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Direction indicator (versions) Invention relates to navigation equipment. Direction indicator consists of a vertical rod or plate or that located in vertical plane fitted in guides by spring or thread ahead of a man to pass through direction demand line. Dial is arranged nearby the guide and has scale marks of side wind or several marks for various flight speed. Said rod has a bulged located so that at aircraft roll said bulge stays always in one vertical plane relative to earth. Besides, tape can be arranged opposite direction demand line with its plane passing through noncommand line. |
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Method of aircraft control and device to this end Method of control over aircraft with two and more engines consists in differential feed of fuel. Fuel feed is performed by main fuel pumps and extra fuel system driven by actuating spring of one of the main engines or by motor and electric or air operated stabilisation control system. Proposed device consists of differential fuel feed system, direction and/or pitch control stabilisation system and set of gyroscope transmitters. |
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Method of aircraft trajectory control in flights over zones with unfavorable weather Invention relates to aircraft engineering, particularly, to aircraft trajectory control. Method of automating the correction of aircraft flight path in preset route in buzzing over dangerous zones (those with bad weather) comprises approximation of dangerous zone by circumference. Corrected course of aircraft is generated as corrected course magnitude calculated on the basis of common methods of guidance. Parameters are defined either at dispatcher (command) station or aboard the aircraft. Aircraft course correction is started when distance from guided aircraft to dangerous zone center is smaller than definite magnitude. |
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Staroverov's aircraft (versions) Invention relates to aircraft engineering. In compliance with the first version, aircraft comprises fuselage, wing, empennage and engine/engines. Said engine is directed forward-upward relative to aircraft lengthwise axis, or engine thrust source is directed forward-upward relative to aircraft lengthwise axis with due allowance for aircraft aerodynamics. In compliance with the first version, aircraft comprises fuselage, wing, empennage, electric remote control system and engine/engines. Amplifier receives signal from the rudder position selector or that pitch selector and that of engine thrust transducers or that from engine control lever position to vary its gain, or this signal is fed as-scaled to amplifier input. |
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Stepped rotary device consists of a housing with rotary elements rotating in it. Rotary ball elements form independent rotary steps. Rotary steps simplify the device start-up considering their interaction and increase maximum number of the shaft revolutions. Stepped rotary device can be used not only as an engine with a big number of revolutions, but also as airborne and submersible vehicles, without changing major structural members of the device, at reduction of metal consumption of the item. In external housing and in internal members of rotary steps there can be arranged different loads, fuels and lubricants, people, as well as they can be used as receivers for exit gases. Steps with parameters necessary for obtaining external shapes of the device with improved aerodynamic characteristics are created by changing the diameter of balls and number of parallel chambers, by means of configuration of cover of external housing. As per the second version, stepped rotary device includes working chambers and exit gas outlet chambers interconnected between themselves via channels and known devices. Exit gas provides reactive motion through nozzles and changes its direction in space. Helicopter rotors can be mounted on the shaft of the stepped rotary device. Jet engines can be arranged inside external housing. |
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Airborne vehicle of "flying saucer" type Invention relates to VTOL aircraft. The airborne vehicle contains frame of axially symmetric shape, fuel tank, instrument compartment, gas-turbine engine including compressor, combustion chamber, turbine, adjustable guide vein including nozzle blades installed with possibility to be rotated, and jet nozzle. Gas-turbine engine is installed along vertical axis of frame. Combustion chamber is made multisectional with fuel systems including fuel governors for each section. Each nozzle blade is equipped with drive. Number of nozzle blades is equal to number of combustion chamber sections. Nozzle blades are fitted between sections of combustion chamber. Compressor is made centrifugal with axial inlet and axial outlet. Fuel tank is installed inside the gas-turbine engine. Emergency landing engine is installed inside the jet nozzle. |
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Flight vehicle (versions), flight vehicles parts, method of exploiting flight vehicle and its parts Invention relates to aircraft engineering. Proposed flight vehicle comprises power plant, fuselage and wing fragments. Set of wing fragments comprises bearing and control surfaces and their mounts. Wing fragment includes structural set including spar, stringer and ribs. Fuselage includes set of frames, spars, stringers and skin. Frames and spars have opening to fasten wing fragments. Engine reversing device comprises flap pivoted in housing to close its openings and provided with grids composed of gas flow guide vanes. Air intake with jet engine integrated in fuselage tail features variable-depth grooves arranged opposite each other on supports. Control system comprises control rod with pedals at its bottom and handle at its top. Said handle has landing gear extension/retraction knob and that of electric drive of bottom set of fragments. Methods of flight vehicle control comprise exploiting air and gas flows. |
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Manoeuvrable aircraft with gas-dynamic control system Invention relates to aircraft engineering. Manoeuvrable aircraft contains fuselage, wing, two turbojet engines and gas-dynamic control system which contains gas passage with one pair of nozzles for creation of gas streams in one plane and another pair of nozzles for creation of gas streams in another transversal plane, rotary drive installed on aft body to rotate central gas passage relative to longitudinal axis of fuselage. Fuselage aft portion forms intermediate gas passage with ring base where central gas passage is installed being possible to rotate. Each turbojet engine has gas passage between turbine and nozzle. Gas passages of turbojet engines are provided with corresponding flaps placed symmetrical relative to longitudinal axis of fuselage with possibility to bleed part of gas after corresponding turbine through intermediate gas passage of gas-dynamic control system. |
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Invention relates to aircraft engineering and aims at protecting jet engine against ingress of birds in flight. Proposed engine comprises two parts with common housing (22). One of said parts is engine made up of fan (1), low-pressure compressor (2), high-pressure compressor (3), combustion chamber (4), high-pressure turbine (5), low-pressure turbine (6), nozzle (7), compressor and high-pressure turbine shaft (8) and compressor and low-pressure turbine shaft (9). Protected engine incorporates second part, making four-stage electric trap arranged ahead of engine and made up of tubular electrodes with branches (10-13) located one after another along compressor rotational axis and dielectric isolators attaching said electrodes to engine housing. Note that potential difference of 100000 V is generated between housing (22) and electrodes (10-13). |
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Method of descending space rocket stage separation part and device to this end Invention relates to space engineering, particularly, to liquid propellant rockets. Proposed method consists in stabilising discarded part in engine-forward position, orienting it and controlling its descent. Said separated from the rocket, maneuver is performed by power of gasified residual liquid fuel components fed into descent rocket gas engine plant. Control over motion of center of mass and around it is carried out by deflecting chambers of gas jet engine plant. Angular position of separation part in space, on cutting in gas jet engine, is set corresponding to minimum angle of attack on re-entry, and separation part is spinned about its lengthwise axis. Proposed separation part comprises control and navigation system, and gasification system. Fuel compartment bottom accommodates four chambers, each being provided with drive. Gasification system incorporates self-contained gas generator with membrane system to feed fuel components, acoustic vibration exciters arranged on unions feeding fuel in fuel tanks. |
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Method of creating aircraft lift or thrust Invention relates to aircraft engineering. Proposed method is intended for VTOL aircraft with annular hollow wing. Central part of said wing has radially slotted nozzle to create airflow generated to form two low-pressure zones nearby top and bottom inner spaces of the wing with possibility to control rarefaction by means of valves. Air is forced into wing central space separated by winglets on both walls to produce equal segments. Air is forced through radially slotted nozzle, with cross section features shape of cone or Laval nozzle. Every segment, above and/or below the wing, has slots running into segments to be shut off by valves. Thrust direction and force are adjusted by opening/closing the valves and controlling flow speed when flowing through radially slotted nozzle. |
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Set of invention relates to aircraft engineering. Proposed method consists in using lifting-bearing turbofans with gas drive from turbojet engines, while horizontal flight is performed by turbojet or piston engines with longitudinal thrust vector with respect to aircraft. Aircraft flight is controlled by elevation and vertical rudders. High-speed aircraft-turbocraft comprises airframe, turbojet engines, lifting-bearing turbofans with gas drive from turbojet engines arranged along aircraft sides or above airframe. High-speed increased load-lifting capacity aircraft comprises combined flight complex consisting of aerodynamic control surface, lifting-bearing variable thrust vector turbofans, turbojet or piston engines, and has-jet rudders. Turbofan engines can be used as gas generators. |
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Method to determine aircraft (or its mock-up) angular position in space Invention relates to aerodynamic tests. Proposed method comprises constructing reference system of Cartesian coordinates, mounting two horizontal measuring post on axes OX and OY at equal distance from origin of coordinates and third measuring post is aligned with vertical axis OZ. Laser radiation source is mounted on aircraft (or its mock-up) is mounted, source optical axis laying in parallel with the plane tangent to aircraft (or its mock-up) surface, or laser beam scanning being parallel with said plane. Aircraft (or its mock-up) is mounted at the point located on its surface to allow its center of mass to move along three degrees of freedom, laser beam, or its scanning, marks coordinates being registered on measuring posts while aircraft angular position is defined from magnitudes of angles (α, β, γ). |
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Method to control twin-engine aircraft and system to this end In control of twin-engine aircraft, control signals are sent from pilot stick to aerodynamic control surfaces and gas dynamic elements representing adjustable nozzles that allow thrust vector deflection. Control signals come along two circuits: aerodynamic control surfaces remote control circuit and thrust vector deflection circuit, and are fed to computing system divided into to operating computing subsystems: primary and auxiliary. The latter is actuated at low flight speeds and large angles of attack. Control system comprises digital computing system consisting of four stand alone units: two operating computing subsystems, primary and auxiliary, altitude-speed parametre computing unit and gas-dynamic parametre computing unit communicated via digital flight data exchange communication channels. |
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Variable-thrust vector aircraft Variable-thrust vector aircraft comprises fuselage, wing and gas turbine power plant comprising turbojet engine with adjustable jet nozzle that features variable thrust vector and is arranged at fuselage tail. Aforesaid nozzle consists of base, two flaps furnished with guide vanes arranged to vary gas flow direction, drive that rotates the base relative to jet nozzle and lever-and-slide mechanism designed to turn aforesaid flaps relative to base. |
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Method for anti-spin control of airplane and system for its realisation System of anti-spin control of airplane includes unit of airplane attack current angles detection, unit for setting of critical attack angles of airplane, unit for comparison of current attack angles with critical values, and also facilities for generation of control action. System is equipped with pulse jet engines fixed on airplane fuselage. Facilities include unit for detection of aerodynamic and damping accelerations, unit for detection of values of main and correction force pulses in transverse direction of airplane motion, shaper of signal for connection of pulse jet engines and actuating mechanisms of pulse jet engines. Method for control of airplane is characterised by application of anti-spin control system. |
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Invention is related to aerospace equipment, namely, to design of aircraft bearing unit. Bearing unit of aircraft (1st version) includes jet or hybrid jet-rocket engine equipped with slotted nozzle, wing located behind slotted nozzle in zone of gas flow action that washes wing panels and suspended on engine body by means of horizontal hinged joints with the possibility to vary angle of wing attack relative to direction of gas flow, to create controlled lifting force of bearing unit. Aircraft bearing unit (2nd version) includes hybrid engine and wing, at that engine is equipped with four opposite slotted nozzles and is installed inside annular wing split into four segments, with the possibility to vary angle of segments attack relative to direction of gas flow to create lifting force that transports apparatus only in vertical direction. Bearing unit is equipped with two supply systems that provide for engine operation on kerosene and oxygen, and also on rocket fuel with oxidant for flight in airless space. |
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Set of invention relates to aeronautical engineering. The methods of creating lift, taking off, flying and landing feature separation of air flow designed to produce opposite parts of jet thrust of blowing over the carrier surfaces. The aircraft comprises fuselage, power plant, air flow intake assembly and wing leading-edge air flow distributor. Fuselage includes the system of lines feeding air flow from the turbojet engine compressor to the aforesaid wing leading-edge air flow distributor. The wing comprises leading-edge air flow distributor. In compliance with the other version the wing outer surface has slots communicating, via appropriate ducts, with the air intake slows. The methods of flight control, taking off, flying and landing comprise using the system of control of aerostatic lift. The aircraft control system comprises a subsystem designed to control aerodynamic lift and that to control aerostatic lift. Thrust reverse incorporates the system controlling flaps and grids intended for separation the jet thrust into parts. The thrust reverse operating technique features using the aforesaid system of controlling flaps and grids. Three-leg landing gear comprises low-pressure tires. Gas separation and distribution system comprises pipelines communicating with the air intake receiver. |
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Aeroplane with jet wings incorporates a fuselage, three pairs of half-wings, two jet engines suspended on pylons at the fuselage rear, vertical and horizontal tailplanes with elevators and rudders, landing gear and control mechanisms. Identical design half-wings are attached at the fuselage sides. Every half-wing represents a rectangular box with lengthwise and crosswise webs dividing the half-wing inner space into separate isolated air ducts each incorporating an air intake, rotary part and vertical outlet channel. The half-wing upper part is inclined backwards towards the tail so that the rectangular box front edge forms with the vertical plane an angle of 45 degrees. The half-wing upper part accommodates horizontal tailplanes. The central tailplanes are furnished with ailerons. |
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Special design body of forced flow-air jet engine Invention relates to special design body of forced flow-air jet engine which has section made square to install rotary shutters on hinge joints with long rods. Section of reaction nozzle is also made square, and rotary plates are installed in nozzle at different levels in horizontal plane to cut off thrust at takeoff and landing of aircraft through air duct for forming air cushion under lower plane of flat fuselage and, in process of landing, to direct vector of thrust opposite to direction of flight for deceleration. |
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Aircraft of simplified arrangement Proposed aircraft has fuselage, pilot's cabin in nose section and turbo-jet engines. Fuselage has rounded-off top and hull-type bottom with landing units on shock-absorber struts and hatches. Turbo-jet engines are provided with controllable nozzle for change of angle of inclination of gas jet; they are mounted on pylons on sides of fuselage; pylons are mounted above longitudinal axis of fuselage and on surface of its tail section. Piloting and maneuvering of aircraft are performed through change of angle of inclination of nozzle of turbo-jet engines and their thrust. Fuselage may be provided with passenger saloon and cargo compartment. Tail section of flying vehicle fuselage is provided with hatches and mechanisms for pan-caking of detachable fuel tanks or cargoes under adverse conditions of flight. |
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Proposed flying vehicle includes one or more inflatable members 1 fastened together and gas supply unit 6 whose outlet is connected with nozzles 3. Even one of nozzles is formed by external surfaces of inflatable members or envelopes embracing the sets of inflatable members ; it is narrowing in way from inlet to outlet or it may be made in form of combination of narrowing part and widening part. |
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Aerospace complex, aircraft and multi-stage rocket and method of launching spacecraft Rocket has first stage with first thrust forming unit and device for control of this first unit during motion over trajectory; rocket has also second stage with thrust forming unit, device for securing the first stage to aircraft and for separating it from aircraft during flight and spacecraft. Thrust forming unit of first stage makes it possible to control thrust vector at limitation of velocity head. Thrust forming unit of second stage ensures terminal control of thrust pulse for minimum deviation from preset trajectory at moment of engine shut-down. Thrust forming unit of first stage is made in form of solid propellant rocket engine provided with nozzle and drive for deflecting the nozzle for control of thrust vector. Aircraft is designed for launching the rocket with spacecraft in flight. Proposed aerospace complex is used for launching the rocket in payload trajectory; this complex has rocket, aircraft and device for securing the first stage of rocket to aircraft and for separating of rocket from aircraft in flight. Proposed method consists in launching the rocket with spacecraft in ascending module in trajectory at control of thrust vector. |
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Guidance-navigation system for multipurpose aircraft System comprises onboard channel of information exchange that is connected with the inputs-outputs of the indicative information-control system for the pilot, indication information-control system of operator, complex of navigation-piloting means, complex of sighting means, system for control of means of air opposition, and onboard computing system. |
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Proposed unit is provided with vertical accelerator for flow of air admitted upward; this accelerator consists of two convergent nozzles located on one axis and tightly interconnected. Each nozzle is rigidly (or for axial motion) is introduced into other nozzle in way of air motion, thus forming cavities between nozzles where intake valves and air energy exciting units are mounted on its wall. Pressure sensors are mounted in all cavities. Air flow escaping from accelerator is branched-off in upper part of casing and is directed to outlet vertical nozzles located at angle of 180° relative to vertical and to horizontal nozzles via air ducts. Provision is made for sensors showing rate of motion of device in three directions and sensors showing velocity of flow at outlets of all nozzles. Device is also provided with actuating mechanisms of door drives in air ducts and control unit. |
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Sighting-navigating complex for multipurpose aircraft Complex comprises set of multipurpose indicators whose inputs and outputs are interconnected through the information channel, indicator mounted on the windscreen, TV camera, members for operative control, assembly of view-sighting means, assembly of flight-navigation means, portable storage for initial data, system for control of means of counteraction, and computing system. The computing system comprises computing-logical units of combined data base which are interconnected by their inputs and outputs via the bus of information exchange, unit for generating flight-navigation parameters, generating sighting-navigation parameters, generating displayed information, and input-output and control of information exchange. |
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Sighting navigational complex for multi-mission aircraft Proposed complex includes set of multi-functional indicators interconnected by inputs and outputs in information exchange channel, windshield indicator, outside-cabin observation TV camera, on-line control elements, set of observation and sighting means, set of navigational and pilotage means, portable initial data carrier, counter-measure control system and computer system. Computer system includes logic elements of combined data base interconnected by inputs and outputs in computer information exchange line, elements of forming navigational and pilotage parameters, sighting and pilotage parameters, forming displayed information, input, output and control of information exchange, synthesizing parameters of motion relative to air medium, synthesizing target designation parameters, control of combat situation and training situations. |
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Mode of landing of an aircraft on the deck of an aircraft carrying ship The mode of landing of an aircraft on the deck of an aircraft carrying ship is in that aircraft's altitude and flight speed are reduced without leveling of the trajectory. At the moment of contacting of an aircraft with the deck the engine is put on the maximum power setting. The aircraft is hooked with arresting cable of the aerofinisher. At flying up to the ship the mode of controlling of the rotatable nozzle is switch on. The nozzle is deflected upward towards the angle in an interval of 5-14° at the moment of contacting of the aircraft with the deck. The nozzle is put in neutral position after braking of the aircraft. If the aircraft is not hooked with the arresting cable of the aerofinisher the nozzle is left deflected upward for making of an angle of attack at the aircraft's taking off. |
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Method of preparation of aircraft for takeoff from flying-off apron of aircraft carrier Proposed method includes arresting the aircraft on flying-off apron, mounting the gas-deflecting shield at angle of 50-70° relative to surface of deck, attaining the "maximum boost" mode of engine, checking the aircraft readiness for takeoff, transmitting the information on readiness to fly off and releasing the lock. If aircraft is equipped with engines provided with swivel nozzle, swivel nozzle control mode shall be switched-on after arresting the aircraft. Then, nozzle is deflected upward through angle of 14-18° which is maintained for 0.7-1 s at "maximum boost" mode and is reduced to 6-9° in 6-10 s and is kept in this position for 6-8 s. At the moment of releasing the lock, nozzle is returned to neutral position. Gas jet of engine is reflected from gas deflecting shield due to reduction of reverse flow of gases sucked by air intake. |
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Military transport aircraft (btc+5) Proposed aircraft has fuselage, wing jet engines or turbo-jet engines mounted for turn relative to horizontal and/or vertical plane. Wing has variable area. Upper and lower surfaces of wing may be wound on/off individual drums. Tail-mounted engines may be provided which are set in horizontal plane at angle relative to aircraft longitudinal axis at similar signs. |
Another patent 2513619.