Hypersonic aircraft and onboard combat laser
FIELD: aircraft engineering, weapons.
SUBSTANCE: invention relates to combat aircraft. Proposed hypersonic aircraft comprises airframe, conical nose, wings, tailplane, fuel tanks, rocket engine and fuel lines. Airframe top accommodates onboard combat laser fitted along airframe lengthwise axis. Rocket engine plant is mounted at airframe rear and incorporates turbopump unit with oxidiser and fuel impellers fitted on the shaft, turbine, starting turbine and gas generator aligned therewith, two combustion chambers and flat central body mounted there between. Turbopump unit and combat laser communicates via gas bleed pipeline incorporating gas flow rate control valve.
EFFECT: higher combat performances.
The invention relates to aviation, namely to hypersonic aircraft.
Known hypersonic aircraft by RF patent for the invention №2010744. The body of the plane is made in any longitudinal section of the cubic parabola with a blunt aft and angle of sweep of the leading edge is not less than 60°. The rudder is made in the form of a hinged front part of the body.
The disadvantage is the relatively low speed of flight of the plane M=4...6..
Known hypersonic aircraft by RF patent for the invention №210407 containing the fuselage, wings starter and main propulsion. The starting of the propulsion system made in the form of gas turbine engines - GTE, and propulsion engines in the form of a ramjet engines, specifically in the patented development is proposed to apply the pulsating detonation of the air-jet engines.
The disadvantages of this plane: a relatively low speed flight and a long time it can accelerate to hypersonic speeds due to the low thrust of the CCD.
The task of creating a hypersonic aircraft: improvement of the martial qualities of the aircraft.
The solution of the stated problem is achieved in hypersonic plane containing the fuselage, nose cone portion, wings, stabilizers, fuel tanks, rocket propulsion system and piping for supplying the components is now fuel thereto, the fact that the upper part of the fuselage along its longitudinal axis mounted combat laser aviation bushiribana, rocket propulsion system installed in the rear fuselage and contains turbopump unit, installed on the shaft impellers of oxidizer and fuel, turbine, starting turbine and coaxially mounted generator, two combustion chambers and flat Central body between them, turbopump Assembly and combat aviation laser-based piped gas extraction containing gas flow regulator. On the wings of the aircraft is equipped with laser aiming. In the forward tapered portion radially mounted four control jet nozzles connected to the controllers with auxiliary gas generator. In gazivode one of the combustion chambers installed in the controller.
These objectives are achieved in combat aviation laser-based due to the fact that it is made of gas-dynamic and piped gas extraction, containing the flow regulator gas turbopump Assembly for a turbine.
The proposed solution has novelty, inventive step and industrial applicability. Novelty is confirmed by the results of the patent research, inventive step that a new set of essential features for valila to get a new technical effect, namely reducing the acceleration of the aircraft to hypersonic speeds and increase airspeed. Industrial applicability is due to the fact that the implementation of the invention does not require a new unknown in the prior art parts and components and new technologies.
The invention is illustrated in figure 1...4, where:
figure 1 shows a diagram of a hypersonic aircraft,
figure 2 shows the section a-a,
figure 3 shows a view of the plane from behind,
figure 4 - scheme of the rocket propulsion system of the aircraft and the power of the combat aviation laser-based.
Hypersonic plane (figure 1) contains the fuselage 1, the nose cone part 2, wings 3, stabilizers 4 mounted on the axis 5 can be rotated. Axis 5 is connected to the actuator 6. The actuator 6 is connected to the control unit 7. In the rear part of the fuselage 1 posted by rocket engine unit 8 containing two combustion chambers 9 and the Central body 10. Inside the fuselage 1 is installed oxidizer tank 11 and the fuel tank 12, a pipeline for supplying oxidant 13, connected to the tank of 11 oxidant and fuel to the tank 12 in the bottom of the docked pipeline supply of fuel 14. Oxidizer tank 11 is connected by a pipeline supply of oxidizer 14 with rocket propulsion system 8. Fuel tank 13 is connected by a pipeline supplying fuel 14 with rocket DWI is athelney installation 8.
In the upper part of the fuselage 1 is a combat aviation laser-based 15 on the ends of the wings 3 lasers guidance 16, and in the front part of the fuselage 1 is the pilot's cabin 17. In the forward conical part 2 of radially mounted four governors of the nozzle 18 (figure 2)connected to the additional gas generator 19 and with the regulators 20. The fuselage 1 of the aircraft is mounted on the chassis 21 (figure 3).
Rocket engine unit 8 (figure 4) contains two combustion chambers 9 and turbopump Assembly (TNA) 22. Turbopump Assembly 22, in turn, contains installed on the shaft TNA 23 and the impeller of the oxidizer pump 24, the impeller of the fuel pump 25, starting the turbine 26, the additional fuel pump 27, with the shaft of the additional fuel pump 28 connected to the multiplier 29, accommodated in the housing 30, with the shaft TNA 23, main turbine 31 in the top part of the turbopump Assembly 22. The gas generator 32 is mounted above the main turbine 31 coaxially with the turbopump Assembly 22. The combustion chamber 21 contains a nozzle 33, made of two shells with a gap "A" between them, and the head of the combustion chamber 34 within which is made of the outer plate 35 and the inner plate 36 with the cavity "B" between them. Inside the head of the combustion chamber 34 is installed injector oxidizer 37 and fuel nozzles 38. Injector oxidizer 37 report of the cavity "b" from inside the second cavity of the combustion chamber "D", and fuel nozzles 38 report of the cavity "B" with the internal cavity of the combustion chamber "D". On the outer surface of the combustion chamber 21 has a fuel manifold 39, which runs the fuel lines 40 to the lower part of the nozzle 33. To the fuel manifold 39 is connected to the output of the fuel valve 41, the inlet of which a fuel pipeline 42 is connected to the exit of the impeller of the fuel pump 25. The output of the additional fuel pump 27 is connected by a high pressure fuel line 43 through the flow regulator 44, with the actuator 45 and the high pressure valve 46 with the gas generator 32, specifically with the cavity "E". The exit of the impeller of the pump oxidizer 24 pipeline oxidant 47 through the valve 48 is also connected to the generator 32, specifically with its cavity "W". On the head 35 of the combustion chamber 21 is installed ignition device 49, and the gas generator 31 - ignition device 50.
For starting the turbine 26 is docked the high pressure pipeline 51 with starting valve 52, which is intended for starting the turbine 26. The other end of the high pressure pipeline 52 is connected with a cylinder of compressed air 53.
To the control unit 21 electrical connections 54 connected electrosupply devices 49 and 50, the fuel valve 41, the valve oxidizer 48, the actuator of the flow regulator 45, the high pressure valve 46, starting valve 52 and the controller 55, have been fitted the th in gazivode 56 one of the combustion chambers 9.
To the fuel manifold 39 is connected vent pipe 57 with the purge valve 58. The combustion chamber 9 can be installed on the pins 59 to swing in the management of the aircraft's heading.
To turbopump Assembly 22 for turbine 31 is connected to the pipeline gas extraction 60 containing the regulator of gas sampling 61, the other end of this pipe is connected to a combat aviation laser base 15 to which is also connected to an exhaust device 62. Combat aviation laser-based contains optical head 63 to output the laser beam.
Indicative characteristics of hypersonic aircraft:
|Starting weight, t||150|
|Thrust rocket propulsion, t||2×80|
|Time set the speed of M=12, p||120|
Components of rocket fuel for rocket engines
|The combat power of the laser, MW||5|
|Time of continuous operation of the laser weapon,||600|
On hypersonic aircraft can be optionally installed conventional weapons: machine guns and air gun.
When launching the rocket propulsion system 21 from the control unit 7 serves signals for starting valve 52. The high pressure air to ground systems for high pressure pipeline 51 is fed to starting the turbine 26 and spins the rotor TNA 22. The pressure of the oxidant and fuel at the outlet of impeller pumps oxidant 22 and 23 fuel increases. The signal to open valve 41, 46 and 48. The oxidizer and fuel enter the combustion chamber 21 and the gas generator 32. A signal to the ignition device 49 and 50, the fuel mixture in the combustion chamber 21 and the gas generator 32 is ignited. Launch rocket engine 4 started. Flow regulator 44 through drive 45 control mode operation.
When starting off a rocket engine control unit 7 sends the signal to the valves 41, 46 and 48 and 55, which are closed. Then the signal to open the purge valve 52, and an inert gas purge pipe 51 flows into the fuel manifold 39 and then into the cavity "A" to remove excess fuel.
When the start and acceleration of the ISU is zvukovogo aircraft control angles of flight is a misalignment of the thrust of the combustion chamber 9 by means of the knob 55, reducing the flow of gas from the gas generator 32 into one of the combustion chambers 9. When flying in the atmosphere of the management plane performs the control unit 7 by means of the actuators 6, which rejects the stabilizers 4. When flying out of the atmosphere (in space) or in a reducing atmosphere at a height of more than 200,000 m start the auxiliary generator 19 (Fig 3) and using the controllers 20 serves the products of combustion in one of the reactive control nozzles 18.
To use the combat aviation laser-based 15 open the regulator of the gas 61, and the gas of high pressure and temperature (up to 20% of the total gas flow generated by the gas generator (22) for pipeline gas extraction 60 enters combat aviation laser-based 15, where the energy of the gas is converted into energy of the laser beam. Exhaust gas is discharged to the system gas outlet 62. The laser beam exits the optical head 63.
The landing of an aircraft is carried out horizontally on the chassis 21.
The application of the invention allowed:
1. To enhance the combat capabilities of the aircraft through the use of a powerful laser weapon and its power of high-energy gas from TNA rocket engine.
2. To increase the speed of flight of a hypersonic aircraft up to M=12.
3. To increase the ceiling plane to the level of cosmic heights, as his flight and control is not needed is and the atmosphere.
4. To speed up the process set maximum hypersonic speed.
5. To simplify the design of the fuel supply starting and engines.
6. To increase the reliability of hypersonic aircraft.
7. To increase the capacity and the specific characteristics of hypersonic aircraft,
8. To reduce the weight of the plane.
9. To ensure reliable operation of aircraft through the use of two control systems: aerodynamic and hydrodynamic.
10. To improve the startup and shutdown of the rocket propulsion system and to ensure their clearance from combustible residues after turning off the blow cavities of the combustion chambers with an inert gas.
Hypersonic plane containing the fuselage, nose cone portion, wings, stabilizers, fuel tanks, rocket propulsion system and piping for supplying fuel components to it, characterized in that on the upper part of the fuselage along its longitudinal axis mounted combat aviation laser-based missile propulsion system installed in the rear fuselage and contains turbopump Assembly installed on the shaft impellers of oxidizer and fuel, turbine, starting turbine and coaxially mounted generator, two combustion chambers and flat Central body between them, turbopump Assembly and combat aviation laser-based connected trubor what Bodom gas extraction, containing gas flow regulator.
SUBSTANCE: proposed vehicle has body stiffness ribs representing ball channels to be jointed, on one side, with the ball feeding device and, on the other side, with the actuating member. Ball-engine pistons are ball-shaped. Walls of the combustion chamber smooth-wall cylinders accommodate spark plugs, pickups of cutting in the system feeding compressed air and hydrogen portions into combustion chamber, and exhaust pipes. Gearbox ball gears ensure preset gear ratios. Differential is arranged so that central ball gears engage ball-type sun gears via operating balls fitted in recessed seats of aforesaid ball-type sun gears. Vehicle tires are furnished with ball-type tire valve and filled with working body representing oiled capsules with air forced therein at excess pressure.
EFFECT: ease of manufacture, higher safety of running.
FIELD: machine building.
SUBSTANCE: invention refers to the sphere of machine building and enables conversion of motion types. The actuator mechanism gearhead is composed of a wave generator (6), roller bodies (7) and (11), a wobble plate (13) and a crown (10) mounted onto two coaxially positioned shafts, the input one (1) and the output one (2). The roller bodies (7) and (11) are installed inside separators (8), (12) and fixed to prevent their axial and/or angular displacement. The generator (6) has a shaped butt-end groove interacting with the roller bodies (7). On the butt end surface of the crown (10) there is also a groove arranged interacting with the roller bodies (11). The roller bodies (7) and (11) interact with the wobble plate (13). The plate (13) is locked with the help of a spherical support (14) freely fit onto the shaft (2). If viewed in coaxial cross section inside the crown (10) groove there are epicycloids arc shaped channels arranged for the roller bodies (11) slideless rolling. If viewed in axial cross section the crown (10) groove shape profile is identical to that of the roller bodies (11). Numerically the roller bodies (11) do not match the arcs.
EFFECT: increase of the gearbox load capacity and performance combined with minimisation of the device weight and dimension parameters and enables the device long-term adjustable and maintainable operation under widely varying environmental conditions.
FIELD: machine building.
SUBSTANCE: invention is related to machine building, namely to frictionless bearings, and may be used in mechanisms that transform rotary motion into oscillating one. Eccentric frictionless bearing comprises external ring that is eccentric to shaft, three rolling elements of different diameter that interact with shaft and external ring, two separating rollers installed between rolling elements, and additional ring that embraces separating rollers. Besides separating rollers on both sides are adjacent to the largest rolling element. Additional ring rests on shaft and separating rollers. At that shaft, external ring and rolling elements or one of them are equipped with gear rims that are engaged.
EFFECT: simplification of drive design and manufacture technology, expansion of bearing kinematic resources.
7 cl, 6 dwg
FIELD: machine building.
SUBSTANCE: invention is designed to be used in mechanisms converting rotation into oscillation at lower frequency. The proposed plain bearing comprises outer and additional races, central intermediate rollers. First group of rollers makes an even part to interact with central roller and additional race. Second group of rollers makes an uneven part wherein each roller interacts with two even group rollers and outer race. For the bearing to be fitted on the shaft, one on even group roller is used. Outer race, roller fitted on the shaft and two rollers adjoining the latter are furnished with meshed rims.
EFFECT: maximum eccentricity of outer race relative to shaft.
7 cl, 9 dwg
SUBSTANCE: invention relates to assemblies for converting rotary movement to progressive movement and may be used for various actuators including window lifts in cars. Converter consists of a grooved body in the form of closed shape, working element of progressive movement with drive coupling and rotary drive. Working element of progressive movement is a set of cylindrical or tapered rollers with circular grooves along generatix. Rollers are placed to each other in the grooves. Rotary drive in the shape of chain gear is installed so that in the points of teeth catching with rollers, they are located in holes formed by circular grooves between each two side-by-side rollers.
EFFECT: simplification of design; improvement of manufacturability, reliability and operation life time; wider field of application.
FIELD: machine engineering, namely rolling bearing assemblies, possibly in mechanisms converting rotation to rocking motion at less frequency.
SUBSTANCE: eccentric rolling bearing assembly includes outer and inner races, two small and two large rolling bodies mutually equal in pairs and arranged symmetrically relative to diametrical cross section of bearing assembly passing through centers of outer and inner races; carrier-retainer having hinges in centers of rolling bodies. Carrier-retainer is made of two halves, each half joins large rolling body with small one through hinged guide whose length may be adjusted at assembling process of bearing assembly.
EFFECT: lowered wear degree of retainer, reduced demands for accuracy of made parts, possibility for controlling gap at operation of mechanism.
6 cl, 7 dwg
FIELD: mechanical engineering.
SUBSTANCE: ball engagement comprises at least two links made of transmitting disks (1) and (2) with periodic grooves made of closed, periodically curved over periphery, ways (3) and (4) on the links which face each other, transmitting disk (26), and chain of balls (5) which engage the grooves of all links. The surface of the links with grooves (3), (25), and (27) act on balls (5) by means of their sides. The grooves are made in the mutually stepped surfaces and are mated so that each groove in one region has increased wall height that exceeds the radius of ball (5) due to the decreased wall height in the opposite region of the groove wall in the other links. The increased walls of the grooves spaced over the periphery has the form inscribed in the surfaces of the opposite periodic grooves.
EFFECT: enhanced reliability.
FIELD: mechanical engineering; agricultural engineering; machine-tool building.
SUBSTANCE: invention relates to step speed change mechanisms. Proposed gearbox has input shaft 1 and output shaft 2 installed in housing 3, transmitting modules and gearshift controlled members. Each module 1-IV is provided with through input shaft and output shaft coaxial to input shaft. Gearshift controlled members are made as shifters, and they connect input of following module either with through input shaft or with output shaft of preceding module. Driven shaft of gearbox is connected by shifter either with through input shaft or with output shaft of last module.
EFFECT: increased number of speeds at one and the same number of transmitting modules and control members, reduced overall dimensions of gearbox.
12 cl, 8 dwg
FIELD: mechanical engineering.
SUBSTANCE: friction ball mechanism comprises driving member (3), driven member (4), and balls. Driving member (3) and driven member (4) are made of male and female spherical parts provided with ways made of grooves (5) and (6). Ring grooves (5) and (6) intersect at two points where balls are located. The angle of inclination of grooves (5) and (6) with respect to each other does not exceed the angle of ball wedging.
EFFECT: enhanced reliability.
8 cl, 12 dwg
FIELD: mechanical engineering.
SUBSTANCE: planet ball gearing comprises central bearing disk (1), central output disk (2) and floating disks (8) and (9) interposed between them. Disks (8) and (9) are mounted on the antiphase eccentrics of output shaft (7) through bearings (10) and (11). The surfaces of disks (8) and (9), which face each other, are provided with periodic raceways (12) and (13) which cooperate through the first chain of balls (14). The surfaces of floating disks (8) and (9), which face central disks (1) and (2), are provided with closed periodic raceways (16) and (17). Periodic raceway (16) cooperates with the periodic members made of semispherical hollows (18) made in the surface of bearing central disk (1) through chains of balls (19). Periodic raceway (17) cooperates with periodic members made of semispherical hollows (2) in the surface of output central disk (20) through chains of balls (21).
EFFECT: simplified method of manufacturing.
1 cl, 5 dwg
FIELD: arms and ammunition.
SUBSTANCE: invention relates to sighting systems and can be used interceptor aircraft in close-in dogfight conditions. Proposed system comprises onboard radar incorporating mirror aerial with control unit. The latter comprises mirror title, tilt and azimuth turn angle and angular speed transducers, signal processor with its input connected with receiver output, as well as indicator and unit of communication with missiles. Proposed sight incorporates coverage area shift switch and aiming control processor. First input of the latter is connected with attach mode switch, its second input being connected with coverage area shift switch, its third switch being connected with aerial mirror turn angle and angular speed transducers, its fourth input being connected with data output of the unit of communication with missiles, and fifth input being connected with aircraft altitude and roll pickups. Aiming control processor first output is connected to indicator input, its second output is connected to input of the unit of communication with missiles, third output is connected to aerial control unit input and fourth out is connected to synchroniser control input. Note here that processors are interconnected via communication lines.
EFFECT: reduced aiming interval.
SUBSTANCE: invention relates to aviation and serves to automatically aim at ground and air targets, both programmed operational. Aiming system comprises target detection and tracking unit, ballistic computer, target data base, aiming parametre generation unit and aircraft preset flight parametre generation unit. Target detection and tracking unit detect current target, tracks it and defines target current relative coordinates. In the case of programmed targets, current relative coordinates are determined in target data base from programmed target parametres and those received from external onboard data system for aircraft flight current parametres. Thus determined current coordinates of targets are transmitted to aiming parametre generation unit that receives also angular corrections computed by aircraft preset flight parametre ballistic unit. Computed aiming parametres are sent into aircraft preset flight parametre generation unit receiving also current aircraft flight parametres from external onboard data system. Aircraft preset flight parametre generation unit computes, proceeding from above specified data, required aircraft flight parametres to be sent into aircraft integrated control system, thus automatically setting aircraft into position for accurate hitting of target.
EFFECT: automatic sighting with no interference of human factor.
SUBSTANCE: invention relates to system designed to increase survivability of drone planes (DP). Proposed method comprises generating signals sent in false directions with the help of opening traps arranged on shoot-off cartridges with pyro charge and accommodated on DP fuselage, and stochastic variation of aircraft course. If DP is locked after it overcomes 1/3 to 1/2 of flight to target, enemy radar system operation is dropped out by stochastic change of DP course and simultaneous change of DP radar reflection by shooting off opening traps. Note here that trap shoot-off is made on the side opposite to DP course change. Note also that shoot-off traps re-reflect enemy radar signals to enemy fire control center in enemy frequencies and with the enemy polarisation mode. DP course is directed towards target, on final part of DP trajectory, with shoot-off of traps.
EFFECT: higher probability of overcoming enemy anti-aircraft system.
SUBSTANCE: airplane comprises fuselage, front and back wings, gas-turbine engines installed on wings, and rocket engine installed in back part of fuselage. On upper part of fuselage along its longitudinal axis there is aviation-based fighting laser installed, which is connected by air sampling pipelines that comprises controller valve to at least one gas-turbine engine and with rocket engine. Laser is arranged as gas-dynamic, comprises optical head and exhaust system, is connected by air sampling pipeline comprising controller valve to turbo-pump set downstream turbine.
EFFECT: improved fighting properties of airplane.
5 cl, 5 dwg
SUBSTANCE: invention relates to system designed to increase survivability of drone planes (DP)-missiles. In compliance with this invention, DP casing surface is furnished with hatches with pyrocartridges-traps fired in preset order in false directions. The first shooting of traps is made on starting the DP engine, the second shot is effected on approaching the target. Probing signals of the traps are intensively reflected to the enemy fire control system radar at its frequency and polarisation. When in flight, DP stochastically changes its course.
EFFECT: increase in survivability.
3 cl, 2 dwg
SUBSTANCE: helicopter is intended for detection and destruction of surface, above-water and air targets, and board radio-electronic equipment complex used in it provides for navigation, control, homing of helicopter, detection, selection, creation of conditions and commands for use of destruction means and counteraction to selected targets. Helicopter is equipped with structural complex of helicopter damage control improvement and preservation of serviceability in case of damage from hitting missiles, bullets and debris, structural complex of crew survival rate increase in case of damage from hitting missiles, bullets, debris, emergency landing and collisions with ground surface in case of failures, damages and accidental collisions in process of low-height flight, structural complex of emergency abandonment of helicopter by crew, structural complex of helicopter functional resources expansion. Complex of board radio electronic equipment is equipped with external permanent memory and computer-logical modules introduced in board computer system for combined survey of surrounding space and target designation, creation of low-height flight parameters, formation of group helicopter navigation parametres, coordinated performance of helicopter group actions. Suggested helicopter and board radio-electronic equipment used in it are characterised by expanded functional resources.
EFFECT: improved indicators of survivability and fighting efficiency of helicopter and interactive fighting complex as a whole.
3 cl, 1 dwg
SUBSTANCE: invention is related to on-board radio-electronic equipment and is intended for control of aviation weapons (AW) preparation and application. System of weapons control comprises controller, exchange modules and coupling modules, inbuilt cannon set (ICS) control module, remote blocks, and also panel of surface preparation, panel of selection and panel of control and indication. Depending on type of target and actual tactical environment pilot may change shooting speed of inbuilt cannon set, and also to train the system without application of battle or training type of weapons and inbuilt equipment control.
EFFECT: increased efficiency of inbuilt cannon set (ICS) application.
2 cl, 1 dwg
FIELD: weapons and ammunition.
SUBSTANCE: invention relates to sights and can be used incorporated with fighter-interceptors for close-in dogfighting. The proposed invention aims at reducing the in-flight view time in attacking air target. To this end, the aircraft sight circuit additionally incorporates a delay circuit, while the aerial mirror drive shifting the said mirror along the inclined line is furnished with the 3rd control input, commutator and 3rd threshold device. Note here the 3rd threshold device signal input is connected to the drive code-shaft transducer, while its output and the 2nd threshold device output are connected, via the commutator signal inputs, to power amplifier input. The commutator control input is connected to the 3rd control input of the drive. Note also that the said delay device in connected in between the drive 3rd control input and memory output.
EFFECT: reducing the in-flight view time in attacking air target.
FIELD: aircraft engineering.
SUBSTANCE: invention relates to defense arms, namely, to highly-accurate guides short-range weapons to be used at attack helicopters and aircraft. Proposed complex incorporates surveillance-aiming system with thermal vision sight, guidance drives and turn angle pickups, onboard computer, video monitor, helicopter flight parameters pickups and control board. It comprises also missiles with steering drives, booster and sustainer arranged in transport-and-launch containers mounted on the launching unit. The represents lift-and turn system, while the surveillance-aiming system is additionally furnished with laser beam rocket control unit and target tracking automatic device.
EFFECT: efficient hitting of several stationary and movable small-sixe surface and high-speed air targets by battery launching of high-velocity guided missiles.
FIELD: transport, weaponry.
SUBSTANCE: invention relates to systems designed to control preparation and application of existing and promising types of aircraft combat hitting equipment (ACHE), including highly accurate missiles, control being effected using the data received from the satellite guidance systems and ACHE new types with interface operated via multiplex data exchange channels. The proposed system incorporates the ACHE power and data channels, interface units, system-to-system and local multiplex data exchange channels.
EFFECT: higher efficiency of combat performances.
FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering, particularly, to methods of decreasing the aircraft sound shock levels. In compliance with proposed invention, cryogenic fluid is blown out at pressure across the incoming air flow at the bottom surface of fuselage nose blunted parts, nearby the area wherein an intermediate (trailing) shock wave is formed and on a site of the surface with cross-section sector that features angle φ not less than 90° and an untight perforation. Liquid nitrogen or aircraft engine cryogenic fuel is used as a cryogenic liquid. The plane comprises a fuselage with blunted nose part and a site of the surface with an untight perforation. The fuselage noise represents a polynomial body of rotation. The surface of the said body is smoothly aligned with surface of spherical blunting. The blunting radius is selected so that to provide the nose part frontal drag not exceeding that of the initial polynomial body of rotation of identical elongation The site of the surface with untight perforation is located in the area wherein an intermediate (trailing) shock wave is formed and on a site of the surface with cross-section sector that features angle φ not less than 90°. Note that this area if thermally isolated along the perimetre from the fuselage adjacent surface, while the degree of perforation on the said area decreases downstream of the airflow.
EFFECT: essential decrease in sound shock level without increase in aerodynamic drag.
4 cl, 9 dwg