Aircraft and aviation and cosmonautics (B64)

B64            Aircraft; aviation; cosmonautics(13655)
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

Aerostatic apparatus // 2628828
FIELD: aviation.SUBSTANCE: apparatus contains a gas-filled shell with a gas release valve, a gondola suspended on the cables to the shell. A number of parallel stretchable folds are horizontally installed in the shell wall with the possibility of changing its volume. The folds are spring-loaded with the possibility of their stretching/compressing when the density of the air environment changes.EFFECT: flight safety increase.4 dwg

Aircraft body // 2628826
FIELD: aviation.SUBSTANCE: body for starting acceleration uses a hydro-gun, which consists of a transverse tube filled with water, with radially located nozzles at the ends. In order to displace water from the tube, either a medium-level powder cartridge or a device producing an explosive mixture of hydrogen and oxygen by water electrolysis is used.EFFECT: technical means arsenal expansion.5 cl, 2 dwg

Air balloon shell // 2628824
FIELD: aviation.SUBSTANCE: air balloon shell on the wall of which on the outside there are light sources, and in the wall on the bottom there is an opening for entering the air heated by a burner. The light sources are arranged linearly along an arc of a circle. The opening for entering the air heated by the burner has a shutoff valve. The light sources in the form of tapes with LEDs are connected to each other in series/in parallel by conductors of electric current. The valve is made in the form of a gate located under the shell. The valve is made in the form of a flap located in the cavity of the shell.EFFECT: increased safety of the air balloon flight.4 cl, 7 dwg

Hot air balloon shell // 2628823
FIELD: aviation.SUBSTANCE: in the hot air balloon shell, which has a valve for the warm air release in the wall at the top, a bottom hole for the entry of the air heated by the burner, the gondola attaching cables covering the wall, an expanding/folding glare shield is attached on the spokes to the shell wall from above along the horizontal perimeter. The free end of the spoke is connected to the cable by a cord. The glare shield has openings for cables and air passage. The glare shield can be equipped with removable cylinders with gas lighter than air.EFFECT: increase in the lifting force of the hot air balloon shell.4 cl, 9 dwg

Airship hull // 2628822
FIELD: aviation.SUBSTANCE: airship hull contains a shell in the form of a longitudinally located central section with a rigid wall and convex side sections, yaw rudders, elevation rudders, mooring elements. Between the edges of the central and lateral sections, a series of parallel, stretchable folds are installed, each of which is spring-loaded with the possibility of stretching/compressing as the density of the air environment changes. Elevation rudders are installed on the lateral sections of the shell.EFFECT: allows to change the volume of the airship with a change in the density of the air environment.3 cl, 4 dwg

Device for the air removing from the water-air jet, incoming while the water withdrawal at the amphibious aircraft gliding // 2628632
FIELD: aviation.SUBSTANCE: device for removing the air from the water-air mixture, incoming while the water withdrawal at the amphibious aircraft gliding, contains the inlet pipeline, supplying the water-air jet, the device body with the helical screw located therein and the air discharge pipeline, the outlet pipeline, supplying the liquid to the aircraft tanks. In this case, the front part of the body device is made in the form of the truncated cone, on the inner surface of which the screw ribs of variable height and pitch are rigidly fixed. The diffuser grid is installed in the outlet pipeline. At that the air discharge pipeline from the device is exposed to the nozzle cut-off of the amphibious aircraft jet engine.EFFECT: maximum filling of the floated aircraft tanks with water by increasing the efficiency of the air-water jet deaeration, the simplicity of the device design.5 dwg

ultipolimeric composite structures and their production method // 2628607
FIELD: aviation.SUBSTANCE: rigid flexible composite structure includes textile construction from at least one textile layer, consisting of textile fibers, and having distribution of pores in it. The pore distribution includes a plurality of pores within the fibers in individual textile fibers and a plurality of pores between the fibers. The structure includes the first polymer that fills pores having a pore diameter equal to or less than pore diameter threshold, and the second polymer that is bonded to the first polymer and substantially fills pores having a pore diameter larger than the pore diameter threshold. Some embodiments include a rigid first polymer, such as an epoxide, and a flexible second polymer, such as silicone. The method for producing the composite structure includes selective filling in a textile layer, having a plurality of pores, only of those pores, diameter of which is equal to or less than the pore diameter threshold by the first polymer, and substantially filling the remaining pores in the textile layer with the second polymer.EFFECT: creation of composite material for coating or obtaining the skin of an aircraft having a mechanical stability suitable for forces acting on it.16 cl, 8 dwg

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

System of winglets and method of improving the flying-technical characteristics of an aircraft plane // 2628548
FIELD: aviation.SUBSTANCE: winglet system for a wing contains an upper winglet and a lower winglet mounted on the wing tip. The lower winglet has a static position when the wing is subject to static loading when parking on the ground. The lower end flap is designed so that the wing deflection upward with a flight load of approximately 1g causes the lower winglet to move from the static position to the flight position, resulting in a relative increase in the span of the wing. The aircraft contains a system of winglets that are located at the intersection of the gate gap and the lumen line at pitch and roll. Method of the aircraft operation is characterized by the movement of the winglets.EFFECT: reduction of inductive drag of the wing.20 cl, 15 dwg
Tethered balloon with the autogyro screw stabiliser // 2628545
FIELD: aviation.SUBSTANCE: tethered balloon has a body of the soft design, rigging, rope tether unit and tail assembly. The lateral stabilisers of the tail assembly are formed by the autogyro screw, the axis of rotation of which is fixed at the top of the vertical stabiliser at the constant angle to the construction horizon.EFFECT: design simplification and take-off weight reduction.2 cl, 1 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

Wing and fin panel or operation of air vehicle from layer composite materials // 2628416
FIELD: aviation.SUBSTANCE: panel contains a skin with a smooth flat outer surface of geometric shape and a framework attached to it in the form of a system of criss-crossing ribs consisting of layers fastened with a polymeric binder, unidirectional high-strength and/or high-modulus yarns and/or fabrics. And in the space between the ribs porous material is located, with formation with the latter of equidistantly outer surface of the skin of a continuous smooth surface on which strips of woven material, with perpendicular to the surface flanges, that are fastened with it by adhesive or polymeric binder in the longitudinal direction of panel between the longitudinal ribs impregnated with the binder, space between which is filled with an impregnated polymeric binder, oriented in the direction of strips arrangement, unidirectional reinforcing material with formation of power stringers coated by woven fabric material, constituting integrally with framework longitudinal ribs.EFFECT: increasing the strength and reliability of the skin connection with power stringer, simplifying the manufacturing.8 cl, 1 dwg

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
Anti-tank mine "strekosa-m" with possibility of spatial movement with hovering and reversibility in air, reconnaissance, neutralisation, and damage of mobile armoured targets // 2628351
FIELD: weapon and ammunition.SUBSTANCE: anti-tank mine contains a cumulative combat element fixedly connected to a multi-copter, with the vertical position of the axis of the cumulative lined funnel of the combat element with the horizontal position of the multi-copter, electric propellers, a power supply, a control system at a safe distance by onboard devices and a surveillance system, at least, through technical vision, as well as a support and landing device oriented vertically downward along the axis of the cumulative funnel at the distance with its peripheral part from the air screws on top. At the same time, the combat element is connected to the multi-copter with the cumulative funnel orientation of the combat element vertically upwards with the horizontal position of the multi-copter, opposite the orientation of the landing gear, with the possibility of repeated shunting-landings of the mine and its destruction from the bottom and the chassis of the latter from its ground position, and the electrical equipment and the control system are configured to differentially control the speed and direction of rotation of the non-aligned propellers to ensure the ability of maneuvering by turning the multi-copter by 180°.EFFECT: increasing the combat characteristics of an anti-tank mine with the possibility of spatial movement with hovering in the air, reconnaissance, neutralisation and single defeat of mobile armoured targets.5 cl, 11 dwg

Fuel tank, main wings, air frame, aircraft and vehicle // 2628291
FIELD: aviation.SUBSTANCE: invention relates to the fuel tank of the aircraft's main wing (AC). The fuel tank contains the structural unit that is using plastic reinforced with carbon fiber. Plastic includes a reinforcing material which comprises carbon fibers and a matrix that contains plastic. The structural unit is formed by laminating a conductive sheet between prepregs of plastic reinforced with carbon fiber. Moreover, carbon fiber included in reinforcing material is exposed in internal circuit in which fuel is stored on the cut surface at the end of structural unit formed by cutting off the structural unit.EFFECT: reduction of labour intensity of production, weight reduction of aircraft structure, increase of conductivity.6 cl, 7 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

Fuselage composite sections junction along window zone // 2628262
FIELD: aviation.SUBSTANCE: fuselage comprises a composite cover comprising a top and bottom composite cover sections, a window zone with a composite cover comprising a window opening in the composite cover and a longitudinal butt joint along the window zone connecting the upper and lower cover sections to each other. Moreover, the edges of the upper and lower covers are joined to each other along and within the window zone during the fuselage barrel assembly production work.EFFECT: increased strength and rigidity of the structure, reduced weight, manufacturing time.15 cl, 26 dwg

ethod of bringing the aircraft in the landing start point // 2628043
FIELD: aviation.SUBSTANCE: aircraft's current coordinates are measured in order to bring the aircraft to the landing start point, the route section is previously plotted as a straight line of the specified path, which is tangential to the arc of the aircraft's awning turn to exit to the axis of the runway at the landing start point with the heading towards its center, the route from the point of return by an arc of a preliminary turn of a given radius is defined for exit of a given path by a straight line tangential to it, four possible routes of combinations of right and left preliminary and pre-departure turn are constructed, the length of their way is calculated, a fly is performed along the route with the minimum path length to the point of the landing start point.EFFECT: shortening the time of bringing the aircraft to the landing start point.2 dwg

Control method for dynamic balancing of helicopter main and steering rotor blades // 2628034
FIELD: aviation.SUBSTANCE: for the control of dynamic balancing, metrological examination is carried out to estimate the validity of signals from sensors and measurement systems, anomalous emissions in the measurement sequence are rejected, training measurement arrays are accumulated first for the helicopter hover condition without turning in the horizontal plane. Then in various modes and at various speeds of horizontal flight and then in all controlled flight modes, individual tolerance limits of dynamic symmetry parameters are formed, the current dynamic symmetry parameters are measured and compared with the tolerance limits. The control is carried out online on board the helicopter and on ground registered data processing device, after the flight, taking into account the results of the previous operation.EFFECT: regular reliable control of the balance of the main and steering helicopter rotors and their blades is ensured.1 dwg

ethod of flying vehicle clearance change at parking and actuating strut (versions) // 2628002
FIELD: aviation.SUBSTANCE: invention relates to a method of flying vehicle (FV) clearance change at parking by changing the position of the chassis supports. At parking, the FV clearance is changed by moving the chassis supports. The rotation of the chassis supports is carried out with the help of the actuating struts mounted on the aircraft and connected to the chassis supports. Actuating struts are made in the form of a hydraulic or pneumatic cylinder with a rod and fix the landing gear in the intermediate and extreme positions.EFFECT: expanding the functionality of the support, reducing the vertical dimensions of the aircraft at parking and storage without affecting the working fluid of the shock absorber and without reducing the pressure in the pneumatics, quick aircraft initialization without using ground equipment.9 cl, 9 dwg

Unmanned high-speed helicopter, desantified from plane aircraft // 2627975
FIELD: aviation.SUBSTANCE: unmanned high-speed helicopter, dropped from a carrier aircraft, has a rotor, an engine, traction and steering screws, a tricycle landing gear. The helicopter is made using the multi-mode aerodynamic control technology, providing super-maneuverability and balancing on pitch, roll, and course by means of various steering screws. The support screw, executed without control of a cyclic step with the rigid fastening of blades, is mounted on a hollow support located coaxially inside its shaft. The support is rigidly fixed at its lower end to the main gear housing, and the upper is centered relative to the shaft by means of a bearing assembly. The upper part of the hollow support is fixed in a teardrop-shaped fairing having a docking/undocking unit in the front part, and in the upper part, there is a container with an exhaust and main parachute. The swept top wing forms with a low-lying straight swept wing a biplane design that forms an X-shaped configuration in plan.EFFECT: improved controllability with hovering, the possibility of landing and docking, undocking with a carrier aircraft.3 cl, 2 dwg
High-speed amphibious rotorcraft // 2627965
FIELD: aviation.SUBSTANCE: high-speed amphibious rotorcraft (HARC) has a two-screw coaxial scheme with carrier screws, a power plant with engines transmitting torque through the main reducer and transmission shafts to the main rotors and propulsion screws in the annular channels, wings of the same size of the high-lying "tandem" scheme and retractable Wheeled chassis. The HARC is made using multi-mode aerodynamic control technology with a propulsion-steering system in the form of coaxial dome-and cup-shaped carrier screws (DCSCS) according to the scheme DCSCS-X2+2, which includes a lower and upper three-blade propellers above the convex profiled fairing, Reverse and straight V-shape of the root zone of the respective blades, and two traction screws in annular channels with controlled thrust vector located on the inner sections of the rear wing.EFFECT: reducing the height of the main gearbox and the required power for pitch and roll control when hovering.3 cl, 1 tbl, 1 dwg

Unmanned rotorcraft with cross-section propellers // 2627963
FIELD: aviation.SUBSTANCE: unmanned rotorcraft with crossed propellers (URCP) is made with two-bladed screws, has on the top of the fuselage the engine that transmits torque through the main reducer to the transverse rotor screws mounted on long shafts, contains vertical tail and a three-wheel retractable wheel chassis. The URCP is designed with a propulsion system based on the concept of distributed traction of criss-cross propellers (DTCP), arranged in accordance with the DTCP-X2+2 scheme in two transverse two-screw modules at the ends of the wing. The modules contain a variety of screws mounted on each pivot sector, a pylon mounted in the front longitudinal semi-circular aperture of the teardrop fairing on the wing tip. URCP is equipped with a reducer with an upper arrangement of V-shaped output shafts located at an angle of 30° Between them. The smaller and larger propellers are located above the wing in the upper hemisphere in the first and second quadrants and have the possibility of deflection parallel to the symmetry plane forward and backward.EFFECT: increase in the weight return, reduction of the required power for the road balance during hovering and improvement of transverse and longitudinal controllability.2 cl, 1 dwg

ethod and apparatus for developing an aircraft warnings and procedures control system // 2627935
FIELD: aviation.SUBSTANCE: to develop the system, warnings are checked in the database for each system equipment unit in relation to a predetermined list of mandatory warnings, the completeness criterion is determined and calculated for the first sub-stage, the completeness criterion is determined and calculated for each of the subsequent stages, comparing the completion criteria of the previous stage with a predetermined threshold for that stage; system configuration is completed at the tenth stage after comparison with the tenth predetermined threshold value. The device for system development includes a simulator comprising a block for storing files and executable files, human-machine interfaces, containing a mouse, keyboard and a screen to display information, and a central processor.EFFECT: creation of standard procedures for development of an aircraft warnings and electronic procedures control system.3 cl, 3 dwg

Tawing helicopters // 2627912
FIELD: aviation.SUBSTANCE: towing helicopter contains a fuselage with a powerplant placed in it, a top-mounted carrier propeller, a torque reaction compensation propeller installed at the end of the tail boom, and a cockpit on the bow of fuselage. To the lower part of fuselage, a garland of aerodynamic wings is attached with transported cargo carried to it. The cockpit is enclosed in a sphere having the possibility of multidirectional rotation with respect to the fuselage. At least one half of the sphere is transparent. The sphere is rotated by rubberized wheel with an electric drive, frictionally interacting with its outer surface.EFFECT: providing comfortable conditions for crew in case of longitudinal slope of helicopter fuselage.4 cl, 2 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

Aircraft fuel supply systems // 2627883
FIELD: aviation.SUBSTANCE: group of inventions relates to fuel supply systems and methods during operation to the aircraft powerplant. The fuel supply system comprises a fuel pipe, a pump, located downstream, a pump disposed in the fuel tank upstream, a pressure sensor located on the inlet or near with the downstream pump and a controller. To supply fuel from the fuel tank to the aircraft powerplant, pumps are used located downstream and upstream, respectively, the pump is controlled in case of the absolute pressure drop at the inlet into the pump located downstream or close to it below a predetermined threshold value.EFFECT: required pressure for fuel supply.13 cl, 2 dwg

Generator of finely dispersed parts // 2627416
FIELD: machine engineering.SUBSTANCE: in the generator of finely divided formations, the axial ejector is in the form of a piston and is placed inside a rigidly fixed cylindrical body on the carrier. The working surface of the piston has gears. The diameter of each stage is determined from the relationship: di=n⋅D/(1+n)⋅i, where di - diameter of the stage of the working profile of the piston; n is the total number of steps; D - diameter of the piston; i=(1n…) is the step number from the center. The positive angle of declination of the steps relative to the end of the piston is: θ=θo+2Ūo/100⋅i, where θo - angle of declination of the central stage; Ūo - dimensionless speed of translational motion.EFFECT: providing the possibility of forming, at specified distances from the carrier, the correct shape of the lens of disperse formations with a uniform distribution of the fractions of the functional filling of the inseparable generator body.3 cl, 2 dwg, 1 tbl

Vertical takeoff aircraft // 2627261
FIELD: aviation.SUBSTANCE: aircraft (1) of vertical takeoff with a wing (3) comprises the engine first unit (4) and the engine second unit (5) mounted rotatably on this wing (3). The engine first unit (4) and the engine second unit (5) are disposed on the wing (3) at a distance from its tip (12). The distance from the engine first unit (4) to the longitudinal axis (10) of the aircraft (1) is approximately equal to the distance from the engine second unit (5) to the longitudinal axis (10) of the aircraft (1). In position of horizontal flight, the engine first unit (4) is on the wing above the surface of the wing, and the engine second unit (5) is on the wing under the wing plane. In vertical flight position, the engine first unit (4) and the engine second unit (5) are disposed in a single actually horizontal plane.EFFECT: increased efficiency of horizontal flight, and stable performance characteristics during vertical takeoff and landing are provided.14 cl, 5 dwg

Device for detection and prevention of swash of trailing-edge flaps // 2627259
FIELD: aviation.SUBSTANCE: device for detection and prevention of swash of trailing-edge flaps (1) comprises of a beam (2), fixed to the wing (4) and provided with guiding elements (3), and of a carriage (5). A pushing mechanism (7) is rigidly fixed to the beam (2) and a double-arm rocker (8) is hingedly mounted. The first arm (9) is connected to the first end (11) of the first spring (10), the second end (12) is connected to the beam (2). The rod (17) of the pushing mechanism (7) abuts against the end of the second arm (16) of the double-arm rocker (8). The end of the first arm (9) of the double-arm rocker (8) is in mesh with the trigger lever (13) mounted on the shaft (15) on the beam (2). The shaft (15) also has a lever with a cylindrical pin connected to the first end of the second spring. The second end of the second spring is connected to the beam (2). The above beam (2) is hingedly connected to the housing (24) of the trailing-edge flap position sensor (1). The end of the rod (25) of said sensor (24) is hingedly connected to one of the arms (27) of the double-arm lever (28), mounted on the beam (2), the second arm (29) of which is connected to the cowling (33) of the flap mechanism by an articulated rod (30).EFFECT: shortest load path.8 dwg

ethod of analysing aircraft collected flight data for the purpose of their division by the flight phases // 2627257
FIELD: aviation.SUBSTANCE: to analyze the flight data collected during the aircraft flight, the flight state model is determined corresponding to a particular flight phase, data is extracted from the collected flight data relating to characteristic aircraft parameters, the state model initialization criterion is calculated corresponding to its initial state, the plurality of state model transition is calculated based on flight data; flight data is divided for their binding to the flight phases. The flight data analysis system includes a processing module, a storage module to store the state models.EFFECT: sustainable data collection with division by flight phases.10 cl, 3 dwg

Vertical takeoff and landing aircraft // 2627220
FIELD: aviation.SUBSTANCE: aircraft includes a basic frame of a spatial structure, a seat, a cabin, controls, motors, a control system, a remote control system. The basic support frame is made with a central part and with two peripheral clusters on the right and left on the flight. Peripheral clusters can be folded up, down or pushed under the central part. The central part and peripheral clusters of the frame are made with a spatial construction. Each peripheral cluster is made of at least three identical sections connected to each other. Inside each section, there is a motor installation containing at least one engine and at least one horizontal rotation propeller.EFFECT: increase of fault tolerance, safety, and maintainability of the aircraft of vertical take-off and landing.24 cl, 34 dwg
ethod for displaying information on vertical displacement of shipborne landing strip when landing helicopter on ship // 2626802
FIELD: physics.SUBSTANCE: invention relates to a method for displaying information on vertical displacement of shipborne landing strip (LS) when landing a helicopter on a ship. In order to display the information, a multifunctional indicator of LS vertical movement is set vertically on the superstructure of the ship in the direction of the helicopter landing approach, heaving motion of the LS center is displayed using super-bright LEDs located parallel to the long side of the indicator in the form of a colourless bar chart. Its beginning is a group of LEDs of the same colour, indicating the beginning of the movement of the LS center, and its end is a group of LEDs of a different colour, which indicates the predicted completion of the LS movement. The amplitude of the colourless bar chart is proportional to the movement time of the LS center from top to bottom or from bottom to top. The indication symbol of the LS position, safe for helicopter approach is displayed by a group of LEDs of the third colour.EFFECT: safety of helicopter landing on the ship in difficult weather conditions and at different times of the day.3 dwg
ethod for displaying information on vertical displacement of shipborne landing strip when landing helicopter on ship // 2626801
FIELD: physics.SUBSTANCE: invention relates to a method for displaying information on vertical displacement of shipborne landing strip (LS) when landing a helicopter on a ship. In order to display the information, a multifunctional indicator of LS vertical movement is set vertically on the superstructure of the ship in the direction of the helicopter landing approach, heaving motion of the LS center is displayed using super-bright LEDs located parallel to the long side of the indicator in the form of a bar chart with groups of LEDs of different colour, one of which displays the beginning of the movement, and the other - the predicted completion of the movement. A symbol of the third type is displayed on the field of a colourless bar chart - a symbol for indicating the safe approach of the helicopter.EFFECT: safety of the helicopter landing on the ship in difficult weather conditions.3 dwg
ethod of minimizing zones of detachable parts exclusion of carrier rocket // 2626797
FIELD: weapon and ammunition.SUBSTANCE: in the method of minimizing the exclusion zones for the detachable parts (DP) of the carrier rocket (CR) during the pre-flight preparation stage, the CR calculates the parameters of the motion of the DP before they fall to the ground. Based on the results of the calculations, the sections on the descent path for impact on the DP are determined, they form a signal in the process of an autonomous DP flight, and effect the design of the DP. The pyrotechnic composition is placed on the DP. During combustion, the pyrotechnic composition ensures heating of the DP to a temperature at which their combustion takes place in the incoming flow of atmospheric air, after reaching a height of 25-30 km, the ignition of the DP is carried out using an igniting composition.EFFECT: maximum reduction of areas allocated for the areas of incidence of the DP CR.6 cl, 1 tbl
ethod of payload delivery to celestial body soil, provision for soil and celestial body exploration and device for its implementation (versions) // 2626792
FIELD: aviation.SUBSTANCE: invention relates to methods of payload delivery - of a scientific package to celestial bodies (planets, asteroids, comets, etc.) for their exploration and penetrator-device with payload, separated from the main space vehicle and representing an impact penetrating probe, penetrating into the soil of the celestial body for the exploration of the body and soil parameters. The invention provides a method for delivering payloads to a celestial body and a device for its implementation, according to which a payload is placed inside a ballast serving as an additional protective body for the payload, and high-strength ice modifications, such as ice-VII or ice-VIII, or ice-X, are used as the ballast material. After the impact penetration of the penetrator into the soil, the ballast and the scientific package in it are freed out of the protective casing, the ballast is removed, releasing the payload, and the soil of the celestial body is explored.EFFECT: increased impact resistance of the payload and higher measurement accuracy of the soil and celestial body parameters.10 cl, 5 dwg

Descent tow vehicle for retrieving space objects from orbits // 2626788
FIELD: aviation.SUBSTANCE: descent tow vehicle for removing objects from the orbits of artificial earth satellites contains a cargo container having a free volume for placing the object to be retrieved, an inflatable braking device with a flexible hermetic heat-resistant shell, adapted to obtain an aerodynamic shape when it is filled with gas. In this case, the inflatable braking device has outer contours in the form of a truncated cone and is made in the form of a set of torus-shaped elements. The device also contains a device for capturing the object to be retrieved, a navigation system for searching for the object to be retrieved from the orbit and a propulsion system for maneuvering the vehicle. The device for capturing the object to be retrieved is made in the form of truncated cone sectors, and the free volume for placing the object to be retrieved is in the form of a conical flare.EFFECT: expansion of the arsenal of space technology by introducing a simple descent tow veihicle for the rapid retrieval of objects from the orbits of artificial Earth satellites.2 cl, 3 dwg
Combined aircraft wing // 2626773
FIELD: aviation.SUBSTANCE: wing of the aircraft contains a bearing surface and a turbojet engine. The bearing surface is combined and made of a conventional aerodynamic wing and a carrier plate rigidly connected to it. The engine is rigidly fixed to the carrier plate so that the jet of hot gases emerging from it flows around its upper surface. The profile of the carrier plate repeats the profile of the turbojet engine Laval nozzle. Effective areas of aerodynamic plate and carrier plate are equal. The aircraft contains a fuselage with wings, the lifting force vectors of which and the center of gravity of the entire aircraft lie in the same plane perpendicular to the aircraft symmetry axis. The aircraft center of gravity is located below the points of application of all lifting forces.EFFECT: increased range, load capacity and safety of their use.2 cl, 4 dwg

Formation node of on-board navigation light radiation indicatrix // 2626464
FIELD: lighting.SUBSTANCE: forming assembly comprising a plurality of LEDs arranged on a flat board mounted on a base and a flat diffusely scattering reflector is provided with a flat partition. In this case, the flat diffusely scattering reflector is combined with the base. A flat board with LEDs is installed perpendicular to the flat base and is made in the form of a symmetrical structure of two groups of LEDs. A flat baffle is installed in a vertical symmetry plane perpendicular to the base. On the lateral surfaces of the flat partition, there are additional diffusely scattering reflectors creating additional light fluxes due to the rereflection of the LEDs light fluxes from the flat diffusely scattering reflector located on the base.EFFECT: simplified design.5 dwg
ethod of selecting grades of optical glasses for design of space equipment optical systems in long-term exposure conditions of space ionising radiation // 2626450
FIELD: physics.SUBSTANCE: method involves calculating, according to a known technique, the dose distribution of ionising radiation from outer space on the optical axis of each glass element of the optical system under operating conditions, taking into account the protective properties of the structure. Next, using computer algebra, the spectral density of these elements is calculated on the basis of the average dose rate of ionising radiation on the said optical axis and the characteristics of the kinetics (formation and relaxation) of the radiation colour of the glass of the element are calculated. The increase in the optical density of the optical system and the corresponding decrease in the spectral transmission coefficient of the optical system are determined. The reduction of this coefficient is compared with the permissible one and, if necessary, the optical glass grades are replaced in the elements with the maximum increase in the spectral optical density.EFFECT: optimisation of optical systems by preliminary estimation with the increased accuracy of decreasing their spectral transmittance during the period of active existence.1 cl

Propulsion unit // 2626419
FIELD: transportation.SUBSTANCE: propulsion unit includes a DC electric motor which shaft is rigidly connected to the actuator shaft. The synchronous generator is rigidly connected to the actuator and the electric motor. The first-sixth unit inputs of three power supply batteries are respectively connected to the first-sixth unit outputs of six releasers. The first, second and third outputs of the power supply unit are respectively connected to the first, second and third inputs of a unit of three releasers. The first, second and third outputs of the unit of three releasers are respectively connected to the first, second and third inputs of the unit of six releasers, the fourth and fifth inputs of which are respectively connected through the battery stabilization and charging unit, respectively, to the first and second outputs of the contactless synchronous generator. The DC electric motor has an input connected to the fourth output of the block of three releases, the fourth input of which is connected to the output of a control unit receiving electromagnetic energy.EFFECT: increased actuator's rotation time.1 dwg
Aqua aerospace vehicle // 2626418
FIELD: aviation.SUBSTANCE: aqua aerospace vehicle includes the body in the form of the biconvex lens, covered with the bottom and the top by the hemispheres of titanium aerodynamic fairings. The body is supported by the steel frame with stiffeners, on which the power unit is mounted. This unit contains four groups of engines: four lifting cruise bypass turbojets, two main rocket engines, four rocket engines of vertical lift and two water-jet engines. The air vehicle has the landing gear legs. The sealed gateway hatch is served for docking and communication with the interplanetary space station (ISS). There are the rear hemisphere lights and the aircraft lights on the vehicle body.EFFECT: creation of the multimode multifunctional vehicle for researches and other operations in near and far space, using for its refuelling the interplanetary space station and celestial bodies.11 cl, 11 dwg

Turboreactive engine gondola with the back section // 2626416
FIELD: engines and pumps.SUBSTANCE: invention relates to a nacelle of a turbojet engine having a rear section comprising at least one front frame (2) adapted for attachment to a fixed part of the nacelle. The rear section is provided with at least one rail or the slider (3). The slide extends substantially in the longitudinal direction of the nacelle and is configured to engage at least one corresponding rail or slider (3') of the turbojet engine strut fastener. The front frame is connected with the rail or the slider (3) of the rear section by means of at least one rotary connecting rod (7a, 7b).EFFECT: invention allows to compensate for relative movements of the turbojet engine and a pylon, and increases the structural strength.9 cl, 16 dwg

ethod and system of building in integrating extension boards to facilitate wire separation // 2625915
FIELD: electricity.SUBSTANCE: method of interconnecting electronic equipment inside of an aircraft (200, 300) includes installing multidimensional integrating board (320, 400) inside the aircraft (200, 300). Thus, the integrating board (320, 400) includes connectors (380, 410) mounted thereupon and the contacts associated with the connectors (380, 410) are interconnected by means of electrical conductors formed in the integrating board (320, 400). Herein, the on-board cabling of an aircraft (340, 342, 344, 346) is attached to the first part of connectors (380, 410) on the integrating board (320, 400) and the electrical connectors of the electronic equipment are attached to the respective connectors (380, 410) on the integrating board.EFFECT: provision of higher density of the equipment packaging due to the physical transfer of the wiring couplers in the previously unused space, reduced weight, cost and additional costs of space related to switchboards, reduced labour costs associated with the formation of complex wire harnesses and installation of switchboards, increased system reliability by eliminating extra splices of wires, connectors and wiring segments associated with switchboards.18 cl, 5 dwg

Surface facility surviellance system and targeting // 2625691
FIELD: aviation.SUBSTANCE: surface facility surveillance system and targeting contains the helicopter-type unmanned flying vehicle, the suspension container with equipment, and ground control equipment. The suspension container contains the sensors unit, the information-command radio link device, the radio navigation device, the targeting module on the gyrostabilized platform. The targeting module contains the container with payload, the video camera, the starter, the laser target designator and ranger. The ground-based equipment contains the portable video monitoring device with the information-command line equipment, four beacons with built-in optical and laser information channels.EFFECT: surveillance and targeting of the ground objects are provided with its marking and mapping.1 dwg

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

Elastomer control surface based on continuous bypassing processing technology // 2625478
FIELD: aviation.SUBSTANCE: elastomer control surface based on the continuous bypassing processing technology comprises the first control surface (712) connected to the hydrogasdynamic housing (704); and the first elastomeric coupling means (702) connected to the first control surface (712) and the hydrogasdynamic housing (704) such that the first butt gap (716) formed while the first control surface (712) moving relative to the hydrogasdynamic housing (704) is filled. The hydrogasdynamic housing (704) comprises a wing. The first control surface (712) comprises a movable trailing edge (706) with the possibility to move in the rear direction to increase the wing area on one side, and thus creating an additional lifting force and initiating a corresponding roll-off. The method characterizes the creation of an elastomer control surface.EFFECT: improved aerodynamic characteristics.14 cl, 9 dwg