WO2013100807A1

WO2013100807A1 - Multifunctional aircraft with reduced radar visibility

Info

Publication number: WO2013100807A1
Application number: PCT/RU2012/000917
Authority: WO
Inventors: Александр Николаевич ДАВИДЕНКО; Михаил Юрьевич СТРЕЛЕЦ; Андрей Юрьевич ГАВРИКОВ; Михаил Алексеевич БОЙКО; Анатолий Ивнович ФЕДОРЕНКО; Андрей Николаевич ЛОГАРЬКОВ; Владимир Александрович РУНИЩЕВ; Сергей Юрьевич БИБИКОВ; Михаил Борисович ВАСИЛЬЕВ; Дмитрий Германович КОНОНОВ; Василий Сергеевич ЕРОФЕЕВ; Наталья Борисовна ПОЛЯКОВА; Роман Станиславович ЛЕБЕДЕВ
Original assignee: Открытое акционерное общество "ОКБ Сухого"
Priority date: 2011-12-30
Filing date: 2012-11-09
Publication date: 2013-07-04
Also published as: RU2011154437A; CN104302545A; CN104302545B; RU2502643C9; RU2502643C2

Abstract

The invention relates to the aircraft industry field, in particular to tactical aviation aircraft providing for the detection and striking of air, above-water and land-based targets. The technical result to which the invention is directed consists in reducing the radar visibility size of an aircraft to an average size of the order of 0.1-1 m². The aircraft comprises a fuselage (1), wings (2), all-flying vertical fin (AFVF) panels (3), all-flying horizontal fin (AFHF) panels (4), a cockpit light (5), horizontal lips of engine air intakes (6), fine-meshed screens closing air exhausts (7), lateral inclined lips of engine air intakes (8), a device reducing the effective scattering surface (ESS) of the power plant (9), and compartment flaps for a probe for in-flight refuelling (10). To provide for specified levels of an effective scattering surface (ESS) on the aircraft, a set of measures is carried out in relation to the airframe; to the power plant; to optical and antenna systems of a set of onboard equipment; and to equipment which is suspended and is extendible during flight.

Description

MULTIFUNCTIONAL PLANE

WITH REDUCED RADAR VISIBILITY

Technical field

The invention relates to the field of aircraft construction, in particular to tactical aircraft, providing detection and destruction of air, surface and ground targets.

State of the art

Known multifunctional aircraft (Fomin A.V. “Su-27. The history of the fighter”, Moscow, “RA Intervestnik”, 1999, p. 208-251), containing a glider, a power plant, general aircraft equipment, an indication system and controls, a complex means of destruction, active and passive countermeasures, sighting devices (radar sighting system, optoelectronic sighting system), a system for monitoring and recording parameters, a communication system between aircraft and control centers, flight and navigation system, system countermeasures, a weapon control system and passive countermeasures that provide navigation, piloting in manual and automatic control modes, integrated systems control, inter-aircraft navigation and tactical information exchange in a group, guidance from command centers, radar view of airspace and underlying surface, location airspace, detection and tracking of ground and air targets, target designation of means of destruction, statement of assets s radar interference, the use of uncorrectable weapons and air weapons (TSA) with passive thermal, passive and active radar homing for land, air and sea targets, the use of means of passive resistance.

As disadvantages of the known technical solution, it should be noted the high value of the effective scattering surface (EPR), which determines the detection characteristics of aircraft by enemy radar. For a well-known aircraft, the EPR value is about 10-15 m (here the average value for the selected angle is considered). Disclosure of invention

The technical result to which the invention is directed is to reduce the value of the radar - the visibility of the aircraft to an average value of the order of 0.1 - 1 m

The specified technical result is achieved by the fact that in a multifunctional aircraft containing a glider, a power plant, a set of on-board equipment, aviation weapons are located inside the glider, the air intake channel is made S-shaped, and radar absorbing coatings are applied to the walls of the air intake channel, while it is installed in the air intake channel a device dividing the geometric section of the air intake channel in front of the inlet guide apparatus into a series of separate cavities formed by cylindrical or flat surfaces, and the arrow-shaped edges of the air intake inlet form a parallelogram, the sweep of the front and rear edges of the bearing surfaces, air intakes, and hatch flaps are shown in two or three directions, the sides of the fuselage in the cross section, the all-inclined vertical tail is inclined from the vertical plane in one direction , air intake and exhaust devices are shielded, the compartment for refueling the aircraft with fuel in flight is closed by a sash, in addition, the space m forward constructively separate technological elements airframe filled conductive sealants, glazing lantern formed metallized, radomes made of a frequency-selective structures; optical sensors are configured to rotate in the idle state with the back side, with a radar absorbing coating applied to it, in the direction of the irradiating radar; antenna compartments are closed by shielding diaphragms; antenna planes deviated from the vertical plane; in this case, at least partially, the design of airframe aggregates was used as antennas, and the antenna-feeder system is based on low-reflection antennas in the radar wavelength range.

Brief Description of the Drawings

The invention is illustrated by drawings, where in FIG. 1 shows an airplane of integrated aerodynamic layout - top view; in FIG. 2 - aircraft integrated aerodynamic layout - bottom view; in FIG. 3 - plane integrated aerodynamic layout - front view; in FIG. 4 is a section AA of FIG. 2 .; in FIG. 5 is a section BB of FIG. 2.

In the drawings, the positions indicated:

1. fuselage

2. wing consoles

3. consoles all-inclined vertical plumage (ЦПГО)

4. consoles all-inclusive horizontal plumage (CPVO)

5. cab light

6. horizontal edges of engine air intakes

7. fine-mesh nets to cover air emissions

8. side inclined edges of engine air intakes

9. a device that reduces the EPR of the power plant

10. in-flight refueling compartment flap

Aircraft onboard equipment complex includes: general aviation equipment; display system and controls; a complex of means of destruction, active and passive counteraction; Survey and sighting devices (radar sighting system, optoelectronic sighting system); a system for monitoring and recording parameters, a communication system between aircraft and control centers; flight navigation system; system of countermeasures; a control system for weapons and passive countermeasures, providing navigation, piloting in manual and automatic control modes; built-in system control; inter-aircraft navigation and exchange of tactical information in a group, guidance from command points, a radar view of airspace and the underlying surface, detection and tracking of air and ground targets, setting active radar interference, non-correctable weapons; as well as aviation weapons with passive thermal, passive and active radar homing heads for air, ground and surface targets, passive countermeasures.

The EPR of an airplane is composed of the EPR of its following components: a glider; power plant; optical and antenna systems of the on-board equipment complex; suspended and in-flight equipment. The magnitude of the EPR of the glider and power plant is determined by three factors:

- the shape of the theoretical contours and the layout of the airframe, including the air intake and the air duct;

- the design of airframe assemblies, technological and operational joints of skins, flaps, hatches and joints between moving and fixed parts of an airframe;

- the use of radar absorbing and shielding materials and coatings. The shape of the theoretical contours and the layout of the airframe made it possible to reduce the energy of reflected EM waves in separate angles due to the redistribution of the maxima of the backscatter diagram in the minimum number of directions and in the least dangerous sectors. Constructive measures.

° Cleaning the TSA into the airframe made it possible to reduce the total EPR due to the exclusion of the reflection of electromagnetic waves irradiating radars from the TSA and their starting devices.

The implementation of the air intake channel S-shaped in combination with radar absorbing coatings (RPP) provides a reduction in EPR in axial directions. In other sectors of the front hemisphere (PPS) due to the shielding of the input guide vane (VNA) of the engine, the elements of which mainly reflect electromagnetic (EM) waves irradiating the radar, which makes up a significant share (up to 60%) in the EPR of the glider-engine system in PPP. The application of RPP on the walls of the channel of the air intake (VZ) allows to reduce the magnitude of the EM signals reflected from the VNA and re-reflected on the channel walls, thereby reducing the overall level of ESR of the VZ in the faculty.

A device 9 in the air intake channel for reducing the EPR of the engine in the front hemisphere can be installed in the channel of any shape in front of the VNA, but it is mainly installed in the “direct” channels. The device 9 acts as a screen partially overlapping the VNA in the axial directions from the ingress of EM waves. In addition to shielding, the device 9 divides the geometric section of the air-channel channel in front of the VNA into a series of separate cavities formed by cylindrical (or concentric or non-concentric) or flat surfaces, while flat surfaces can be parallel or intersecting. Each cavity has a smaller cross-sectional area than the CW channel in this zone. Such segmentation with simultaneous coating of the walls of the RPP segments makes it possible to reduce the magnitude of the EM signals reflected from the VNA and reflected to the walls of the cavities of the device 9, thereby reducing the overall level of ESR of the VZ in the teaching staff.

Reducing the sweep of the leading and trailing edges of the bearing surfaces, air intakes, and hatch flaps to two or three directions (sweep angles) other than the axial allows one to reduce the global maxima of the backscatter pattern (DOR) to these directions. Such DOR causes a decrease in the overall level of ESR in the faculty.

The inclination of the sides of the fuselage 1 in the cross section, the inclination of the vertical aerodynamic surfaces (vertical tail 4, side edges 8 of the airborne field) to one direction in the cross section allows to reduce the EPR in the side hemisphere (BPS) due to the re-reflection of the EM wave incident on the inclined surface of the airframe, in side different from the direction of the irradiating radar.

Screening of air intake and exhaust devices with structural elements, as well as with fine mesh, allows to reduce or eliminate the EPR component from the “inhomogeneities” of the airframe (such as a hole, slit, sinus) due to the fact that the linear mesh cell size of the covering inhomogeneity is less than ¹ A of the EM wavelength irradiating the plane. In such a situation, the fine-mesh network acts as a screen for the EM wave, which reduces the component of the indicated heterogeneities in the EPR.

The closure of the refueling rod compartment in flight by the sash 10 excludes the niche component and the rod in the overall EPR of the aircraft.

The use of all-rotational vertical plumage 4 allows you to reduce the total area of the VO and, as a result, reduce the level of the signal reflected from the VO, which, in turn, reduces the value of the EPR in the BPS. The use of conductive sealants allows electrical conductivity between the individual structural and technological elements of the airframe, which, in turn, eliminates the component in the EPR of the aircraft “heterogeneities” (such as gap, joint) due to the fact that in the absence of electrical inhomogeneities there is no scattering of surface EM waves . The use of RPP allows to significantly reduce the level of global ESR maxima due to the fact that the principle of the RPP is to partially absorb the energy of the EM wave incident on the material, therefore, to ensure a decrease in the level of the reflected radar signal.

The metallic glazing of the flashlight provides EM impermeability in such a way that the glazing is essentially an impenetrable inclined wall reflecting the incident EM wave away from the irradiating radar. The main measures to reduce the component of the onboard equipment complex in the EPR are.

The use of frequency-selective structures in radomes of antennas, allowing transmission of radiation in the operating frequency range of their own antenna, and to be impermeable to emissions of other frequency ranges (irradiating radar). Thus, the EM waves incident on the antenna fairings from the irradiating radars are reflected (due to the shape of the fairings formed by the surfaces inclined to the vertical plane) to the side from the irradiation direction.

Rotation of the optical part of the optical sensors in the idle state with the application of RPP on the back side. Thus, in the non-working (passive) state of the sensors (the state of minimum EPR), the sensor faces the direction of the radar irradiating side with the applied RPP - providing partial absorption of the incident EM waves, thereby reducing the EPR.

The use of shielding diaphragms in antenna compartments to eliminate the effect of a stray wave, when the irradiating wave after multiple re-reflection in a closed compartment is amplified and radiated into the outer space. A shielding diaphragm is installed around the antenna post in such a way that it borders the post on the periphery. On the wall of the diaphragm facing the irradiating radar, applied RPP. During irradiation, the protective diaphragm prevents the EM wave from penetrating into the antenna compartment, while absorbing part of the energy of the incident wave and providing a decrease in the EPR.

The deviation of the antenna plane from the vertical and, therefore, the deviation of the antenna normals from the horizontal plane provides a change in direction reflected EM waves away from the irradiating radar, thereby reducing the EPR of the antennas.

Reducing the total number of antennas and using the design of airframe assemblies as antennas (for example, vertical tail as a communication antenna). Reducing the total number of antennas reduces the overall EPR because each antenna contributes a specific component to the EPR. Using an existing airframe (VO) unit as an antenna allows not to use a separate antenna, which naturally reduces the EPR compared to the version of a separate antenna.

The use of an antenna-feeder system based on antennas that are low reflective in the radar wavelength range. The low reflective properties of the antennas are ensured by the fact that they are made non-protruding beyond the outer contours of the aircraft and do not introduce a component into the EPR of the aircraft due to direct reflection of EM waves.

The integrated implementation of the totality of these measures provides the maximum effect of reducing visibility with minimal negative impact on the aerodynamic, weighted technological, operational and other characteristics of the aircraft.

Claims

CLAIM

A multifunctional aircraft containing a glider, a power plant, a set of on-board equipment, characterized in that the aviation weapons are located inside the glider, the air intake channel is made S-shaped, and radar absorbing coatings are applied to the walls of the air intake channel, while a device separating the geometric is installed in the air intake channel the cross section of the air intake channel in front of the inlet guide vane onto a series of individual cavities formed by cylindrical or flat surfaces, and the arrow-shaped edges of the air intake inlet form a parallelogram, the sweep of the front and rear edges of the bearing surfaces, air intakes, and manholes are reduced to two or three directions, the sides of the fuselage in cross section, the all-inclined vertical tail are executed with an inclination from the vertical plane in one direction and the fence the air is filled with shielded, the compartment of the aircraft refueling rod in flight is closed by a sash, in addition, the spaces between the individual structural ologicheskimi elements airframe filled conductive sealants, glazing lantern formed metallized, radomes vsholneny of frequency-selective structures; optical sensors are configured to rotate in the idle state with the back side, with a radar absorbing coating applied to it, in the direction of the irradiating radar; antenna compartments are closed by shielding diaphragms; antenna planes deviated from the vertical plane; in this case, at least partially, the designs of airframe aggregates were used as antennas, and the antenna-feeder system is based on low-reflecting antennas in the radar wavelength range.