Pilotless flight vehicle (versions)

IPC classes for russian patent Pilotless flight vehicle (versions) (RU 2349508):

H01Q1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons

B64C39/02 - characterised by special use

B64C1/36 - adapted to receive aerials or radomes (aerials or radomes per seH01Q)

Another patents in same IPC classes:

Umbrella-type balloon antenna / 2340986

Antenna contains working elements including one of three conductive-braided captive ropes (conducting rope), counterpoise earth, umbrella-type capacitive load and vertical bar. The bar consists of two interpenetrating conductive pipes interconnecting to contact pad. One pipe is rigidly connected to lower pole of balloon gas bag, and another one is pivoted with respect to vertical axis. Aerodynamic solid body is mounted with retain strap at bar top, "umbrella" is shaped by radial conductors attached on surface of solid body. Connection point of conductors is fixed on bar top, and their free ends on solid body frame. Working elements of antenna are electrically interconnected. Antenna is excited by means of transceiver output of which is connected to conducting rope, and its body is connected to counterpoise earth. Captive balloon rise is reduced 1.8÷2.2 times with maintained antenna performance; gas consumption is considerably reduced. Reliable meteo-stable design is produced.

Spacecraft and section of phased antenna array / 2333139

Spacecraft includes the phased antenna array (PHAA) representing flat rectangular sections, each of them the structures furnished with a front covering fitted on the carcass. The spacecraft onboard equipment is fixed on the rear sides of the flat hardware platforms arranged at the PHAA sections rear. In placing the spacecraft into orbit, the PHAA sections are folded with their faces parallel to each other, with solar batteries panels being inserted there between. Transceiver units are arranged on the front covering rear with their radiator on the covering face. Thermal pipes are arranged inside the front covering and connected with the device of heat withdrawal into space. The suggested PHAA section contains a carcass, the a front skin, a transceiver units and radiators. The section carcass is made up of rectangular closed section channels furnished with an extra internal strip. The front covering made up of three-layer panels is attached to the said strip. A screen-vacuum heat-insulation layer is arranged between the aforesaid panels. The outer panel is made from carbon-based plastic material, the inner panel is made from aluminum alloy. The inner panel honeycomb structure accommodates heat pipes withdrawing heat from the transceiver units.

Balloon ultrashort-wave antenna / 2321110

Proposed ultrashort-wave balloon antenna has metal container accommodating radio station and conductors running above container surface parallel to its longitudinal axis. Counterpoise in the form of metal disk and conductors radially diverging from its edge is installed in cavity perpendicular to container longitudinal axis. One end of each conductor disposed above container is connected to container base and other, to counterpoise metal disk. Container surface is connected in addition to each of these conductors through shorting jumper. Coaxial feeder is disposed in cavity of one of jumpers and in part of conductor running to metal disk, feeder external sheath being connected to disk center and central conductor, to container top. U-shaped conductors are connected in addition to container body.

Balloon container antenna / 2321109

Proposed balloon container antenna has metal container in the form of two identical coaxially installed metal blocks with conductor leads connected to their peripheral ends. Rectangular metal plates are installed on opposite edges of blocks on each of butt-ends abutting against each other. Planes of all plates are relatively parallel and perpendicular to butt-end plane. Output coaxial feeder running from radio station is connected through shielding screen to vertex of one of triangular plates and through central conductor, to vertex of other plate. Optimal proportions of dimensions of components affording desired effect are evaluated.

Balloon antenna / 2318274

Proposed balloon antenna has metal container and metal rod secured coaxially to the latter at metal-rod base. External end of rod mounts two loop radiators orthogonal relative to one another, their outputs being integrated and connected by means of metal ring to central conductor of coaxial output of radio station disposed in metal container; connected to this central conductor is antenna counterpoise in the form of radially diverging conductors and additional conductor sections connected to their external ends. Optimal proportion of antenna structural component dimensions are determined.

Mechanical design of elongated radar antenna array for flying vehicle / 2308129

Proposed elongated radar antenna array for flying vehicle, for instance helicopter, is essentially set of printed-circuit antenna modules installed in array enclosure to form flat effective surface of antenna array by effective sides of module dipoles; antenna array is provided with enclosure-mounted suspension unit for its setting up from horizontal shipment position to vertical operating one and for rotating it in operating position by means of drives disposed in flying vehicle; antenna array has pressurized enclosure combined with antenna module dome whose function is performed by front electromagnetically transparent wall of antenna array enclosure. Antenna modules are installed on internal load-bearing partition of antenna array enclosure and disposed between this partition and mentioned front wall functioning as dome under conditions of forced air supply to antenna modules to abstract internal heat affording utmost use of external air flow during vehicle flight; its cooling facilities are disposed within enclosure, on its rear part, between its rear wall and mentioned load-bearing partition; cooling air is admitted through inlet holes of hollow longitudinal framework member built integral with load-bearing partition and positioned in parallel with antenna-module along antenna array curtain; distribution line; it is provided with inlet cooling air distribution holes on their disposition end to supply cooling air to antenna modules and to area of module clearances accommodating antenna module heat sinks forming cooling ducts for air passage through circulation ports of internal load-bearing partition to rear part of array enclosure; the latter is composite structure built of several (say, three) longitudinal parts joined together; capacity of cooling facilities is sufficient to ensure total flow not over 1.32 (l/s) x W^-1 per unit heat power released by antenna modules.

Ball antenna / 2308128

Proposed antenna that can be used for receiving television programs, for mobile and USW radio communications in zones of uncertain horizontal- and vertical-polarization wave reception is applied to surface of ball filled with light gas and is made in the form of circular loops whose geometric dimensions comply with main and additional frequency bands. Connected to loops through half-wave intervals are short-circuited stubs integrating adjacent loops. The latter can be applied along parallel or meridian lines of ball depending on wave polarization.

Folding antenna / 2304328

The antenna has three identical n-links pantographs 1,2,3 installed vertically so that they form a straight cylinder with a cross-section in the form of an equilateral triangle, adjoining to each other the ends of the elements 4₁,4₂ forming the links of the pantographs are connected to each other pivotally, some ends of the pantographs are fastened with the foundation in the shape of a beaker provided with a cover in which pantographs are located in packed state, elements 4₁, 4₂ of the links of the pantographs are connected pivotally in the centers, in the places of hinged connection of the elements there are rings 6, the antenna is provided with a holder limiting the maximal size of the antenna in an unfolding state and with a holder preventing the antenna from piling up after its unfolding.

Helicopter radar antenna-feeder assembly / 2291525

Proposed radar antenna-feeder assembly designed for trouble-free operation under variable- and vibratory-load conditions due to enhanced strength incorporated in its mechanical design and improved aerodynamic properties of elongated antenna array and feeder circuit has its receiving-radiating components forming flat elongated antenna array and high-frequency feeder circuit physically integrated with functional units; antenna array case accommodates its suspension unit for turning it by means of helicopter-mounted drive from horizontal transport position under helicopter fuselage to vertical working position and vice versa. Antenna array modules function as its stiffness ribs. Provision is made for easy disconnection of antenna array from helicopter under emergency conditions.

Spacecraft antenna-feeder assembly (alternatives) / 2276434

Proposed spacecraft antenna-feeder assembly has antennas disposed in diametric opposition to external diameter of spacecraft hull and integrated by feeder system incorporating radio-frequency feeders and power splitters connected to on-board radio system; each antenna has axially symmetric funnel-shaped directivity pattern whose opening angle is regulated by spacecraft flight path. Directions of axial minimum value of directivity pattern of antennas are combined with central direction of sector of communication angles with equipped ground measuring station during oriented flight of spacecraft; installed in immediate proximity of antennas and inserted in feeder system are radio-signal amplifiers. Antenna-feeder assembly for high-power and large-size spacecraft incorporates provision to adapt its power characteristics to spacecraft altitude changes in space, including equally probable spacecraft position in space.

Super-cargo aircraft / 2346853

In the super-cargo aircraft, structural robustness of the fuselage is partially provided for by the transported element. The super-cargo aircraft can have a fastening device for fastening the transported element to the fuselage. The fastening device is designed for holding part of the load carried by the super-cargo aircraft.

Airborne microdevice / 2339543

Airborne microdevice contains load-carrying structure in the center part which instrument compartment is located at different sides of which at least two screw blocks are located, as well as fitted in instrument compartment video camera, radio-controlled on-board vehicle flight operation system and accumulator battery. Radio-controlled on-board system is executed in the form of fitted in polyurethane base electronic unit consisting of following parts interconnected by elements of electromechanical wiring: power amplifier board, gimbailess inertial navigation system, receiver module of on-board navigation system, guidance and telemetry data receiver-transmitter module. External surface of electronic module polyurethane base is made spherical and accumulator battery is located in instrument compartment on upper side of removable plate connected with load-carrying structure by vertically directed curved stands, at that, on the lower side of this plate video camera and heating element are mounted.

Recoverable multimode unmanned flight vehicle / 2327604

Recoverable multimode unmanned flight vehicle is made as a low-wing monoplane with its body lower part incorporating a support in the form of an elastic take-on ski. The said vehicle body is made up of three parts, a nose, a central part and a tail. The nose accommodates the front horizontal empennage. A wing is formed by two detachable planes and the body central part under-fuselage section. Here the wing front edge has in plane, at least, one fracture and a straight rear edge. The vehicle has a twin-fin tail unit with an angle of flare of 20 degrees, while the air-jet engine is mounted so that the outcoming gas jet passes above the vehicle body between the fins of the tail unit.

Integrated mechanisms "vipper" for preparation and realization of remote monitoring and blocking of potentially dangerous object, fitted with unitized-modular equipment and machine-read carriers of data bases and plug-in program module libraries / 2315258

The automated complex includes miniature pilot less flight vehicles installed in the separated nose cones of salvo-fire jet projectiles, automated transport-launcher and a remote-control station fitted with the respective radio-electronic and the equipment and machine-read carriers of data bares and plug-in program module libraries. The stand-trainer has information insertion, processing, output and presentation units, automated work stations of operators, units of their support, memory, monitoring, evaluation, forecasting, program control, priority code distributors, control pulse sharper and a switchboard. The set of the interrelated stand-trainer and the complex is positioned as an integrated system of automated monitoring and blocking of potentially dangerous objects.

Unmanned flying vehicle / 2288140

Proposed flying vehicle has cantilever wing equipped with aerodynamic control members, vertical tail, engine nacelle and one engine with propeller. Engine is mounted in nacelle. Flying vehicle is made according to flying wing arrangement without fuselage. Leading edge of nose part of central profile is rounded-off and bent downward. Outlines of tail section of central profile are bow-shaped curves with convex part directed upward; these curves come together to trailing edge of central profile. Outlines of upper and lower contours of center part of central profile are straight parallel lines connected with respective outlines of nose and tail sections of central profile. Wing leading edge in plan is formed by arc of circle whose center angle is equal to 180° with center lying on chord of wing central profile. Wing trailing edge is rectilinear in plan but not swept. Nose section of wing bounded in plan by wing leading edge is formed by rotation of nose and center parts of center profile relative to said center of circle arc in plane perpendicular to plane of symmetry of flying vehicle and running through chord of central profile. Tail section of wing is rectangular in plan passing through chord of central profile. Terminal edges of rectangular section of wing are engageable with leading edge of wing nose section.

Fighting vehicle reconnaissance complex / 2272753

Proposed reconnaissance complex includes main rotor with electric drive, platform flight control system and reconnaissance equipment mounted on unmanned flying platform. Reconnaissance equipment is provided with system for transmission of data to complex control unit mounted on fighting vehicle and transmission of commands from complex control unit to platform flight control unit. Platform is provided with specimen automatic tracking system. Data transmission system is equipped with unit of conjugation with object of installation. Said control unit is provided with operator's automated position with computer and control console. Units of reconnaissance complex are connected with operator's automated position through conjugation unit.

Helicopter with radar antenna / 2245820

Radar antenna is located under fuselage and is provided with mechanisms for rotating it relative to vertical axis and turning it relative to horizontal axis. Rotation mechanism has body consisting of two parts; one part is secured in fuselage and other part is rotatable relative to first one. Radar antenna is secured on frame through strip on which charge for emergency jettisoning is mounted; said frame is connected with movable part of body by means of supports; one end of each support is connected with movable part of body and other end is connected with frame by means of axle. Rotation mechanism of radar antenna is mounted on movable part of body and is made in form of rod performing reciprocating motion by means of drive; its one end is connected with frame by means of axle and bracket. Mounted on fixed part of body is drive of mechanism turning the radar antenna relative to vertical and horizontal axes.

Helicopter with radar antenna / 2245820

Pilotless flight vehicle (versions) / 2349508

Invention relates to flight vehicle fuselage outer element designs. Pilotless flight vehicle comprises basing (1) with tight radiotransparent blister (2) and control system (3). Note that proposed designs can incorporate a self-contained compressed air source, atmospheric air pressure head, self-contained compressor or aircraft engine compressor.

Helicopter / 2361775

Proposed helicopter incorporates fenestron fitted onto tail boom and comprising a casing housing a metal duct to accommodate a screw and HF-aerial therein. The latter comprises radiating circuit and matching device wired in between the radiating circuit element and feeder coaxial cable terminal. The fenestron casing lower part is made of dielectric, while aforesaid radiating circuit represents a current-conducting bus arranged on fenestron casing bottom outer surface and connected, by its one end, to matching device output. Current-conducting bus other end is conductor-connected to previously mentioned metal duct. The latter is jointed, via metal structure of fenestron casing top, to matching device casing jointed, in its turn, to helicopter fuselage.

Method of making dielectric cowling / 2416844

Layers of Optex glass fabric saturated with binder based on polysaturated resin are successively worn on a special form and fibre glass filament is wound on top of each packet consisting of two layers of glass fabric except the last. Winding is done from top to bottom while increasing the winding spacing from 5 to 16 mm, and final moulding is carried out in a drying cabinet at temperature not higher than 50°C.

FIELD: aeronautical engineering.

SUBSTANCE: invention relates to flight vehicle fuselage outer element designs. Pilotless flight vehicle comprises basing (1) with tight radiotransparent blister (2) and control system (3). Note that proposed designs can incorporate a self-contained compressed air source, atmospheric air pressure head, self-contained compressor or aircraft engine compressor.

EFFECT: higher tightness of blisters.

20 cl, 4 dwg

The invention relates to the design of the exterior elements of the fuselage of aircraft (LA), in particular of the front fairing, which is also the envelope of the antenna does not have a mechanical connection to the radiating elements.

Known unmanned aerial vehicle (UAV), RF patent for the invention №2297950 adopted for the prototype, comprising a housing with a nose radiotransparent Radome, propulsion system, control system, including the homing head, placed under the nose fairing, payload aerodynamic surfaces, equipped with at least one mounted fuel tank, which is equipped with an aerodynamic fairing, mounted on the outside of its body with the formation of additional volume that hosts the devices more passive wideband channel seekers reported electrical communication with the control system, while the aerodynamic fairing is made with radiotransparent characteristics optimised for equipment additional channel. Alternatively, the UAV may contain an aircraft engine with an air compressor.

The essential features of the proposed UAV version 1-3 of the present invention, coinciding with the essential features of the prototype are available to the pus with radiotransparent fairing and system management. The essential features of the proposed UAV version 4 of the present invention, coinciding with significant signs of a prototype version, are the availability of housing with radiotransparent fairing, aircraft engine with an air compressor and control system.

In the currently known UAV used onboard radar station (radar), working in a narrow range of wavelengths. For UAVs with a broadband or multiband radar terms and conditions acceptable radio parameters required fairings extremely small thickness, when the thickness of the shell in the zone of radiation δ significantly less than the minimum wavelength λ radiation radar (δ=(0,05-0,1)λ) - "thin-walled" fairings. These fairings have insufficient strength for use in high-speed UAV.

The task to be solved by the invention is the provision of strength thin-walled radiotransparent fairings to allow their use on large, transonic and supersonic speeds.

To achieve the mentioned technical result according to the first variant, in UAVs, comprising a housing with a radiation transparent Radome and control system, radiotransparent fairing is airtight, and the UAV is equipped with an Autonomous source of compressed gas is, communicated with the cavity of the fairing and connected to the control system. In addition, optional: to reduce the maximum working pressure in the cavity of the fairing when the maximum capacity of the gas source (maximum operating temperature) or increased aerodynamic heating of the walls of the fairing, the UAV is equipped with a vent line gas from the cavity of the fairing having a relief valve; to ensure a smooth pressurization cavity of the fairing, reducing an acoustic load on the equipment UAV provided with a device for limiting the flow of compressed gas; to reduce the dynamic impact force of the jet of gas pressurization on the wall of the fairing, in the cavity of the fairing installed the distributor jet gas pressurization system; the UAV control for more accurate determination of the time of gas supply charge detector contains characteristic perenapryajenie fairing, for example, installed in a potentially dangerous place fairing detector limit value move the walls of the fairing, its deformation, increasing the temperature, etc.

To achieve the mentioned technical result according to the second variant - UAV, comprising a housing with a radiation transparent Radome and control system, radiotransparent fairing is airtight, and the body of a flying machine is made of a receiver pressure of atmospheric air, communicated with the cavity of the fairing. In addition, additional: exception message cavity of the fairing with the atmosphere through the receiver during storage and air transportation, in the message line of the receiver head with the cavity of the fairing installed diverter valve connected to the control system; for a more precise definition of the moment of gas supply charge control system includes a detector characteristic perenapryajenie fairing.

To achieve the mentioned technical result by the third variant - UAV, comprising a housing with a radiation transparent Radome and control system, radiotransparent fairing is airtight, and the UAV is equipped with independent compressor is communicated with the cavity of the fairing, and a drive unit connected to the control system. In addition, optional: control system includes a detector characteristic perenapryajenie fairing; to keep the pressure in the cavity of the fairing when you disconnect the compressor and expansion of technical capabilities, the message line of the compressor with the cavity of the fairing equipped with a diverter valve.

To solve the mentioned technical result according to the fourth variant in the UAV, comprising a housing with a radiotransparent fairing, aircraft engine with an air compressor and control system, radiotransparent obaka the spruce is airtight and connected to the charge air compressor. In addition, optional: to reduce the maximum working pressure in the cavity of the fairing with increasing pressure in the compressor of the aircraft engine, as well as to provide the required charge pressure cavity of the fairing, the selection of air from the regular fitting with high pressure, the UAV is equipped with a vent line gas from the cavity of the fairing having a relief valve; to reduce the flow cross-sections and masses of the mains supply and discharge of gas, pressure relief valve, and also to ensure the possibility of joining the gas supply lines charge to the standard fitting of the engine with a pressure greater than required for pressurization cavity of the fairing, the line charge fairing provided with a device for limiting the flow of compressed gas; to expand technical capabilities, in line pressurization fairing installed diverter valve connected to the control system; the control system further comprises a detector characteristic perenapryajenie fairing; UAV equipped with a vent line gas from the cavity of the fairing having a drain valve connected to the control system.

The distinguishing characteristics of the proposed device in the first embodiment UAVs are performing radiotransparent fairing sealed, UAV Autonomous source of compressed gas, reported by Spoleto fairing and connected to the control system, in addition, the presence of UAVs line of discharge of gas from the cavity of the fairing having a relief valve; a device limits the flow of compressed gas; the presence in the cavity of the fairing of the distributor jet gas pressurization; the control system of the detector characteristic of perenapryajenie fairing.

The distinguishing characteristics of the proposed device according to the second variant UAV are performing radiotransparent fairing sealed, installation on the hull receiver pressure of atmospheric air is communicated with the cavity of the fairing, in addition, in the message line of the receiver head with the cavity of the fairing diverter valve connected to the control system; the control system of the detector characteristic of perenapryajenie fairing.

The distinguishing characteristics of the proposed device according to a third variant UAV are performing radiotransparent fairing sealed, self-contained compressor, communicated with the cavity of the fairing, and a drive unit connected to the control system, in addition, the presence in the control system of the detector characteristic of perenapryajenie fairing; the presence in the message line of the compressor with the cavity of the fairing diverter valve.

Distinctive in what nakami proposed device according to the fourth variant UAV are performing radiotransparent fairing sealed and connected by a line charge air compressor, in addition, the line of discharge of gas from the cavity of the fairing having a relief valve; in line pressurization of the fairing device limits the flow of compressed gas; the presence in the line charge fairing diverter valve connected to the control system; the control system of the detector characteristic of perenapryajenie fairing; the line of discharge of gas from the cavity of the fairing having a drain valve connected to the control system.

Due to the presence of these distinctive features in conjunction with the known specified in the restrictive part of the formula, when using any of the proposed options UAV provides strength thin-walled fairing at transonic and supersonic speeds. This provides a significant gain weight designs fairing, compared with the design without pressurization system. Additionally, the UAV according to the second variant provides flight with a wide range of possible trajectories for the altitude and speed of flight, when the minimum required wall thickness of the Radome.

In addition, due to the additional items in UAV:

- on the first and fourth options excluded surge pressure in the cavity of the fairing in a wide temperature range of operation and flight regimes UAV; excluding the fast dynamic impact of a jet of gas on the wall of the Radome; reduced acoustic impact of a jet of gas pressurization equipment UAV;

- for the second, third and fourth variants decreases the possibility of accumulation in the cavity of the fairing moisture, Papademos gas pressurization;

- on the third and fourth options are provided flight with a wide range of possible trajectories for the altitude and speed of flight, when the minimum required wall thickness of the Radome.

The invention is illustrated by drawings.

Figure 1 shows the UAV according to claims 1-8 formula, equipped with an Autonomous source of compressed gas to pressurize the cavity of the fairing.

Figure 2 presents the UAV on PP-11 formula using pressurization cavity of the fairing body UAV receiver pressure of the atmospheric air.

Figure 3 presents the UAV on PP-14 formula, adjustable compressor.

Figure 4 presents the UAV on p-20 formula, in which the cavity of the fairing is in communication with the air compressor of the aircraft engine.

Represented in the drawings, figure 1-4 UAV has a body with a radiation transparent Radome 2 and the control system 3. The Radome 2 is sealed by installing partition walls 4. To the control system 3 is connected to the receiver 5 of the radio waves, is placed in the cavity of the fairing 2.

For option 1 (figure 1) UAV is equipped with independent source 6 compressed gas, indicated by the line 7 with the cavity obte is on of the motor 2 and is connected to the control system 3. Independent source 6 compressed gas may be in the form of a cylinder 8 high pressure charger 9 and a starting valve 10. In this embodiment, source 6, connected to the control system 3 is provided a supply voltage to the actuator starting valve 10 source 6. Independent source 6 may be made in the form of a cylinder of liquefied gas with a starting valve or solid-fuel generator with a starting device (not shown). The UAV is equipped with a line 11 to the discharge of gas from the cavity of the fairing 2, with the safety valve 12, and provided with a device 13 limiting the gas flow that is installed in line 7 of the message of the cylinder 8 source 6 with the cavity of the fairing 2. As the device 13 limiting the gas flow can be used to throttle or pressure reducer. In the cavity of the fairing 2 is a distributor 14 of the jet emerging from lines 7 gas pressurization and control system 3 includes a detector 15 characteristic perenapryajenie fairing 2.

For option 2 (figure 2) to pressurize the cavity of the fairing 2 compressed gas used in the receiver 16 of the pressure of the atmospheric air, mounted on the housing 1 UAV or an integral part of the housing 1 of the fairing 2, indicated by the line 17 with the cavity of the fairing 2; in line 17 is installed diverter valve 18; the control system 3 soderjatelinii 15 characteristic perenapryajenie fairing 2.

For option 3 (figure 3) for pressurization cavity of the fairing 2 UAV is equipped with independent compressor 19 is communicated with the cavity of the fairing 2 line 20 gas supply and the drive of the compressor 21 is connected to the system control 3; control system 3 includes a detector 15 characteristic perenapryajenie fairing 2; line 20 feed into the cavity of the fairing 2 is equipped with diverter valve 18.

For option 4 (figure 4) fairing 2 is connected by a line 22 pressurization with air compressor 23 aircraft engine 24 UAV. The UAV is equipped with a line 11 to the discharge of gas from the cavity of the fairing 2, with the safety valve 12. Line 22 pressurization of the Radome 2 is equipped with a device 13 limiting the gas flow and diverter valve 18 connected to the system control 3; control system 3 includes a detector 15 characteristic perenapryajenie fairing 2; UAV is equipped with a line 25 to the discharge of gas from the cavity of the fairing 2, having a drain valve 26.

UAV according to claim 1 of the formula (1) works as follows. With the acceleration of the UAV in flight or decrease its altitude increases dynamic pressure (pressure) of the jet flowing UAV flow of atmospheric air on the walls of the radio waves of the fairing 2 and the pressure drop experienced by the wall of the Radome 2, the system controller 3 outputs an electric voltage to the actuator starting valve 10 compressed gas source 6,and the compressed gas from the cylinder 8 through the open starting valve 10 through line 7 is fed into the cavity of the fairing 2, tightness is ensured by a partition wall 4; the increase of gas pressure in the cavity of the fairing 2 reduces the differential pressure perceived by the wall of the Radome 2, which ensures the preservation of the strength of the radio waves of the fairing 2 with minimum conditions radioprogramas wall thickness with increased external loads. To enable starting valve 10, the control system 3 can use the standard on-Board command, for example, run the aircraft engine, reduction, translation engine to another mode. According to claim 2 of the formula when increasing the initial temperature of the working medium of the gas source 6 in the operating temperature range or increased aerodynamic external heating of the walls of the fairing 2 increases the temperature of the gas in the cavity of the fairing 2, thus to prevent additional pressure increase in the cavity of the fairing 2 part of the gas through the line 11 and the relief valve 12 is discharged into the environment, which reduces the possible operating range of the pressure of the pressurization of the cavity 2, and thereby further reduces the work load on the wall of the fairing 2 and ensures its strength with increased external loads with a smaller wall thickness. According to claim 3 of the formula supply UAV device 13 limiting the gas flow reduces the maximum gas flow,therefore, and the velocity of the gas at the outlet of line 7 into the cavity of the fairing, with a decrease which decreases the dynamic and acoustic impact of the jet on the design of the fairing 2 and the receiver 5. According to claims 4, 5 formula dispenser 14 gas jet boost coming out of the line 7 into the cavity of the fairing, allows to distribute the force from the jet on the elements of design, to exclude local ("point") the impact of the jet on the wall of the Radome 2, and the scattering of the jet structure of the distributor 14 leads to a reduction of the acoustic impact on the design of the fairing 2 and 5 receiver. On PP-8 formula signalling device 15 allows the control system 3 to identify more precisely the moment when starting valve 10 Autonomous compressed gas source 6, and thereby avoid premature increase in pressure in the cavity of the fairing 2 and, consequently, increasing the differential pressure acting on his wall when flying UAVs in the upper layers of the atmosphere or at the earth's surface to a substantial increase in the speed of the UAV. The detector 15 is configured so that in-flight UAV to minimize the maximum operating differential pressure across the wall of the fairing 2.

UAV according to claim 9 of the formula (2) works as follows. When overclocking LA in flight or decrease its altitude increases the dynamic pressure of the jet is becausehe UAV flow of atmospheric air on the wall radiotransparent fairing 2, when the air pressure of the pressure perceived by the receiver 16 through line 17 enters the cavity of the fairing 2 and it increases the pressure accordingly, the increase in external pressure of the air flow on the wall of the fairing 2 and reduces the differential pressure perceived by the wall of the fairing 2. Reducing a pressure of the atmospheric air with a decrease in flight speed or increase in altitude, the air from the cavity of the fairing with high pressure through the line 17 and the receiver 16 of the pressure of the atmospheric air is discharged to atmosphere. Thus, the minimum pressure difference across the wall of the Radome 2 is provided at various pressures of atmospheric air, which can further reduce the required wall thickness for a UAV with a wide range of possible trajectories, with different heights and speeds. In paragraph 10 of the formula control system 3 enables the diverter valve 18 only on the sections of the trajectory with the acceleration UAV or decrease with great speed when necessary unloading the walls of the cowling 2 on the terms of his strength. The rest of the atmospheric air is not supplied into the cavity of the fairing 2, which reduces the possibility of accumulation in its cavity moisture coming from the atmospheric air. By clause 11 of the formula signalling device 15 allows the control system 3 accurately determine elati times for switching on and off diverter valve 18 and thereby further reduce the total time of the message with the atmosphere of the cavity of the fairing 2 through line 17 and the receiver 16 and accordingly, further reduce the possibility of accumulation of moisture in the cavity of the fairing 2.

UAV on p.12 of the formula (3) works as follows. For unloading the walls of the fairing 2 control system 3 supplies the actuator 21 offline compressor 19 and compressed by the compressor 19 air on the message line 20 enters the cavity of the fairing 2, providing an increase in pressure inside, with the growth of the velocity head of the atmospheric air. When reducing the velocity head of the air control system 3 power off the drive 21 of the compressor 19 and the air from the cavity of the fairing 2 on the message line 20 through the cavity of the compressor 19 is discharged into the environment. On item 13 of the formula signalling device 15 allows for more accurate control system 3 to determine the points in time for drive control 21 offline compressor 19 and thereby save the endurance of the actuator 21 of the compressor 19 and to reduce the possibility of accumulation of moisture in the cavity of the fairing 2, Papademos gas pressurization. On 14 formula diverter valve 18 allows, after increasing the pressure in the cavity of the fairing 2, to store the pressure when the actuator 21 of the compressor 19, which further saves operating life of the compressor 19 and the actuator 21 and reduces the possibility of the accumulation of moisture in the cavity of the fairing 2. Additionally, the device containing the detector 15, Addow cavity of the fairing 2 when increasing the velocity head of the atmospheric air is stopped after opening the detector 15. The system control 3 closes the diverter valve 18 and switches off the actuator 21 of the compressor 19. When reducing the speed of the UAV flight control system 3 opens the diverter valve 18, the air from the cavity of the fairing through the message line 20 and the cavity broken compressor 19 is discharged into the environment, and the pressure in the cavity of the fairing 2 is reduced. To open the diverter valve 18, the control system 3 can use the onboard team. In addition, the detector 15 may be made of a two-stage, with a pair of contacts, the defining moment the main discharge cavity of the fairing 2, to control the enable or disable of the drive 21 of the compressor 19, and a pair of contacts, a defining moment full discharge cavity of the fairing 2, for closing or opening the control system 3 diverter valve 18. Thus, the pressurization of the cavity of the fairing 2 compressor 19 to specific pressures, specific speed of the pressure of the atmospheric air, which allows the UAV to maintain a minimum pressure differential on the wall of the Radome 2 for a wide range of trajectories with different altitude and flight speed, and thereby to ensure that the fairing 2 with the minimum required wall thickness.

UAV according to § 15 of the formula (figure 4) is as Abrazame the start of the engine 24 and the promotion of the compressor 23 is increased pressure for the speed of the compressor 23 and the compressed air through the line charge 22 is fed into the cavity of the fairing 2, pressure which increases the value of the pressure in the compressor 23 at the point of connection thereto of a line charge 22. The amount of increase in the pressure in the cavity of the fairing 2 is increased and its ability to retain strength when exposed to the wall of the Radome 2 is increased pressure of atmospheric air. In the UAV according to article 16 of the formula, in case of increasing pressure in the compressor 23 of the engine 24 when changing to another mode of operation and, accordingly, the appearance of additional air flow into the cavity of the fairing 2 line pressurization 22, begins to increase the pressure in the cavity of the fairing 2, this opens the safety valve 12 in line 11, the excess air is discharged from the cavity of the fairing 2 and further increase in pressure in it stops. Thus, the presence of line 11 of the discharge gas from the cavity of the fairing 2 with safety valve 12 allows to reduce the possible surge pressure during the pressurization cavity of the fairing 2, respectively, decreases the possible pressure difference across the wall and ensures the strength of the Radome 2 with a smaller wall thickness, as compared with the device of clause 15 of the formula. On 17 formulas device 13 limiting the gas flow, for example, a throttle or pressure reducer reduces the gas flow in the pressurization cavity of the fairing 2 and, accordingly, reduce the consumption of gas is on the line 11 at the opening of the safety valve 12, that allows to reduce the required flow areas of highways 11 and 22, and the weight of the safety valve 12. Additionally, the presence of the device 13 limiting the gas flow line charge 22 of the fairing 2 provides the possibility to use not specifically made a point of joining the pressurization line 22 to the compressor 23, with the necessary pressurization of the cavity of the fairing 2 pressure, and any standard fitting bleed air from the compressor 23 of the engine 24, with a working pressure, a great need for pressurization cavity of the fairing 2. On p formula management system 3 enables the diverter valve 18 only on the sections of the trajectory with the acceleration UAV or its reduction with great speed when necessary unloading the walls of the cowling 2 on the terms of his strength. The rest of the atmospheric air is not supplied into the cavity of the fairing 2, which reduces the possibility of accumulation of moisture coming from the atmospheric air. In addition, periodic inclusion diverter valve 18 allows the pressurization of the cavity of the fairing 2 various, increasing as the speed of the UAV pressure, which further reduces the maximum operating pressure differential experienced by the wall of the Radome 2, at different flight speeds and allows to reduce the required t is Lino wall of the fairing 2 when flying UAVs in these conditions. On p.19 formula signalling device 15 allows the control system 3 to more accurately determine the time of switching diverter valve 18. The detector 15 is configured so that in-flight UAV to minimize the maximum operating differential pressure across the wall of the Radome 2, respectively, to provide strength with less wall thickness of the Radome 2. According to claim 20, of formula, with the opening of the detector 15, the system controller 3 opens the drain valve 26 in the gas discharge line 25 and closes the diverter valve 18 in line 22 pressurization of the fairing 2. The pressure in the cavity of the fairing 2 is reduced. When the circuit of the signalling device 15, the control system 3 closes the drain valve 26 in line 25, and opens the diverter valve 18 in line 22, which leads to the increase of pressure in the cavity of the fairing 2. Thus, the minimum pressure difference across the wall of the Radome 2 is provided at various speed the pressure of the atmospheric air, respectively, provided the strength of the Radome 2 with the minimum required wall thickness for a wide range of possible trajectories of the UAVs, with different altitudes and flight speeds.

1. Unmanned aerial vehicle, having a housing with a radiation transparent Radome and the control system, wherein the radiotransparent fairing is airtight, and aircraft sleep the wives Autonomous source of compressed gas, communicated with the cavity of the fairing and connected to the control system.

2. The unmanned aerial vehicle according to claim 1, characterized in that it is equipped with a vent line gas from the cavity of the fairing having a relief valve.

3. The unmanned aerial vehicle according to claim 1 or 2, characterized in that provided with a device for limiting the flow of compressed gas.

4. The unmanned aerial vehicle according to claim 1 or 2, characterized in that in the cavity of the fairing installed the distributor jet gas pressurization.

5. The unmanned aerial vehicle according to claim 3, characterized in that in the cavity of the fairing installed the distributor jet gas pressurization.

6. The unmanned aerial vehicle according to claim 1 or 2, characterized in that the control system includes a detector characteristic perenapryajenie fairing.

7. The unmanned aerial vehicle according to claim 3, wherein the control system includes a detector characteristic perenapryajenie fairing.

8. The unmanned aerial vehicle according to claim 4, wherein the control system includes a detector characteristic perenapryajenie fairing.

9. Unmanned aerial vehicle, having a housing with a radiation transparent Radome and the control system, wherein the radiotransparent fairing is airtight, hull mounted receiver voltage is RA atmospheric air, communicated with the cavity of the fairing.

10. The unmanned aerial vehicle according to claim 9, characterized in that in the message line of the receiver head with the cavity of the fairing installed diverter valve connected to the control system.

11. The unmanned aerial vehicle of claim 10, wherein the control system includes a detector characteristic perenapryajenie fairing.

12. Unmanned aerial vehicle, having a housing with a radiation transparent Radome and the control system, wherein the radiotransparent fairing is airtight, and the aircraft is equipped with independent compressor is communicated with the cavity of the fairing, and a drive unit connected to the control system.

13. The unmanned aerial vehicle according to item 12, wherein the control system includes a detector characteristic perenapryajenie fairing.

14. The unmanned aerial vehicle according to item 12 or 13, characterized in that the message line of the compressor with the cavity of the fairing equipped with a diverter valve.

15. Unmanned aerial vehicle, having a housing with radiotransparent fairing, aircraft engine with an air compressor and control system, characterized in that the radio waves fairing is airtight and connected to the charge air compressor.

16. Flying so the t 15, characterized in that it is equipped with a vent line gas from the cavity of the fairing having a relief valve.

17. The unmanned aerial vehicle according to item 16, characterized in that the line charge fairing provided with a device for limiting the gas flow.

18. The unmanned aerial vehicle according to any one of p-17, characterized in that the line charge fairing installed diverter valve connected to the control system.

19. The unmanned aerial vehicle according p, wherein the control system includes a detector characteristic perenapryajenie fairing.

20. The unmanned aerial vehicle according to item 15 or 16, characterized in that it is equipped with a vent line gas from the cavity of the fairing, with the drain valve.