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RussianPatents.com
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Control over hybrid helicopter speed Invention relates to aircraft engineering, particularly to control over hybrid helicopters. Helicopter comprises at least one rotor and one propulsive screw equipped with a set of variable-pitch blades driven by at least one engine. Proposed method comprises controlled flight wherein propulsive screw pitch control signals are generated by manual control member depending upon power consumed by said screw. Besides, it comprises correcting actions with the help of at least one limiting parameters of adjustment related with the hybrid helicopter strength characteristics. Pilotage instructions include preset air speed while correcting process is used proceeding from preset air speed in compliance with at least first correction mode. In compliance with this mode, pilotage instructions are corrected in compliance with the first law with allowance for preset consumed power corresponding to preset air speed. |
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Helicopter rotor (versions) and helicopter with said rotor (versions) Invention relates to production of helicopters. Rotor (3, 3') of copter (1) comprises drive shaft (10) to run about first axis (A), rotor hub (11) to run integral with drive shaft (10) about said axis (A) and several blades (12) extending from said hub (11) on opposite side from said axis (A) and along appropriate second axis (B) perpendicular to first axis (A). Every blade (12) can displace relative to hub (11) and other blades (12) about appropriate third axis (C) perpendicular to appropriate second axis (B), Said screw (3, 3') incorporates several oscillation dampers (40) for appropriate blade (12) relative to appropriate third axis (C) including appropriate first part (41) displacing integral with blade (12) about said axis (C). Damper (40) comprises appropriate second parts (42, 46a, 46b) articulated with appropriate parts (41) and functionally engaged therewith. |
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Method of constructing spacecraft Invention relates to space engineering, particularly, to configuration of spacecraft. Vessel is made with three vapour discharge openings. Main of them features centre for vessel central axis to cross it parallel with satellite lengthwise axis directed to satellite centre of gravity. Two extra openings feature centres for another vessel parallel axis to cross, parallel with satellite axis directed in its flight direction. Said vessel is arranged at maximum possible distance of the centre of gravity in direction parallel with said satellite lengthwise axis. Note here that vessel central axis parallel with satellite lengthwise axis is located at minimum departure therefrom. At a time, second central axis of said vessel perpendicular to the former is parallel with satellite axis directed in direction of its flight in orbit. Three vapour discharge openings of said vessel are connected via electric valves with reducer. |
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Rotorcraft adjustable transmission Proposed transmission comprises reduction gearbox (1), two overrunning clutches (2) at engine shafts, rotor shaft (4), propulsive engine shaft (5) and differential gear engaged by gears (3) with engine shafts. One output link (7) of differential gearbox is engaged with propulsive engine shaft (5). Another output link (8) of differential gearbox is engaged with rotor shaft (4) via high-rpm overrunning clutch (12). Carrier (9) of differential gearbox is engaged with rotor shaft (4) via low-rpm overrunning clutch (11). Every link of differential gearbox incorporates the braking device (13, 14). |
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Spacecraft onboard electrolysis unit Invention relates to spacecraft hardware, particularly to electric power plants. Proposed electrolysis unit comprises solid-polymer electrolytic cell connected to spacecraft power supply system and water supply system. The latter incorporates circulation pump, water circulation oxygen and hydrogen circuits. Each said circuit comprises appropriate chamber of electrolytic cell and gas separator composed by rotary separator. Separators are connected with DC electric drive of circulation pump. This electric drive is connected with spacecraft power supply system in series with electrolytic cell. Oxygen circuit is equipped with input water line with valve and accommodates heat exchanger connected to spacecraft thermal control system. |
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Group of inventions relates to methods and means of making spacecraft trajectory measurements using radio links. The method employs three spaced-apart measurement stations. The first measurement station operates in coherent query mode and measures relative range and velocity of the spacecraft and records the time of arrival of the response transmission of the range query from the spacecraft. The other two measurement stations operate in non-coherent non-query mode. Said stations receive a response (frequency-shifted) signal from the spacecraft generated from the query signal of the first measurement station. Based on the received signal, said two measurement stations determine the range and velocity of the spacecraft relative to said measurement stations, as well as the time of arrival of the response transmission of the query from the spacecraft. Information received from said three measurement stations is transmitted to a ballistic centre for processing. |
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Invention relates to aircraft engineering. Proposed wing tip has end plate with aerodynamic sweep of light elongation and sharp leading edge arranged at end plate end outer side. Tailing edge of extra aerofoil is aligned with rear edge of end plate while nose flap is located at leading edge of end plate under the level of tailing edge, sweep making 60-85 degrees. Leading edge sweep makes 60-85 degrees. Extra aerodynamic sweep of light elongation has extra sharp leading edge made at end plate inner side to make with leading edge outside end plate outer side the sweep of 76-87 degrees. |
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Rocket fastening at carrier support with help of pad with suction cups Invention relates to transportation of rockets by carriers. Proposed device comprises airtight surface on the sides of said support and rocket, are rarefaction system, pipelines, distribution system, pressure gage and suction cups with seal. Damping pad with suction cups is laid between two uneven mating surfaces. Chamber of suction cups are divided by flexible membrane into two chambers, each including individual channel with valve. Said valve is designed to communicate with or disconnect from preliminary or constant rarefaction pressure main line. |
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Electric generator for earth satellite Invention relates to the field of electric engineering, in particular, to devices designed to generate electric energy, and may be used to generate electric energy on aircrafts that move in space relative to power lines of Earth magnetic field. The technical result is achieved by the fact that in the proposed electric generator for an Earth satellite, the anchor of which is made in the form of a coil, half of which, comprising a half of each turn of the coil, is closed by a magnetically impermeable screen, according to the invention the generator anchor is made of two identical coils, arranged at both sides of the Earth satellite symmetrically relative to its centre of mass, at the same time windings of generator coils are connected in parallel or in series and matching. |
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Invention relates to aircraft engineering, particularly, to pylon fastener. This fastener comprises power element secured by bolt with nut via bush in mounting hole in aircraft wing. It comprises nut lock. Bush has shaped bore. Bolt head shape complies with bush shaped hole. Power element has bored to dolt and nut thrust seat at bottom. |
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Device for turboprop fan blade orientation control Turboprop comprises at least of assembly (24a) of controlled-orientation fan blades (26) fixed with rotary ring (28a) articulated with turbine rotor. Every blade of said assembly is coupled with sync ring (30a) for orientation control. Additionally, this device comprises frictionless bearing (54a) with inner cage (56a) to slide on turbine crankcase. Said cage is connected with power cylinder (38) rod (44) and with outer cage (52a) engaged with sync ring with the help of multiple connection levers (40a). Levers are coupled with power cylinder rod and articulated with sync ring so that power cylinder actuation turns said sync ring about lengthwise axis. Turboprop comprises, preferably, turbine (20) with two rotors (22a, 22b) of opposite rotation and two fan (26) blade assemblies (24a, 24b) with controlled orientation. |
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Screw without cowling with blades with variable angle of pitch for turbomachine Turbomachine comprises at least one screw with cowling with variable-pitch blades. These blades are retained by cylindrical plates fitted on spinning pins (B) fitted in radial grooves of circular rotor element and interconnected by their radially inner ends with adjusting ring. Said ring spins about turbomachine shaft (A) and reciprocates there along to drive the plates about their axes. Said adjusting ring is centred and driven about turbomachine axis at means that cannot spin bur are reciprocated along said axis by power cylinder retained by turbomachine stator. Said adjusting ring centring and guiding means comprise circular guide that features U-like cross-section. Aid guide comprises two lateral walls to confine circular flute extending outward. Adjusting ring is fitted in said flute. Bearings are arranged on both sides of adjusting ring between it and lateral walls. |
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Invention relates to aircraft engineering, namely, to lead screw drive. Drive comprises first circuit of load composed by lead screw and second circuit of load composed by solid torsion arranged in lead screw and connected therewith. Note here that at one position of the drive said solid torsion can act on lead screw to make it spin. Note that lead screw drive comprises sensor to register relative displacement between spindle and solid torsion. |
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Invention relates to aircraft brake remote control system incorporating both pedal and automatic control modes. To load pedals of aircraft wheel brake foot control station brake pedal is depressed to turn it. At pedal turn force is applied thereto by pedal spring loader under normal braking conditions (NB) owing to loader spring expansion. At further turn of the pedal under NB conditions with higher retardation characteristic via simultaneous action of expansion and compression springs. At changing from NB mode to NB mode with higher retardation characteristic load at pedal is increased in stepwise manner owing to overcoming of prestressed compression spring at initial stage of its squeezing. Spring loader comprises upper bracket, rod with bearing site, lower moving bracket arranged to slide on the rod at brake pedal turn and consists of two halves surrounding the rod, and expansion springs. The latter are connected with upper bracket by one end and with lower bracket by opposite end to slide thereon to interact via mid element with pre-contracted compression spring. Compression spring thrusts against the rod bearing site made at its free lower end. Mid element interacts with spring loader fixed part by one end and with free end of compression spring by opposite end. |
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Aircraft tail unit attachment connectors Invention relates to aircraft engineering. Connector (41, 71) for fastening of aircraft vertical tail unit is made of composite material and includes first part (43, 73) including lugs (45, 45'; 75, 75') fastening of said unit and vertical walls (47, 47'; 77, 77') for attachment of connector (41, 71) to frames (7). Two extra parts (49, 49'; 79, 79') including horizontal walls (51, 51'; 81, 81') serve for attachment of connector (41, 71) to skin (5). Connector (71) for attachment with inclined load comprises also the second pair of angular parts (90, 90') with vertical walls (93, 93') for attachment with lugs (75, 75'). Versions of proposed method describe the assembly of connectors (42, 71). |
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Procedure of auxiliary power plant maintenance (app), app assembly and app air intake Invention relates to aircraft engineering, particularly, to aircraft power plant maintenance. Proposed method comprises removal air intake channel from aircraft skin. Air intake channel is brought to skin outer side. Air intake channel can be detached from and secured to auxiliary power plant at both as-mounted position and maintenance position. In every said position, air intake channels stays as-assembled. |
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Propeller blade, propeller, aircraft and method Propeller (5) blade (20) comprises top surface (21) and bottom surface (22) extending crosswise from leading edge (23) to trailing edge (24) and, in sweep, from root section (31) to free end section (41). Blade (20) comprises root zone (30) and bulged zone (35) extending from root section (31) to free end section (41). Said bulged zone (35) comprises bulged bottom surface (22'') and top surface (21'') from leading edge (23) to trailing edge (24) to extend from root section from principal plane (P1) in direction (Z) parallel with blade pivot pin and in direction opposite the airflow direction via the blade to the point of maximum flexure and towards said principal plane (P1). |
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Aircraft compartment separation system (versions) Invention relates to aircraft engineering and can be used for compartment separation. Aircraft compartment system comprises plug-in fastener, separator with pusher (two parallel pushers) with spherical thrust element. Said thrust element comprises circular bead with inner surface shaped to conical taper. Shaper geometrical centre is located at the centre of gravity of detachable compartment while thrust element hardness is higher than that pusher part in contact therewith. |
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Space incremental velocity gauge Invention relates to a spacecraft (SC) instrumentation and can be used for high-accuracy determination of minor incremental velocity of the SC progressive motion. The gauge has a hollow spherical body (1) on the outer surface whereof electric magnets (2) are positioned. Position on the body (1) is a network of targeted photoreceivers with an inertial mass (5) contained inside the body. The mass electromagnetic suspension (5) is designed in the form of embedded electric magnets (6) interacting with the electric magnets (2). The mass position sensor (5) represents an optocoupler composed of three optocouples. The radiators in the optocouples are represented by LEDs inside the mass (5) with optic axes (27). Radiation along the said axes falls onto the said photoreceivers of the body. The LEDs are powered from a helium battery embedded into the mass (5). It is charged from currents in the electric magnets (6) windings. The device operation modes are set by the operator (10) via the software (9) control and administration unit (7). Power is supplied from the source (8). |
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Oil cooling system of main gearbox of helicopter during testing Oil system for cooling the main gearbox of a helicopter during testing includes the main gearbox (22) with a tray, containing cavities of hot and cold oil. Two vertical oil pumps (15) and (16) with electric drives, an oil aerial cooler apparatus (46) with an electric drive, two oil-oil heat exchangers (34) and (35) and an oil flow metre (19) are installed in the oil system. The system also includes pipelines with electric drives and without them, filters (20) and (30) and an oil tank (1) with the equipment for oil filling and draining. |
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Invention relates to shipbuilding and aircraft engineering, in particular to ship and air propellers where propellers are used as engines. Propulsor (propeller) contains hub, blades with inlet and outlet portions, amplitude and deviation pitch of blade outlet edge profile. Outlet portions of blades throughout their height starting from 1/2 of profile length at the hub and 1/3 of profile length at periphery are made with periodic deviations of profile angle thus forming wavy surface of outlet blade portion and wavy outlet edge relative to designed value of blade angle in each cylindrical cross-section. Amplitude and pitch of blade outlet edge profile deviations from designed height value are maximal at the hub and minimal or equal to zero at maximum blade diameter, and on each subsequent blade the start of wave at hub is displaced relative to wave start of previous blade for amount of T/z, where T is pitch of the first wave, and z is number of blades. |
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Multifunctional training complex for spacemen training for works in open space Proposed complex consists of two main parts, i.e. functional-simulator bench for pre-simulator training and complex simulator for training for works in open space. Functional-simulator bench consists of computer-aided work station of training head, computer-aided work stations of trainees, first interface with the object, second unit of digital communication, functional mock-up of space suit, observation TV cameras and first module of shared info display means. Said complex simulator for training for works in open space comprises space suit, life activities means, zero-gravity simulators and simulators of Solar system space object surface. |
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Method for cleaning from space debris Invention relates to cosmonautics and can be used for cleaning outer space form space debris (SD). On the geocentric orbit, spatial area is allocated, which area has greater resistance force (friction, electromagnetic) and density, than resistance force and density of atmosphere on this orbit, and is formed by peripheral surface of tubular body. SD particles pass through tubular body via open butt ends. The tubular body has area to mass relation required for exit from specified orbit. |
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Invention relates to aviation, more specifically to turbojet nacelle (1) comprising external structure containing ring edge (7), as well as cowl panel (9), and immovable interior structure (19) going along the line of air intake extension and having portion provided with equipment assembly. Exterior structure is made capable to move relative to interior structure between operational position where the cowl panel (9) covers the portion provided with equipment assembly, and maintenance position where the cowl panel (9) opens the portion affording access to this equipment assembly from outside. Additionally, the exterior structure is provided with at least one reinforcing beam (10) mounted with possibility to transfer forces between ring edge (7) and cowl panel (9), where the beam (10) passes in radial plane (P) of air intake from exterior structure to interior structure and contains guiding means (17) made capable to interact with mating guiding means (22, 23) of interior structure. Guiding means (17) of the beam (10) and mating guiding means (23) of interior structure are shifted relative to radial plane (P) in which the beam (10) passes. |
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Vertical take-off and landing aircraft VTOL aircraft consists of fuselage, wing, tail unit, compressor with air intake and engine. Diesel shaft is arranged aligned with aircraft lengthwise axis and engaged via step-up gearing with compressor shaft. Compressor receiver is communicated via air duct extending through fuselage and equipped with throttles with electromechanical drive with the wing leading and tailing edge air duct and tail unit leading edge air duct, said edges being equipped with slot-type nozzles. Nozzles of the wing and tail unit leading edges are directed tangentially to top skins while wing tailing edge air duct nozzle is directed in bisecant. Said throttles with electromechanical drive are connected with aircraft vertical stabilisation system built around digital processor. Compressor shaft output end can be equipped with propeller. |
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Actuation of blades of engine with open blower Propulsion engine has rotor with at least one rotary blade and drive engaged with said blade to turn it. Drive (1) comprises at least one electric power source (2, 2'), electric drive (3) to turn aforesaid blade and power supply circuit (4, 4') connecting said electric power source (2, 2') with said drive (3). Said drive incorporates extra inertial device connected with said power supply circuit (4, 4'). Said inertial device (5) is designed to convert electric power supplied from said circuit (4, 4') into mechanical energy, to store the latter and to convert it into electric power for said electric power supply circuit (4, 4'). |
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Multifunctional heavy transport helicopter of day-and-night operation includes body with power plant, common helicopter equipment, helicopter mechanisation means, operational controls. Cabin is divided by partition-wall with door into two parts - crew cockpit for two crew members in the front part of which there is panel for radioelectronic equipment installation and in the rear part - additional folding seat, and cabin for attendants. In-cabin partition wall is made as rack with structural access doors in which rack instrumentation units are placed. On-board radioelectronic equipment complex includes navigation-flight instrumentation complex, helicopter and power plant control system, complex of radiocommunication facilities, state identification facilities, switching unit, on-board defence complex, on-board meteo-radar station, land approach early warning system, on-board TV unit, on-board control system, backup devices system, five multifunctional indicators, multifunctional instrument panel, external memory unit and on-board computing system. |
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Controlled buoyancy system and its implementation Proposed system (10) comprises bearing structure with sealed hollow shell (12) including first gas and enveloped by second gas, both being easier than air. Said hollow shell is prefilled with first gas via one-way air pressure control valve to prevent first gas leaks and altitude sensor (14). Altitude transducer (17, 21, 61, 66, 67, 68) connected with said hollow shell responds to altitude signal to vary the bearing structure buoyancy. Controller (15) is connected with altitude sensor and altitude transducer to respond to altitude signal and to one altitude count signal for maintenance of bearing structure at preset altitude. |
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Modular drone (versions) and bayonet joint for coupling of modules In compliance with first version, drone is a tailless aircraft and comprises fuselage composed by nose module, central module and tail module, wing composed by left and right outer wings, ailerons, winglets, undercarriage front leg, undercarriage rear legs, engine and push propellers. In compliance with second version, this drone is a twin-boom aircraft. In compliance with both versions, fuselage modules are coupled by bayonet joint including male part, female part, plate spring, seal ring and bolts. |
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Paddle for sport rowing and canoeing Proposed paddle for sport rowing and canoeing includes shaft and palm in the form of rigid frame carrying element in the form of wings of aircraft profile. Carrying working element in the form of wings of aircraft profile is fixed transversely and at an angle to palm longitudinal axis with gap between themselves, has various surface area, slit-type gaps between the front edges of wings are greater than between rear edges. Paddle palm frame is installed crosswise the paddle palm plane, in its end portion has shape of ship keel. |
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Production of metal structures containing closed chambers with low geometrical height Prepreg layers cut out to patterns and forming solid mandrel are made from moulding mass, their shape complying with article inner cavities, Mandrels from moulding mass are made from material with high linear expansion factor and low mechanical properties and wrapped with anti-adhesion film. Prepreg blank layers are laid on prepared solid mandrels. Then, separate blanks are assembled with their forming elements into one-piece structure in the mould. Forming is performed by heating the mould with its contents. After forming, aforesaid moulding mass is destructed and removed via small-size individual holes. |
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Fuel supply system of unmanned aerial vehicle System comprises N fuel tanks built into the annular fairing. The tanks are located circumferentially symmetrically relative to the vertical axis of the vehicle. The pipeline supplying fuel to the engine connect the fuel tanks in series with each other, at that each subsequent connected tank is located oppositely or about oppositely relative to the vertical axis of the fairing, to the previous tank. The last tank is connected by the pipeline to the engine. |
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Aerodynamic structure having airfoil, with corrugated reinforcing element Airfoil (1) contains longerons (2, 4) spaced in forward and back direction and longitudinal corrugated reinforcing element (6, 7) located between longerons and designed to provide space between longerons for fuel transportation. Each reinforcing element is corrugated in longitudinal direction thus forming a number of front reinforcement ribs (9) on the front side of reinforcing element and a number of rear reinforcement ribs (8) on the back side of reinforcing element. Each reinforcing element is directly attached to one of longerons or to rear reinforcement ribs of one of adjacent reinforcing elements by means of front reinforcement ribs or to front reinforcement ribs of one of adjacent reinforcing elements by means of rear reinforcement ribs. Method of manufacturing features using airfoil reinforcing elements. |
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Main rotor of rotary-winged aircraft Main rotor of rotary-winged aircraft mounted on the propeller shaft, comprises blades, a hub with sleeves, radial rotating bearings, axial hinge shaft, an intermediate part made in the form of a tube having a collar, an opening, a lever, a torsion bar fixed by the pin through the opening in the intermediate part, and a leash of controlling the blade which is inside the propeller shaft. The axial hinge shaft is a rod of variable cross section with a longitudinal opening, connected through the radial rotating bearings with the hub. The longitudinal opening of the axial hinge shaft is made in the form cylindrical surfaces of different diameters turning into each other and eccentrically located relative to each other, interacting with the blade shank. The blade shank has a longitudinal opening of the rectangular cross-section turning into the opening with a circular cross-section, on which border there is a groove, which axis makes with the axis of rectangular cross-section of the opening in the blade shank the angle of 90°. |
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Diagnostic system and method for detection of critical condition when assembling aircraft body Diagnostic system is intended for detection of critical condition and giving positional information to operator which information relates to location of detected critical condition. The diagnostic system is capable to prevent body movement from one position to another when critical condition has been detected and to unlock such movement when error source is eliminated. |
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Device for moving power cylinder for control over turboprop fan vanes Turboprop comprises the system (24a) of fan vanes (26) with adjustable orientation rigidly coupled with spinning ring (28a). Said ring is centred relative to lengthwise axis (12) and engaged with turbine rotor. Every vane of said system is connected with timing ring (30a) centred along lengthwise axis for adjustment of vane orientation. Besides, it incorporates power cylinder (38) rigidly engaged at revolution with turbine rotor and mechanically connected with timing ring by several coupling levers (40a). Every lever is coupled with power cylinder con-rod (44) and articulated with timing ring so that power cylinder motion caused rotation of timing ring about lengthwise axis. Turboprop with dual screw comprises turbine (20) with two opposite-rotation rotors and two systems of fan vanes (26) of adjustable orientation. |
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Device for landing gear unlocking in extended position and landing gear equipped with such device Aircraft (AC) landing gear contains leg pivotally mounted on AC, capable to rotate around retraction axis. The leg can be stabilised in extended position by means of brace containing two pivotally interconnected connecting rods and can be held in aligned position by stabilising element containing two pivotally interconnected links. One of the links is pivotally connected with brace, and the second link is pivotally connected with landing gear leg or with AC. The links are held in their aligned and locked position. The landing gear contains unlocking device. The unlocking device contains rotary drive, crank lever, lever pivotally mounted on the crank lever end and comprising recess, pin, returning device pressing lever to the pin. Drive axis is parallel to pivot of stabilising element links. The crank lever is connected with rotary drive shaft. The pin is rigidly fixed to one of stabilising element links and protrudes from this link. The crank lever is made capable to be shifted from the first angular position where the pin contacts with the lever being opposite the recess when links are in aligned position, to the second angular position to which the lever comes when lever recess thrusts away the pin thus bringing the stabilising element links out of aligned position. |
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Invention relates to multiaxle chassis where one of axles is of steering type. The chassis with undercarriage consists of elongated beam with axles located on it. Each axle has a pair of wheels installed on it. One of the axles is installed on the beam rotatably. Additionally, the chassis includes means for displacement limitation which are located between rotatable axle and beam and engaging with them. Means of limitation are deformed in one direction from stable and locked position corresponding to seat position of rotatable axle. Means of limitation contain telescopic backstop butt ends of which are pivotally connected with rotatable axle and elongated beam so that stable locked position could correspond to one of the following positions: fully extended or fully retracted position of telescopic backstop. The telescopic backstop contains means of internal locking for automatic locking the backstop when it returns to stable position. The telescopic backstop can be used as steering gear. It is possible to apply different braking force to wheels installed on the rear axle in order to facilitate or implement return of rotatable axle into seat position. Lockable and drivable telescopic backstop contains rod movably inserted into cylinder and hydraulically operated by means of hole in release chamber and hole in compression chamber. The backstop also contains means of internal locking intended for locking the backstop in of the following positions: fully extended or fully retracted position. Locking means are hydraulically moved between locked and unlocked positions by means of locking and unlocking hole which function independently of hole in release chamber and hole in compression chamber. |
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Intermediate gearbox of helicopter tail transmission Driving (4) and driven (5) conical gear wheels is made integral with their shafts and installed among themselves with reversal of rotation. In the casing (1), each of gear wheels is mounted on two bearing assemblies. Area of engagement of gear wheel crown gears is located between front and rear bearing assemblies of shafts. The casing comprises front wall bent with upper part forward tilt according to position of gear wheels installed with specified angle between axes, and two covers (2, 3). In the boring of front wall lower part, roller bearing (6) of driving gear wheel (4) shaft front support is installed. In the boring at the inner side of lower cover, double-row ball bearing (10) of driving gear wheel (4) shaft rear support is installed. Inside the boring of casing in the front wall lower part, roller bearing (19) of driving gear wheel (5) shaft front support is installed. In the boring of lower cover, double-row ball bearing (22) of driven gear wheel (5) shaft rear support is installed. |
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Power supply circuit for aircraft deicing system Aircraft power supply circuit includes on-board power distribution network (17) for electric devices (5b) located in or near the aircraft engine, and power supply generator (27) integrated in the aircraft engine to supply AC power to deicing system (5a). Power supply generator is connected to electromechanical drive of thrust reverser (5c) via rectifier to supply DC power to the mentioned drive. |
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Method for stabilisation of in-flight fuelling unit taper gage Invention relates to controlled in-flight aircraft fuelling units. When taper is stabilised in its three perpendicular axes of symmetry the jets are blown out the intensity of which is set as linear function of speed and taper displacement in corresponding direction. To determine these parameters accelerometers in two mutually perpendicular planes and microprocessor are installed. The microprocessor calculates from measured by accelerometers accelerations the time-dependent taper speed and displacement from which it determines reactive forces of jets in two mutually perpendicular planes, which forces are needed to correct taper position. According to values of these forces the microprocessor gives signal to change jet parameters. |
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Device of fixing in fold position of wing panels of unmanned aerial vehicle Device of fixing in the fold position of wing panels of unmanned aerial vehicle comprises a housing, in which in the deformed state the compression spring is mounted, which axis is parallel to the median plane of the wing panel, the fixing unit in contact with the spring and mounted with the ability to move along the axis in the folded position of the wing panels. The structure of the fixing unit comprises two pressure rollers, each of which enters in the recess on the ending of the wing panel. The fixing unit enables to provide fixation of two wing panels at the same time in the folded position. |
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Method of providing spacecraft flight management Information and computer complex of the control centre is integrated by rebroadcast and communication with communication means in structurally selected segment, communication channel is organised with complex of external information exchanges on a single structurally selected segment the simultaneous execution of program procedures is planned, initiated and implemented, receiving and processing of applications of consumers is carried out for providing services of rebroadcast and communication over all types of information, exchange over a local computer net is carried out with all kinds of flight information on controlled spacecrafts, by the external subscribers through the complex of external information exchanges the spacecraft motion is predicted relative to satellites-rebroadcasting transmitters produce, route selection of information rebroadcast is carried out, bringing messages to consumers on provision of rebroadcast services and connections is carried out, the programs of spacecraft flight management programs are formed, provision of programs of management to spacecrafts is implemented. |
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System of visual aircraft (ac) landing System of visual aircraft landing consists of two glide path laser emitters, the course and two side laser emitters, the laser subsystem of visual indication of the axis of runway, the subsystem of initial runway threshold, the subsystem of final runway threshold, and the subsystem of end part of the side runway outline. |
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Spacecraft fuel tank for liquid components storing and delivery Invention relates to pneumohydraulic system for fuel components delivery to jet propulsion system of aircraft. The fuel tank includes pressurised body made of two semispheres with input and output nozzles and external mounting elements. Metal diaphragm is placed inside the body and connected with them along perimeter. Its thickness is maximal in equatorial part and gradually decreases towards polar part. In this system, the diaphragm in its equatorial part (6) is made in the form of truncated cone, in its middle part (7) - in the form of toroidal surface, and in the polar part (8) - in the form of spherical surface segment. The final (after re-laying) position of the diaphragm is shown on the drawing by dotted line. |
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Stationary device of turboprop fan vane pitch controller actuator Invention relates to turboprops. Proposed engine comprises at least one set of variable-pitch fan vanes (26) driven by rotary ring (28b) centred along lengthwise axis (12) and mechanically connected with turbine rotor. Every vane of said set is connected to timing ring (30) for pitch adjustment purposes. Besides, this device comprises extra disc (44) fitted via rotary joint to link of actuator (38) secured to fixed structural element of turboprop. Said disc (44) is mechanically connected to timing ring via multiple connection levers (46) articulated with said disc and connected with timing ring so that disc lengthwise displacement forced by the drive makes timing ring turn about lengthwise axis. |
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Method for producing hollow structures with inner walls Method for manufacturing hollow structures with inner walls includes manufacturing of workpiece by laying the prepreg layers of the upper and lower casings, cut by patterns, and frame forming, laying of workpiece into the mould, consisting of individual shaping parts, previous moulding of lined workpieces, extrusion by means of mandrels and sealed flexible bags placed inside the workpiece, and their removal from the item after extrusion. Laying of upper and lower construction panels is performed at the respective design formative parts of the mould, laying of inner walls and their preliminary moulding is carried out on the combined mandrel. Combined mandrel comprises rigid base and flexible edges. Individual workpieces with their shape-generating elements of equipment are collected into the integral design workpiece. |
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Invention relates to aerodynamics of rotation bodies. Axisymmetric rotation body (ARB) (shell shape) with ogival or sharp-pointed nose contains additional airfoil (AF) (fixed, all-movable, rotary with different rotation axes, slotted, all-extendible, adaptive) in calibre, sub-calibre, over-calibre position. Between ARB and AF, two confusors are created with two channels distributed along ring of confusor, after contactor, closed ring diffuser and closed ring channel with constant in length cross-section are formed. |
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Method of electric checks for spacecrafts Invention refers to land checks of spacecrafts and preparation for routine operation. Method involves spacecraft (SC) switching on and off, including electric power sources, particularly accumulator batteries (AB). Before SC actuation, stabilised land power sources are connected to AB, and after SC deactivation, current of AB boost charge from those sources is monitored additionally. That current is indicative of routine completion of SC deactivation process. In addition, boost charge current is used to assess AB loss current with SC switched off, that should not exceed a set value. |
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Air intake power unit device of hypersonic aircraft In the air intake power unit device of the hypersonic aircraft, comprising a stepped horizontal wedge of braking, an external shell and an internal partition forming two flow paths, one of the flow paths - centre - is composed of two channels of rectangular cross-section, formed by two stepped horizontal wedges of braking, two outer flat shells and two internal partitions, which are simultaneously the inner walls of two side channels of semi-circular cross-section of other flow path formed by two stepped cones of braking and two outer semi-circular shells. |
Another patent 2513902.
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