device for production of compressed gas, connected to cavity to supply compressed gas inside it, slings, made with possibility of changing their length, some ends of which are connected with said canopies, and other ends can be attached to cargo, nozzles, equipped with valves made with possibility of their forced opening and closing placed on aforesaid bridge and connected with cavity, circular confusers made with possibility of their forced opening and closing, placed on external canopy, connected with cavity and oriented along external surface of canopy, passing through cargo.EFFECT: technical result is increase of safety due to avoiding effect of folding and delaying of falling.5 cl, 1 dwg
Structural element positioning setting device // 2606657
FIELD: aircraft engineering.SUBSTANCE: invention relates to aviation equipment, particularly, to structural element positioning setting device (1), for example, horizontal tail. Setting device (1) contains at least two loading paths (2, 3), wherein loading paths (2, 3) are formed by group of load transmitting parts. At that, second loading path (3) comprises gap (50, 51) to take elongation of, at least, one part of first loading path (2). Besides, setting device (1) comprises fixing unit (4) with fixation device (40). Fixing device (40) enters gap (50, 51), if first loading path (2) part is damaged.EFFECT: higher reliability.10 cl, 9 dwg
Assembly formed by gas turbine engine and system for its attachment to aircraft structure // 2606524
FIELD: engines and pumps.SUBSTANCE: invention relates to aircraft gas turbine engines. Unit comprises gas turbine engine and engine to aircraft mounting system. Attachment system comprises support, rear fasteners and support rear closing element. Rear closing element has two side walls. Every wall has first part (42a) passing along and next to support and passing rearward, and second part (42b), which protrudes in lateral direction relative to wall first part to its outer side so, that to close rear fasteners. Each second part (42b) of closing element rear side wall has essentially bulge shape and connected to side wall first part.EFFECT: invention allows to reduce specific fuel consumption.5 cl, 5 dwg
Planetary gear for aircraft made with possibility of hovering // 2606423
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering, particularly, to helicopters and converter planes reduction gears. Planetary gear for aircraft (1) made with possibility of hovering, has sun gear (7), rotating around first axis (A), fixed crown gear (9) located coaxially with first axis (A) and radially outside relative to sun gear (7). Plurality of planetary gears (11) are placed between teeth of sun (7) and crown gears (9), engaged with them and rotating around corresponding second axes (B), which, in turn, are turned around first axis (A). Lubricant supply device (16) has several nozzles (17) arranged around first axis (A) and sun gear (7) to create lubricant circular flow (F).EFFECT: better lubrication of sun gear.12 cl, 7 dwg
Electric charge dissipation system for aircraft // 2606419
FIELD: machine building.SUBSTANCE: group of inventions relates to aerospace and other articles structural elements (SE) structure and production process. SE comprises first and second composite layers. Second layer with electrically conductive fibres is made decreasing electrochemical corrosion during its contact with first layer, also providing electric charge dissipation on SE surface (of first layer). SE production includes placement of first and second composite layers in mold and their curing.EFFECT: group of inventions technical result is higher articles fire safety, in particular composite fuel tanks, on surface of which static electricity can be quickly accumulated.15 cl, 9 dwg
Automatic system for stabilizing suspended loads with automatic control // 2606244
FIELD: aircraft engineering.SUBSTANCE: invention relates to an automatic system for stabilizing rotation speed of at least one suspended load attached to the helicopter. Automatic system comprises at least one aerodynamic device – wing (9), wherein wing (9) is at least partially fixed on the suspended load, at least one movement system, which can move at least a part of wing (9), at least one sensor of angular speed defined by here as a primary sensor, at least one software or a computer program and at least one processor, on which the software is at least installed. By means of the system, based on at least value of at least a part of at least one component of angular speed of the suspended load, said value is detected by the primary sensor, physical action is automatically generated by interaction between the aerodynamic device and a flow channel located downstream of helicopter blades, and by the processor. Physical action is a moment or torque acting on at least a part of the suspended load tending to stabilize and reduce the rotation speed of the suspended load. System can be especially useful in rescue operations performed by means of a helicopter, especially during lifting and lowering suspended load, comprising mainly a rescuer, litter and patient lying on it.EFFECT: provision of the system for stabilizing at least one suspended load, preferably for rescue operations performed with the help of a helicopter, which requires less amount of energy for operation in relation to already known devices and has higher efficiency, when the suspended load approaches a helicopter.11 cl, 11 dwg
Short takeoff and landing unmanned aerial vehicle // 2606216
FIELD: aircraft engineering.SUBSTANCE: invention relates to unmanned aerial vehicles. Unmanned aerial vehicle comprises swept-back wing (1), made under condition of using "flying wing" aerodynamic configuration, power plant, including engine with propeller, as well as control elements. Wing (1) in fore end is equipped with power plant and control elements, made in form of foreplane (5) and canard fin (6). Power plant, foreplane (5) and canard fin (6) are located on support (2) above wing upper surface, wherein enabled possibility of wing upper surface and control elements blowing by propeller.EFFECT: invention increases aircraft lift and maneuverability.3 cl, 2 dwg
Space solar power plant // 2605956
FIELD: energy.SUBSTANCE: invention relates to conversion of solar energy and its transmission to terrestrial consumers. Space solar power plant comprises lobe-type solar collector (1), station housing (2) and beam (3) of microwave antennae. Collector (1) is made of plates (boards) of photoelectric converters – main and auxiliary. Plates are rectangular and triangular. Their connections are made in the form of automatic hooks and loops, which are connected by means of multilobed mechanism when deploying the collector. Folded collector (1) has the shape of a cube. Antennae of beam (3) focus microwave power on the amplifier, transmitting this energy to ground power plants.EFFECT: technical result of the invention is higher efficiency of conversion and transmission of energy to consumers on large areas of the Earth.1 cl, 16 dwg

Flight interpreter for demonstration of unmanned aircraft systems with external load // 2605801
FIELD: aircraft engineering.SUBSTANCE: group of inventions relates to unmanned aircraft system (UAS) testing method and system, as well as to UAS with external load testing system. UAS testing system comprises UAS flight control system, optionally piloted vehicle (OPV) with its own control system, flight control interpreter. To conduct UAS testing UAS fuselage is attached to OPV, UAS flight control system is connected to flight control interpreter, latter is connected to OPV flight control system, UAS mission profile is initiated, sending control parameters from UAS flight control system to flight control interpreter for their interpretation, determining mission profile completeness, otherwise sending current state commands from flight control system interpreter to OPV control system, determining presence of pilot intervention, controlling OPV based on current state commands. UAS with external load testing system comprises UAS flight control system, OPV with own control system, OPV ground-based tracking system. OPV carries UAS fuselage flight control interpreter.EFFECT: enabling UAS testing in accordance with certain mission profile.12 cl, 8 dwg

Space garbage removal // 2605799
FIELD: space.SUBSTANCE: group of inventions relates to removal of space garbage by its braking for re-entry into atmosphere and combustion in it. For this purpose on garbage path unstable gaseous spherical (or hemispherical) cloud is created with average height of not less than 100 km. Cloud is formed by Prandtl-Meyer expansion of gas leaking from Laval nozzle (two nozzles, unfolded to each other by 180°) with appropriate outlet angle. Gas can include metal additives, heavy molecules with low adiabat index, high-molecular elements and halogens.EFFECT: group of inventions technical result is aimed at creation of relatively simple and reliable cleaning of near-Earth orbits from garbage.13 cl, 10 dwg

Aircraft hydraulic system // 2605797
FIELD: engines and pumps.SUBSTANCE: invention relates to aircraft engineering and can be used in hydraulic systems designs implementing several control modes. Hydraulic system comprises electrically driven pump (7) with controlled supply, actuator motor (8), presented in form of hydraulic cylinders with pistons progressive motion, main line (10), connecting actuating motor (8) with electrically driven pump (7). System is equipped with hydraulic tank (1), inside of which piston with spring-loaded dampers with possibility of longitudinal movement is installed, which separates hydraulic tank (1) to high-pressure and low-pressure chambers. Power-driven pump (7) input is connected to hydraulic tank low-pressure chamber, and its output is connected with hydraulic tank high-pressure chamber and to actuator motor (8) input, wherein electrically driven pump (7) and actuator motor (8) are connected to missile control system (12).EFFECT: reduction of total heat release, dimensions and weight by required increase of hydraulic system power during aircraft with hydraulic tank programmed manoeuvres periods.1 cl, 2 dwg

Structural material for making structural elements, fuel tank, main wing and aircraft // 2605716
FIELD: aircraft engineering.SUBSTANCE: invention relates to structural material for making structural elements on the basis of plastic reinforced by hydrocarbon fibre, of fuel tank, of the main wing and aircraft. Structural material contains plastic reinforced by carbon fibers, wherein the reinforcing material includes carbon fibres, and matrix contains plastic, material for protecting the surface with low viscosity, which is imparted with conductivity due to application of plastic reinforced by carbon fibers on the surface, on which the ends of carbon fibres exude.EFFECT: invention ensures reduction of time and cost of the structural elements production process without increasing their weight.6 cl, 7 dwg
ethod of emergency aircraft landing in case of impossibility to reach the nearest airport // 2605670
FIELD: aviation.SUBSTANCE: invention relates to means of emergency aircraft landing. Method of emergency aircraft landing involves using an automatic braking device including dowel-piles, an resilient elastic halyard and a dowel-gun. In case of impossibility of an aircraft to reach the nearest airport a flat landing site shall be found, the length of which is at least 1.5-1.3 of the halyard length. Aircraft is landed at the beginning of the landing site. When the aircraft landing gear touches the landing site, a dowel-pile is automatically shot in by means of the dowel-gun. Braking device partially brakes the aircraft movement via the braking resilient elastic halyard till complete stop of the aircraft. Passengers are evacuated.EFFECT: invention is aimed at landing an aircraft outside an airport.1 cl

Vertical take-off and landing aircraft (versions) // 2605667
FIELD: aircraft engineering.SUBSTANCE: invention relates to aviation and space engineering, particularly, to VTOL aircraft designes. Vertical take-off and landing aircraft includes jet power plants containing compressors, bypass valves, receivers, a nuclear power plant. Turbine are equipped with hybrid engines with the ability to operate both from electricity and liquid fuel. Each turbine on the aircraft outer side has a corrugated tip consisting of two parts: a base and an extending part. Herewith bases of the corrugated tips on the turbine are hinged to rotate around their axes and are connected to the device of side orientation to change the discharge side, and the second part of the corrugated tip is connected to the automatic angle control device, which, if necessary, extends out of the body one side of the corrugated part for changing the discharge angle by more than 90 degrees from vertical to horizontal planes.EFFECT: higher efficiency and reliability of the aircraft.8 cl, 10 dwg

Adjustment connecting device // 2605666
FIELD: machine building.SUBSTANCE: invention can be used as device for fixation of equipment to spacecraft airframe design. Adjustment connecting device has a set of fasteners for hinge joint, frame, on mounting surfaces of which there are adjustment units. Adjustment units consist of two straps with spherical mating surfaces, one of straps has extending from it four guys and three additional sets of fastening elements forming a hinge joint.EFFECT: technical result is improvement of reliability and ease of installation of equipment, higher quality of adjustment.3 cl, 5 dwg

ethod of engine arrangement on "flying wing" type aircraft // 2605653
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering. Method of engine arrangement on “flying wing” type aircraft consists in fact, that engine nacelle (1) is installed in wing (2) trailing-edge assembly so, that gap between engine nacelle (1) lower point and wing (2) surface is (0.37-0.41)D, where D is air intake inlet cross-section inner diameter.EFFECT: invention increases aerodynamic quality.1 cl, 1 tbl, 6 dwg

Supersonic convertible aircraft // 2605587
FIELD: aviation.SUBSTANCE: invention relates to aircraft engineering. Supersonic convertible aircraft comprises airframe including foreplane, vertical fins, front triangular gull wing, rear wing with trapezoidal outer wings, boost power jet engine and auxiliary cruise ramjet engines. Front wing and rear wing are arranged in closed structure of longitudinal triplane with possibility of in-flight configuration conversion.EFFECT: invention is aimed at increasing of flight noiselessness by improving of wings laminar supersonic flow.6 cl, 3 dwg

Supersonic low-noise aircraft with tandem wings // 2605585
FIELD: aviation.SUBSTANCE: invention relates to aviation. Supersonic aircraft with tandem wings has a triplane longitudinal arrangement and comprises a fuselage with smooth coupling of extensions of delta in plane wing (1), low rear inverted-gull wing (8), front horizontal tail (6), a vertical tail made integral with stabilizer (7), two jet turbine bypass engines, the front and the rear parts of which are installed respectively under the gull wing and along outer sides thereof with the stabilizer cantilevers and a tricycle landing gear. Fuselage (3) is equipped with cone-shaped damper (4) of the sound shock in nose fairing (5). Wings are made respectively with negative and positive angles of their transverse V, feature variable sweep and make a diamond-shaped closed structure at the front view. Stabilizer is made of a reverse V-shape with a rounded top and is equipped with nacelle (14) of the engine.EFFECT: invention provides higher aerodynamic efficiency of the aircraft.7 cl, 1 tbl, 3 dwg

Vertical take-off and landing aircraft // 2605466
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering, particularly, to vertical take-off and landing aircraft. Vertical take-off and landing aircraft comprises a fuselage, a lift-cruise engine and its thrust vector changing mechanism. Fuselage is composed as a disc-shape flying wing, and the lift-cruise engine is mounted at the angle of 30-60° to the longitudinal axis of the aircraft with the possibility of suction of the air flow from the wing upper surface and ejection of the air flow from the lift-cruise engine to the lower part of the wing. Thrust vector changing mechanism is made in the form of a set of rotary guide blades installed in the lower part of the wing in the air flow from the lift-cruise engine with the possibility of changing the thrust vector from 0° to 105° to the longitudinal axis of the aircraft. Wing features a longitudinal self-balancing S-shaped profile.EFFECT: provided is a simplified design of the aircraft power plant.4 cl, 6 dwg

ethod of transport space system controlling // 2605463
FIELD: transport.SUBSTANCE: invention relates to transport spacecraft (TSC) flights between two orbital stations (OS), one of which is located on atmosphere planet orbit, and another one is either on other celestial body orbit (for example, the Moon) or near libration points (for example, L1 or L2 of Earth-Moon system). Proposed method comprises TSC undocking from circumplanetary OS, its bringing on boosters (BM) module support orbit, TSC approach and docking to BM module. Then to formed packet pulses for flight to remote OS are applied. For return travel to TSC reverse pulse is applied and then, several series of flights in planet atmosphere are performed for TSC deceleration to circular on circumplanetary OS orbit. After that, TSC is docked to OS.EFFECT: technical result is possibility to create over a short period of time and at low costs on its development of transportation system between Earth OS and remote OS.1 cl, 4 dwg
ethod of determining deformation of spacecraft hull in flight // 2605232
FIELD: space.SUBSTANCE: invention relates to space engineering. In the method for determining deformation of a SC hull in flight fixed is a camera on the inner surface of the SC window in a preset position, as reference points selected are points on the outer surface of the SC within the photocamera field of view, and fixed are directions from the camera to the reference points. During the flight measured is acute angle α between the normal to the plane tangent to the outer surface of the SC in the reference point and the direction towards the Sun. Acute angle β is measured between the optical axis of the photocamera and the direction towards the Sun. To achieve the required illumination of the reproduced reference point the SC orientation is changed until angle α reaches the specified value, and angle β reaches the value exceeding the value of the camera angle of view. Performed is a series of images of the reference point for a selected interval of flight. Obtained images of the reference point are successively overlayed on each other and the reference point images shift on the photography is used to determine the SC hull deformation.EFFECT: technical result of the invention is reliable and accurate determination of the SC hull deformation.1 cl
ethod for semi-automatic control berthing // 2605231
FIELD: space.SUBSTANCE: invention relates to traffic control of abutting spacecrafts (SC). Method provides the touch of active (AC) and passive (PA) of the SC with required missiles of velocity, for which regulate the speed of berthing depending on the distance. By the outer command is performed automatic orientation of AC relative to the same coordinate system, in which the docking station PC is oriented. Control of movement of the mass AC centre of in plane perpendicular to longitudinal axis of the AC, is carried out by a deflection angle of mating target relative to the supported coordinate system. This angle is determined visually as per deviation of external cross of a target relative to the crosshairs of the optical means of observation external environment.EFFECT: technical result of invention is increasing of quality of controlling berthing in the presence of interaction of control channels, delays in channels of transmitting an image of the target and when transmitting instructions from control handles on the AC.1 cl

ethod of controlling spacecraft crew readiness to emergency situations and system for its implementation // 2605230
FIELD: astronautics.SUBSTANCE: group of inventions relates to spacecraft (SC) crew readiness to emergency situations monitoring method and system. To control crew readiness emergency situations extraordinary situation is simulated, determining astronauts readiness to emergency situation by comparing astronauts current coordinates parameters, using infrared radiation emitters and detectors, with given values, crew readiness control system comprises devices for visual information display, unit of SC systems models, training control unit, emergency situations setting unit, reference actions parameters setting unit, level of training determining unit, units of infrared pulsed signals emitters, radio receiving devices, infrared radiation position-sensitive detectors, optical systems, infrared signals reception data generation units, radio receiving-transmitting devices, radiation control commands and infrared signals reception unit, synchronizer, infrared radiation detectors location setting unit, optical systems parameters setting unit, from detectors to emitters directions parameters determination unit, emitters location coordinates determination unit, astronauts fixed positions display unit emitters at fixed position relative position parameters determination unit, astronauts position parameters determination unit, astronauts performed operations information analyzing and recording unit, astronauts reference positions setting unit, emergency situations events parameters simulation unit, audio playback units, audio recording units, radio device interface with screen and audio recording and playback units, data exchange system, connected in certain manner.EFFECT: accurate determination of crew members current position relative to SC systems and elements.2 cl, 3 dwg

Helicopter onboard equipment complex based on integrated modular avionics // 2605222
FIELD: aircraft engineering.SUBSTANCE: helicopter onboard equipment complex contains k-intelligent widescreen indicators, control system of common-helicopter equipment, integrated system of backup devices, information system of altitude-speed parameters, meteo navigation radar station, integrated monitoring system, computer system of helicopter-navigation, complex control system onboard communication system, radar altimeterd/doppler speedometer, emergency rescue radio beacons, radio station-transponder, display system of emergency and notifying signalling, cockpit lighting control system, set of inner lighting and signaling equipment, multispectral computer vision system, channel of standard data exchange, video data exchange channel, onboard computer system, gimballess inertial navigation system, indicator on windscreen, system for measuring mass and center of mass, integrated radio-navigation system, onboard system of video surveillance and recording, main high-speed fail-safe data exchange channel, interacting in certain manner.EFFECT: increasing of technical and operational characteristics, wider operating conditions, higher safety are achieved.1 cl, 1 dwg

Pulse jet propulsion plant of spacecraft // 2605163
FIELD: astronautics.SUBSTANCE: invention relates to space engineering and can be used for correction of manned spacecraft (SC) orbits. Pulse jet propulsion plant comprises a solid-polymer water electrolysis unit, the hydrogen cavity input of which is hydraulically connected with a sealed tank with water having a supercharging union, a gas-liquid separator connected to the output of the hydrogen cavity of the electrolysis unit and coupled with its input by a bypass line, where there are a pump, a hydrogen storage cylinder and a jet engine interconnected by a pneumatic line with a valve, as well as a controlled current source connected to the electrolysis unit. Plant includes connected to the controlled current source an electrochemical hydrogen compressor, the input of which is pneumatically connected with a gas cavity of a gas-liquid separator, and the output - to the cylinder for hydrogen storage and the supercharging union of the water tank by pneumatic lines with valves, herewith on the second of them there is also a pressure reducer, herewith the electrochemical hydrogen compressor has a bypass discharge pneumatic line with a valve connecting the output of the compressor with its input.EFFECT: invention provides improved of life and reliability of a pulse jet propulsion plant of a spacecraft.1 cl, 1 dwg

ethod of aircraft engines synchronization // 2605140
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engines control. Method of aircraft engines synchronization by means of activation logic, intended for checking safety conditions and/or activation for use of synchronization, where activation logic detects deactivated state, readiness and activated states. Method further includes synchronization transition from deactivated state into readiness state, when command for activation is given by aircraft pilot; synchronization transition from readiness state into activated state, when certain safety and/or activation conditions are met and synchronization transition from activated state or readiness state into deactivated state, when command for deactivation is given by pilot or when safety conditions are not met.EFFECT: reduced risk for engines.10 cl, 4 dwg

Short takeoff and landing aircraft // 2604951
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering, particularly, to short takeoff and landing aircraft designs. Aircraft comprises wing (1) made together with fuselage according to “flying wing" aerodynamic design. In fore end wing (1) is equipped with support (2), on which above wing top surface (1) power plant is installed, including engine (3) with propeller (4). On support (2) foreplane (5) and canard fin (6) are also installed, which are control elements. Engine (3) with propeller (4) is installed so, that during air flow blowing, created during propeller (4) rotation, wing top surface (1) was most complete in blowing area, as well as that controls, foreplane (5) and canard fin (6) were in blowing area.EFFECT: higher efficiency of control elements in wide range of angles of attack in pitch, roll and yawing, which substantially improves aircraft maneuverability.4 cl, 2 dwg

Device and method for active power feedback control for control device // 2604950
FIELD: aircraft engineering.SUBSTANCE: group of inventions relates to aircraft, method and device for aircraft control device power feedback control. Device for control device active power feedback control has computer, position sensor, drive. For control device active power feedback control, control device is moved using computer controlled drive, control device current position is measured, setting current entering drive modulation is performed, saturation limit is formed in a certain manner, by means of which setpoint current is saturated by upper and lower limits. Aircraft comprises control unit, control device, control device of active power feedback control device.EFFECT: higher reliability, accuracy and flexibility of mini control wheel control system.10 cl, 5 dwg

ethod of ice and snow removing from aircraft surface // 2604921
FIELD: airfield equipment.SUBSTANCE: invention relates to aircraft surfaces servicing during preflight preparation in winter time. Method of ice and snow removing from aircraft surface consists in preparation of mixture of hot and cold air to certain temperature and following heating of critical aircraft surfaces with it. Heating of critical aircraft surfaces is performed during preflight preparation on ground through an aircraft anti-icing system by controlling ejectors gates. Snow-ice mass is removed from aircraft critical surfaces by aircraft breakaway.EFFECT: invention simplifies preflight preparation and reduces duration of aircraft critical surfaces cleaning of ice and snow.1 cl, 5 dwg

Airborne early warning airship // 2604914
FIELD: radar ranging and radio navigation.SUBSTANCE: invention relates to air navigation of radar early-warning systems. Airborne early warning airship comprises a shell, nacelle, engine, screw and airborne radar, installed in the nacelle. Antenna system of the airborne radar is made in the form of an active phased antenna array. Receiving-transmitting modules and a power distribution system are mounted in the shell material of the airship on one of its sides. On the opposite side of the shell there is a control marking. In the nacelle there are a starting platform for an air drone, tracking system and channel for controlling said air drone, which is equipped with two weakly directional radiators.EFFECT: invention provides higher efficiency of detecting stealth targets.1 cl, 2 dwg

Device for aircraft transportation and maneuvering // 2604903
FIELD: aircraft engineering.SUBSTANCE: device relates to airfield equipment intended for aircraft transportation. Device comprises tractor with rotating in horizontal plane platform arranged on it, on which pneumo-fabric elevator is rigidly fixed by its lower part, on upper part of which there platform is arranged made of two parts in form of aircraft fuselage, interconnected by power hydraulic cylinder with possibility to move in horizontal plane. Platform includes movement mechanisms and electronic unit with display and audio warning device, located in tractor cabin. Platform and tractor rear transverse frame additionally include sensors, determining when tractor and platform are located under aircraft fuselage and transmitting these data to electronic unit with display and audio warning device.EFFECT: technical result is aircraft transportation preparation process automation and, as a result, higher safety during performing these operations and accuracy of tractor movement and maneuvering under aircraft fuselage, reduced duration of these works.1 cl, 2 dwg

Space objects path changing device // 2604902
FIELD: space.SUBSTANCE: invention relates to protection means and intended for massive space bodies orbit changing, threatening collision with the Earth. Device consists of housing, guidance and orientation system, laser range finder. In housing heat insulated container with metal hydride is located, produced by saturation electrochemical process or based on nickel matrix, having various versions of their hydrogen saturation. In housing head part set of impact elements is arranged in barrel, generally, from 2 to 5 pieces, having own guidance and orientation system. Device approaches space body with hyperbolic speed. At impact elements collision with space object large inner energy is released and funnel is formed, functioning as “nozzle” for products of said elements explosions.EFFECT: technical result of invention is more efficient change of threatening space body flight path.1 cl, 1 dwg

Device for installation on satellite of orbital spacecraft // 2604765
FIELD: space.SUBSTANCE: invention relates to equipment of spacecrafts (artificial satellites) and means of its deployment in orbit. Device has two identical mutually balanced in terms of weight pairs of linear guide mechanisms, installed symmetrically in vertical parallel planes. Each pair, in its turn, comprises pair of flat mirror symmetric and balanced cantilever mechanisms with common support horizontal crossbar. Top ends of outer wings are jointed with deployed spacecraft (SC) in area of its center of gravity, while bottom ends are articulated with crossbar slides. Latter are provided with drives of their synchronous movement in mutually opposite directions. Device provides movement of center of mass of SC along local vertical direction, meeting equilibrium position of satellite in circular working orbit.EFFECT: technical result of invention consists in reduction of disturbing actions on satellite during SC deployment in orbit.8 cl, 7 dwg

Device of warning about aerological phenomena for aircraft // 2604761
FIELD: aircraft engineering.SUBSTANCE: device of warning about aerological phenomena comprises on-board equipment capable to identify meteorological phenomena, a module for collection and storage of meteorological data, a module for creating a summary of collected meteorological data, a module for sending the summaries, a module for receiving the summaries from other aircraft, a module for processing, consolidation of the received summaries and forming warnings, a module for facilitating the go-around, an input module, a module of interactive dialogue, a module for polling other aircraft and collecting data from them. Module for processing and consolidation comprises a system of data fusion containing a fusion module located at a station on the ground. Fusion module comprises a ground/air communication module.EFFECT: provided is higher flight safety due to receiving meteorological information from aircraft and from the ground.5 cl, 3 dwg

Turbo machine with propeller (-s) for aircraft with propeller pitch change system // 2604760
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering, particularly, to propeller pitch changing devices. Turbo machine (1) comprises propeller pitch changing system (23) containing linear action circular control hydraulic power cylinder (25) and connection mechanism (26), connecting power cylinder with propeller blades to change their orientation. System circular power cylinder (25) is rigidly connected with fixed housing (13) on which said propeller is retained, and is internal relative to blades installed in propeller external rotary bushing (14). Connection mechanism (26) has movement transmission bearing (31), attached with one side to power cylinder movable part and interacting, from other side, with mechanism (26) connection means (32) to propeller blades.EFFECT: higher air-tightness, reduced overall dimensions with guaranteed reliability during operation.14 cl, 3 dwg

Vertical or short takeoff and landing universal unmanned aircraft // 2604755
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering, particularly, to designs of drones. Universal drone comprises fuselage and wing, made according to "flying wing" (1) aerodynamic design, as well as power plant, installed on support (2) and made in form of engine (3) and propeller (4). Power plant is installed in nose part of wing (1) on support (2) with possibility of blowing both wing top surface (1), and additional controls, fixed on power plant support (2) and made in form of foreplane (5) and canard fin (6). Takeoff and landing supports are made in form of three symmetrically arranged telescopic supports (7, 8 and 9). Support (7) is equipped with rudders (10). Supports (8) and (9) are equipped with controlled rotary hydrofoils (11) and chassis (12). On wing lower surface (1) in its front part additional support (13) is installed, provided with controlled rotary hydrofoils (14) and landing gear (15).EFFECT: aircraft higher maneuverability by pitch, roll and yawing in wide range of angles of attack.1 cl, 3 dwg

Helicopter car (versions) // 2604750
FIELD: transport.SUBSTANCE: invention relates to vehicles designs, able to move on ground and in air. Helicopter car includes motorcar-shaped body with cockpit, steering system, gyrostabilizer, parachute, louver flaps, power plant, closed with fairing, forming air channel with body. Lifting and propelling machinery is made in form of two lengthwise arranged propellers, one of which is arranged in front of cockpit, and other one is behind cockpit. Propellers are connected by means of individual reduction gears, couplings, main drive shaft and belt drive to power plant. Front propeller reduction gear is connected to main drive shaft via front wheels drive reduction gear. Air rudders are arranged under propeller in body lower front part. Under louver flaps, arranged behind cockpit, two transverse arranged propellers can be installed, actuated by means of belt transmissions from common shaft, connected to main cardan shaft by means of coupling and reduction gear. Louvre flaps are connected with gyrostabilizer.EFFECT: enabling possibility to simplify converted vehicle design and reduce its dimensions.2 cl, 7 dwg
 
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