Nozzle of gas-jet helicopter control system

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering and can be used for helicopters with jet control system. Control mechanism of flaps of tricuspid nozzle with controlled thrust vector consists of toothed sector of middle flap position control, side flaps control levers, central rocker, engaged by rods with levers of side flaps. Central rocker is engaged with toothed sector of middle flap, wherein gear ratio from middle flap to central rocker is 0.70–0.78. Arms of central rocker have length of 0.3–0.4 width of nozzle inlet section and opening angle of arms 140–150°. Levers of side flaps have arms of length of 0.3–0.35 and 0.4–0.45 of nozzle inlet cross-section width and angle of inclination 50°–55° and 55°–60° respectively, and thrusts of levers of side flaps are 0.5–0.55 and 0.4–0.45 of nozzle inlet cross-section width.

EFFECT: reduced pressure losses in nozzle and improved its efficiency, providing required for each flight mode ratio of side and propulsion forces.

1 cl, 7 dwg

 



 

Same patents:

FIELD: transport.

SUBSTANCE: helicopter comprises tail section (1) with crosswise duct (6) and drive shaft (23) inside driven shaft cowl (14) to counteract the torque. Device (2) comprises rotor and stator shifted in rotor axis, drive shaft (23) and control rod (24) to control the pitch of blades (13). Rotor comprises sleeve (12) and vanes (13). Rotor vanes (13) feature modulated angular distribution around said rotor axis. Stator comprises multiple vanes (16, 17). Said vanes (16, 17) are modulated in angle to limit the interference between rotor vanes (13) and stator vanes (16, 17). This is ensured by making whatever angular difference between two rotor vanes (13) comply with whatever angular difference between two stator vanes (16, 17) or whatever stator vane and drive shaft cowl (14). Rotor runs about axis inclined through -20° to +45° from axis (18) shifted in parallel relative to helicopter or drive shaft lengthwise axis. Maximized spacing for any points (21) on trailing edges (30) of stator vanes (16, 17) is defined by the width of case (3), that is, confined inside the contour composed by said case (3).

EFFECT: decreased noise.

15 cl, 6 dwg

FIELD: aircraft engineering.

SUBSTANCE: this antitorque rotor has shaped leading part, cylindrical part and trailing part. It consists of stator accommodating reduction gear with input and output shafts whereat the hub with vanes secured thereto is mounted. Fixed directing vanes are fitted inclined to the surface of encasement and are secured by one end to encasement cylindrical part and by other end at stator. Antitorque rotor comprises twelve blades arranged in two lines. Second line of blades is located in encasement cylindrical part. Spacing between said lines makes 0.08-0.20 of rotor radius. Note here that angular distances between two adjacent blades in common sequence for two lines of blades in each of three consecutive pairs of blades are related as 3:5:7. Note also that the number of blades in every line is even and that said blades are located diametrically opposite. Supports of directing vanes at encasement cylindrical surface are arranged in symmetry relative to input shaft axis. Attachment of every blade to stator is shifted relative to this blade to encasement surface in clockwise direction on the side of shaped inlet part of said encasement.

EFFECT: decreased acoustic radiation of rotor at minimum vibration, better aerodynamics.

4 dwg

FIELD: aircraft engineering.

SUBSTANCE: proposed method consists in application of exhaust jet of gas turbine engines. Said jet is directed to tail boom and amplified in compliance with Bernoulli effect thanks to air intake openings made at boom base. Then, at flowing through tail boom said gas flow is directed towards all-moving keel arranged at boom end.

EFFECT: higher reliability of control over helicopter.

2 dwg

FIELD: aircraft engineering.

SUBSTANCE: anti-torque-rotor 12 has drive 1 including electrical machine with crosswise magnetic flux excited by permanent magnets with duplex configuration of stators. Disc-type rotor 5 is arranged between two stators 2, each being provided with the system 8 of circular windings. Said rotor has permanent magnets 15 while blades 14 of rotor 12 are arranged at rotor outer surface. Every said system 8 of circular windings is arranged concentrically about shaft 17 of rotor 12 so that circular windings of said system 8 are arranged radially relative to said shaft and one above the other. Rotor rests via radial bearing on shaft 17. Permanent magnets 15 are laminar. Said system 8 of circular windings is oil cooled. Note here that said system 8 of circular windings of every stator 4 is immersed in oil bath.

EFFECT: simplified design, decreased weight.

12 cl, 2 dwg

FIELD: transport.

SUBSTANCE: proposed helicopter has one-side wedge-like nose cone. Said nose cone is formed by one-side skewed side airframe panel to counteract helicopter turn in forward flight.

EFFECT: reduced power consumption of rotor drive.

1 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering and can be used in helicopter contrarotation devices. Proposed device comprises circular cylinder filled with heavy fluid and arranged below rotor and aligned with it. Said cylinder incorporates hydraulic propulsor to force fluid through it and to create reactive moment of contrarotation.

EFFECT: higher stability and maneuverability.

FIELD: aircraft engineering.

SUBSTANCE: invention relates aircraft engineering, particularly to system of rotors drive system. Proposed system comprises the system of rotors, main reduction gearbox to drive said rotors, overrunning clutch and system of forward thrust. Note here that said forward thrust system is driven by the main reduction gearbox, while overrunning clutch is thrown into mesh with the latter so that torque developed by the system of rotors in autorotation is absorbed by the forward thrust system during high-speed flight when rotor autorotates, thus, bringing about rotor lift.

EFFECT: improved control over RPM developed by rotor system and reduced vibration.

14 cl, 5 dwg

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering. Proposed helicopter comprises fuselage and rotor. Fuselage has skewed contrarotation aerodynamic surfaces (1, 2) arranged in nose and tail fuselage parts.

EFFECT: reduced overall dimensions.

3 dwg

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering, particularly, to helicopters with one lift rotor. The proposed short helicopter comprises a lift rotor and lift rotor reactive moment compensation mechanism. The disk of lift rotor rotation is crossed by compensating rotor/rotors rotation disk/disks. The gear ratio between the disks, representing the lift rotor RPM-to-compensating rotor RPM ratio satisfies ratio that follows, i.e. where, A is the gear ratio, N is the number of blades of lift rotor, n is the number of blades of the compensating rotor/rotors, C is an integer. The tail rotor rotation disk can be located at an angle to the helicopter a longitudinal vertical plane. The helicopter can have more than two compensating rotors on each side.

EFFECT: shortened helicopter tail boom.

7 cl, 7 dwg

FIELD: structural members helicopter; devices for compensation of reactive torque of main rotor.

SUBSTANCE: proposed device has two longitudinal fences; one of them is mounted on external side of board of tail boom on side of retreating blade and is located above second longitudinal fence mounted on external side of board of tail boom on side of advancing blade; longitudinal fence located on side of retreating blade is mounted in lower quarter part of tail boom cross-section at angle 90-140° from upper point of tail boom cross section; height of this fence is no less than 10% of maximum width of tail boom cross section and longitudinal fence located on side of advancing blade is mounted in lower quarter of tail boom cross section at angle of 0-50° from lower point of tail boom cross section. Position of upper fence on side of retreating blade together with proposed height of this fence imparts additionally functions of deflector which considerable changes direction of vertical layer of inductive flow of main rotor above trail boom from practically vertical to direction dictated by plane of position of structural depth of fence. Super-circulation flow around boom thus formed gives rise to additional force directed towards part of main rotor disk with advancing blade. Second fence ensures drawing down point of boundary layer separation and simultaneously separates increased pressure zone arising under action of first fence from negative pressure zone, thus ensuring rise of pressure on tail boom surface on side of retreating blade and increasing on first boom arising under action of first fence.

EFFECT: increased lateral force on tail boom and creating of compensation part of reactive torque at hovering and low speeds.

7 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft control systems. Proposed method relates to control over aircraft (1) with airfoil spinning at high rpm. Said aircraft comprises fuselage (2) at least one rotor (3), at least one pull variable pitch propeller (4) and at least two half-wings (11, 11′) located on both sides of fuselage (2). Besides, it includes, at least one horizontal tail (20) provided with moving surface (21, 21′) and at least one power plant (2) to drive said rotor (3) and every pull propeller (4). Proposed method comprises determination of total lift of aircraft, adjustment of lift of every half-wing (11, 11') by acting at the drive of flaps (12) so that said lift equal the first preset percentage of total lift. Note here that difference in lift between half-wings (11, 11′) allows to compensate for rotor (3) influence on said half-wings.

EFFECT: automatic stabilisation of hybrid copper position.

18 cl, 6 dwg

FIELD: transport.

SUBSTANCE: invention relates to aerostatics. Control over airship including airframe, tail unit, nacelle with payload and onboard systems and differs in that airship required stability and controllability at takeoff, flight and landing result from application of gyro rotor with controlled vector of the full aerodynamic force. Gyro rotor (1) can incline relative to lengthwise and crosswise directions with separate sustainer power plants that perform their traction functions irrespective gyro rotor.

EFFECT: simplified control.

1 dwg

FIELD: transport.

SUBSTANCE: invention relates to development of lift in air. Development of lift for displacement of cargo in air comprises arrangement of two main discs of carrier two sides for vertical turn thereabout. Spiral-like sets of unidirectional ribs are arranged above every said disc to develop decreased pressure by spinning of extra disc. There is the hole to locate and fix the drive at turning device for spinning of extra disc. Stiffness plate is secured at turning device and aligned with main disc. Gearing is fixed at said plate to engage with drive reduction gear, as well as several pairs of limiting rollers. Internal U-like stiffness rib is arranged between limiting rollers of every pair and feature toothed surface of the wheel for motion of the ground. Gearing is engaged with toothed surface of U-like stiffness rib of said wheel.

EFFECT: decreased overall dimensions.

9 dwg

FIELD: transport.

SUBSTANCE: invention relates to vehicles for moving in air and over road surface. Method of lifting force generation for cargo lifting and transfer in air includes using two main disks at two sides of transport body with possibility of vertical turn by means of turning mechanism. Over the main disks, helical sequences of ribs of one orientation are placed to create decreased pressure above their surfaces by rotating them by means of additional disk of drive which is made with gearset. Turning mechanism is made with linear drive and with two parallel cylindrical guides functionally associated with bushings of longitudinal movement which are mounted on diametrically opposite sides of limit washer and connected with linear drive. On the limit washer, several pairs of limit rollers are rotatably fixed. Between rollers of each pair, internal flat-topped reinforcement rib with scalloped surface of land moving wheel is installed which surface is linked with drive gearset.

EFFECT: minimisation of overall dimensions.

3 cl, 6 dwg

FIELD: transport.

SUBSTANCE: version of every hybrid aircraft consists of fuselage, turboprop and wings. First version incorporates bearing devices arranged on both sides of fuselage and consisting of aircraft transverse wing root with engine fan ahead of front edge at fuselage nose and wings arranged there behind, several wings at top or bottom side, along fuselage. Second version incorporates top and bottom pairs of cantilever straight wings with spacing between pairs for gas-air flow from engine nozzles. Turboprop et engine incorporates shaped confuser and diffuser sections of propfan ring inner surface. Wing versions feature availability of bearing section and airfoil section. Methods comprises using said aircraft and engine.

EFFECT: higher safety, lower costs.

13 cl, 8 dwg

FIELD: aeronautical engineering.

SUBSTANCE: 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.

EFFECT: reduced dependence of flight upon weather conditions.

43 cl, 27 dwg

FIELD: aeronautical engineering.

SUBSTANCE: proposed device includes main inflatable envelopes and at least one additional inflatable envelope; each inflatable envelope is provided with unit for adjustable formation of gas, container with units for securing on object to be rescued, parachute or system of parachutes and system for control of pressure inside main inflatable envelopes. Parachute or system of parachutes is connected with main inflatable envelopes which are located over perimeter of parachute gore and are connected with it by means of flexible couplings.

EFFECT: enhanced reliability and accuracy of landing.

10 cl, 8 dwg

Helicopter // 2246426

FIELD: aviation; single-rotor helicopters.

SUBSTANCE: proposed helicopter has fuselage with main rotor, tail and end booms and steering rotor; tail boom narrows from rear compartment of fuselage towards end boom; external outlines of cross-sections of end boom have shape of aerodynamic profile forming moment of force counter-acting to reaction torque of main rotor under action of velocity head of air during horizontal flight. Secured on side of tail boom is profiled deflector with aerodynamic outer surface; nose of this deflector is located at level of separation of induction flow of air created by rotation of main rotor from lateral surface of tail boom; inner surface of deflector embraces lower part of lateral surface of tail boom forming air passage narrowing under tail boom with longitudinal slit for discharge of reaction jet of air in way opposite to motion of main rotor above tail boom. Deflector is secured on tail boom at distance equal to 0.65-0.85 of radius of rotation of main rotor blade.

EFFECT: enhanced controllability of single-rotor helicopter equipped with steering rotor in yawing under conditions of critical density of air and increased flying altitudes.

2 cl, 3 dwg

The invention relates to control apparatus (LA), as well as to indicators, displaying information about the flight parameters and LA

Helicopter // 2246426

FIELD: aviation; single-rotor helicopters.

SUBSTANCE: proposed helicopter has fuselage with main rotor, tail and end booms and steering rotor; tail boom narrows from rear compartment of fuselage towards end boom; external outlines of cross-sections of end boom have shape of aerodynamic profile forming moment of force counter-acting to reaction torque of main rotor under action of velocity head of air during horizontal flight. Secured on side of tail boom is profiled deflector with aerodynamic outer surface; nose of this deflector is located at level of separation of induction flow of air created by rotation of main rotor from lateral surface of tail boom; inner surface of deflector embraces lower part of lateral surface of tail boom forming air passage narrowing under tail boom with longitudinal slit for discharge of reaction jet of air in way opposite to motion of main rotor above tail boom. Deflector is secured on tail boom at distance equal to 0.65-0.85 of radius of rotation of main rotor blade.

EFFECT: enhanced controllability of single-rotor helicopter equipped with steering rotor in yawing under conditions of critical density of air and increased flying altitudes.

2 cl, 3 dwg

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