OA21898A - Multi-Functional Supersonic SingleEngine Aircraft. - Google Patents

Abstract

The invention relates to the aviation field. A multifunctional supersonic single-engine aircraft comprises a fuselage, a tapered wing, an allmoving V-shaped empennage, advanced side beams, lower lateral engine air intake located under the fuselage fore section with a duel extending along the aircraft centerline, central and lateral payload bays, a single-engine power plant comprising an engine with a rotatable propulsive nozzle arranged along the aircraft centerline. The aircraft design provides reduced aircraft dimension and lower weight, reduced aerodynamic drag, reduced RCS and radar signature, high aircraft performance and maneuverable characteristics, outstanding stability and controllability characteristics, enlarged payload bays volume, multi-purpose large-sized loads capacity, as well as multi functional capability of aircraft.

Description

MULTI-FUNCTIONAL SUPERSONIC SINGLE-ENGINE AIRCRAFT

Technical field

The invention relates to aviation, particularly to low radar signature supersonic aircrafts.

Background

A multi-mode highly maneuverable aircraft with an integrated aerodynamic configuration is known in the State of the art, see patent RU 2400402 Cl, published 9/27/2010. IPC B64C 30/00. B64C I/22. The known aircraft comprises a fuselage having a middle section smoothly passing to outer wing panels and with fore and aft sections of the aircraft; the aircraft also comprises all-moving vertical fins and allmoving horizontal empennage configured to hâve inphase and differential moving capabilities; the aircraft also comprises a twin-engine power plant, and two main payload bays. The middle section of the fuselage is flattened and the fuselage has an increased width in the cross-section.

Patent RU 2440916 Cl published 1/27/2012, IPC B64D 27/20, B64D 33/02, discloses an aircraft with integrated aerodynamic configuration. The known aircraft comprises a fuselage, a wing, wherein the wing has outboard panels smoothly passing to the fuselage, the aircraft comprises all-moving vertical fins and all-moving horizontal empennage, a twin-engine power plant and payload bays.

Patent RU 2502643 C2 published 12/27/2013, IPC B64D 7/00. B64D 27/16, B64D 33/02, B64D 45/00, B64D 39/04, B64C 1/36, discloses a multi-ftinctional low radar signature aircraft. The aircraft comprises an airframe, a twin-engine power plant and an avionics suite.

Patent RU 2583824 C2 published 5/10/2016, IPC B64D 7/08, B64C 30/00 discloses a supersonic aircraft with internai payload bays. The aircraft comprises fuselage with large longitudinal cutouts in the bottom part, the cutouts configured for tandem-type payload bays.

The aircrafts known from the State of the art hâve a drawback of large géométrie overall dimensions and weight, caused by using two engines. Two main payload bays prevent from carrying large size loads in latéral bays. Furthermore, placing the main payload bay, the latéral payload bays, an air intake ducts and main landing gear wells along one distance increases fuselage mid-section area, which. in combination with large number of aerodynamic control surfaces increasing the aircraft exposed surface area, results in increasing of the aircraft weight and aerodynamical drag. Presence of the all-moving horizontal fin forming, together with the all-moving vertical fin. an acute angle, causes increased radar cross section (RCS) in the side hemisphere. which decrease requires using spécial coatings. The straight ducts of the power plant air intakes require installation of spécial devices therein to reduce engine RCS in the forward hemisphere, which also results in increase of the aircraft weight. Placing the heat exchanger air inlets of the aircraft Systems and engine nacelle al the front parts of the pylons ofthe all-moving vertical fin results in the RCS increase in the forward and side hémisphères, which requires spécial measures for the RCS decrease, which, in tum, causes increase ofthe aircraft weight.

The object of the invention is to eliminate the above indicated drawbacks of the aircrafts known in the State of the art and to provide a light tactical aircraft having lower geometrical overall dimensions and lower weight, small RCS, and having large payload capacity.

Disclosure of Invention

The technical resuit of the invention is a reduced overall dimension and lower weight of the aircraft. reduced aircraft aerodynamic drag. reduced RCS and radar signature, high aircraft performance and maneuverable characteristics, better stability and controllability characteristics, enlarged payload bays relative volume, multipurpose large-sized loads capacity, as well as multi-functional capability of aircraft.

The technical resuit described above is achîeved by an aircraft having a fuselage with a fore section, an aft section and lower side surfaces, a tapered wing having panels with leading edges, panels of an all-moving V-shaped empennage having outer side surfaces, advanced side beams, central and latéral payload bays, a single-engine power plant comprising an engine with a rotatable propulsive (jet) nozzle arranged along the

C- ô aîrcraft centerline, a lower latéral engine air intake located under the fuselage fore section and having a duct extending along the aîrcraft centerline.

The panels of the all-moving V-shaped vertical empennage are mounted on pylons and are deflected from a vertical plane for an increased angle, preferably 12° — 50°; the panels functîon as both horizontal and vertical empennage.

The duct of the lower latéral engine air intake is bent in a vertical plane and has a variable cross-section shape from a U-type shape up to a round shape.

The central payload bay is located under the lower latéral engine air intake duct.

The aîrcraft side beams accommodate in sériés: the latéral payload bays, main landing gear wells, and equipment compartments.

The aîrcraft side beams hâve controlled rotatable tail sections with trailing edges, arranged at the tail parts of the side beams, the tail sections functioning as an elevator.

The panels of the all-moving V-shaped vertical empennage are mounted on pylons, the aîrcraft comprises heat exchangers and engine nacelles with blow through air intakes. and the air intakes are located at the înboard sides of the pylons.

In one embodiment of the invention the leading horizontal edges of the lower latéral engine air intake, the leading edges of the tapered wing panels and trailing edges ofthe side beams tail sections, are ail arranged in parallel.

The lower side surfaces ofthe fuselage are deflected from a vertical plane for an increased angle, preferably 12° - 50°.

The lower side surfaces of the fuselage and the outer side surfaces ofthe allmoving V-shaped vertical empennage are deflected from a vertical plane for the same angle.

Brief Description of Drawings

The invention is clarifîed by the following drawings:

Fig. I - aîrcraft side view

Fig. 2 - aîrcraft top view

Fig. 3 - aîrcraft bottom view

Fig. 4 - aîrcraft front view

Fig. 5 - section A-A

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Fig. 6 - section B-B

Fig. 7 - section C-C

The positions at the drawings hâve the following reference numbers:

l - fuselage;

- side beams;

- tapered wing outer panels;

- panels of the all-moving V-shaped vertical empennage;

- rotatable propulsive nozzle;

- moving tail parts of the beam;

- pylons;

- blow through air intakes of the engine nacelles and heat exchangers;

- lower latéral air intake of the engine;

- duct of the lower latéral air intake of the engine;

- central payload bay;

- latéral payload bays;

- main landing gear wells;

- equipment compartments.

Detailed description

Multi-functional supersonic single-engine aircraft represents a tailless monoplane with a V-shaped fin. The aircraft include a fuselage l, advanced side beams 2, a tapered wing having outer panels 3 smoothly passing to the fuselage l, an allmoving V-shaped vertical empennage having panels 4 deflected from the aircraft vertical plane, a single-engine power plant comprising an engine with a rotatable propulsive nozzle 5 arranged in an engine nacelle along the aircraft centerline.

The outer panels 3 of the tapered wing smoothly pass into the fuselage l and are provided with high lift Systems of the leading and trailing edges including leading edge flaps, élevons and flaperons.

The high lift System of the tapered wing is used for a roll and pitch control, for increasing lift-to-drag ratios and lift force.

The panels 4 of the all-moving V-shaped vertical empennage are mounted on the pylons and are deflected from the vertical plane for an increased angle, preferably 12° — 50°; they function as both horizontal empennage and vertical fins and provide necessary stability and controllability characteristics of the aircraft not havîng a horizontal empennage.

Thercfore, instead of the central movable horizontal empennage, the proposcd aircraft is provided with the all-moving empennage that combines the functions of both vertical and horizontal empennage. The all-moving V-shaped fins are used for a longitudinal, latéral and directional control and provides effective longitudinal and latéral control, adjustment and trim in ail flight modes.

Furthermore, lack of any horizontal empennage allows to avoid an acute angle between the vertical and horizontal fins, to reduce a number of aircraft edges thus reducing the whole aircraft RCS both in an azimuth plane and the side hemisphere.

The panels 4 of the all-moving V-shaped vertical empennage are mounted at fixed pylons 7, the pylons 7 attached to the side beams 2 of the fuselage l.

The side beams 2 comprise trailing edge moving parts 6 located at the tail sections of side beams 2. The trailing edge moving parts 6 are used for a longitudinal control of the aircraft, i.e. function as an elevator for control. adjustment and trim in a longitudinal channel.

Ail présent control surfaces, when they tilt simultaneously, can be used to increase aerodynamic drag and as a drag flap.

The blow through air intakes 8 of the heat exchangers and engine nacelles of the aircraft Systems are arranged at the inboard sides of the pylons 7. Furthermore, the pylons 7 serve as fairings of hydraulic actuators for all-moving empennage.

Lower latéral air intake 9 of the engine is located under the fuselage fore section under the cockpit. An inlet of the lower latéral air intake 9 of the engine is arranged at the lower and latéral parts of the fuselage l fore section.

The duct 10 of the lower latéral engine air intake 9 is bent in a vertical plane and has a variable cross-section shape from a U-type to a round shape. Such arrangement

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21898 of the duct 10 does not allow direct visibility of the engine guide vanes in the forward hemisphere.

Central payload bay 11 is located under the duct 10 of the lower latéral engine air intake 9. The fore section of the fuselage l side beams 2 accommodâtes latéral payload bays 12. Main landing gear wells 13 are located behind the latéral payload bays 12 in the middle part of the side beams 2. Equîpment compartiments Î4 are arranged in the aft section of side beams 2. The adjustable tail parts 6 of the side beams are located behind the equîpment compartiments 14.

The proposed aircraft design embodied in a number of interrelated design components and interconnected layout of the parts, namely: using the all-moving Vshaped vertical fins as both vertical and horizontal empennage instead of the allmoving horizontal empennage, locating the lower latéral engine air intake under the fuselage fore section, using the single-engine power plant, and presence of the central and latéral payload bays. Ail these improvements make it possible to reduce the aircraft weight and geometrical dimensions, decrease aerodynamic drag, RCS and radar signature, as well as to ensure high aircraft performance and maneuverable characteristics, stabilîty and controllability characteristics.

In addition to the above said advantages, using of the lower latéral engine air intake having the duct bent in a vertical plane and having a variable cross-section shape from the U-type up to the round shape, does not allow direct visibility of the engine guide vanes and addîtionally decreases aircraft RCS in the forward and latéral aspect angles. This improvement also enables to arrange the large-sized central payload bay under the lower latéral air intake and ensures steady engine operations in ail flight modes.

Locating the main landing gear wells behind the latéral payload bays allows to reduce the mid-section area and simultaneously makes it possible to enlarge considerably the volume of the latéral payload bays and carry large-sized loads therein. This allows to reduce the number of the payload bays, while the amount of the carried large-sized loads remains the same in comparison with the known équivalents.

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The proposed design and arrangement of the payload bays and wells allows to enlarge their volume as the aircraft dimensions remain small and even has reduced size. The large-sized payload bays make it possible to carry multi-purpose large-sized loads, due to which the aircraft becomes multi-functional.

Arranging the lower latéral air intake horizontal leading edges, the tapered wing outer panels and the trailing edges of side beam adjustable tail parts in parallel allows localizing the peaks of electromagnetic waves reflected from the airframe lift surfaces and thus to reduce the whole level of the aircraft radar signature in an azimuth plane.

The aircraft lower side fuselage surfaces and the outer side surfaces of the allmoving vertical fin are deflected from the aircraft vertical symmetry plane for the same angle (see Fig. 4). Such orientation of the aircraft components contributes to reflection of the electromagnetic waves reaching the airframe components from latéral aspect angles, into the upper and lower hemispheres, thereby reducing the general aircraft RCS level in the latéral hemisphere.

The proposed aircraft design arrangement reduces the radar signature in the forward and side hemispheres.

The proposed multi-functional supersonic single-engine aircraft provides an innovative engineering solution in a volume, weight and structural design configuration being a light tactical aircraft with high key spécifications: small dimensions and lower weight, low radar-band signature, outstanding aircraft performance and maneuverable characteristics, due to which it is operational within wide range of flight altitudes and speeds.

Claims (8)

1. l. A multi-functional supersonic single-engine aircraft having a centerline and comprising the following components:

   a fuselage having a fore section, an ait section, and lower side surfaces, a tapered wing having panels with leading edges, panels of an all-moving V-shaped vertical empennage having outer side surfaces, advanced side beams, central and latéral payload bays, a single-engine power plant comprising an engine with a rotatable propulsive nozzle, wherein the rotatable propulsive nozzle is arranged along the aircraft centerline, a lower latéral engine air intake having leading horizontal edges, wherein the lower latéral engine air intake is located under the fuselage fore section and has a duct extending along the aircraft centerline.
2. 2. The aircraft as claimed in claim l, wherein the panels of the all-moving V-shaped vertical empennage are mounted on pylons, are deflected from the vertical plane for an increased angle, preferably 12° - 50°, and configured to function as both horizontal and vertical empennage,
3. 3. The aircraft as claimed in claim 1, wherein the duct of the lower latéral engine air intake is bent in a vertical plane and has a variable cross-section shape from a Utype shape up to a round shape.
4. 4. The aircraft as claimed in claim 1, wherein the central payload bay is located under the lower latéral engine air intake duct.
5. 5. The aircraft as claimed in claim 1, wherein the side beams accommodate in sériés: the latéral payload bays, main landing gear wells, and equipment compartments.
6. 6. The aircraft as claimed in claim 1, wherein the side beams hâve controlled rotatable tail sections with trailing edges, located at the tail parts of the side beams, the tail sections configured to function as an elevator.
7. 7. The aircraft as claimed in claim 1, wherein the panels of the all-moving V-shaped vertical empennage are mounted on pylons, the aircraft comprises heat exchangers and

   5 engine nacelles with blow through air intakes, and the air intakes are located at the inboard sides of the pylons.
8. 8. The aircraft as claimed in claim 6, wherein the leading edges of the lower latéral engine air intake, the leading edges of the tapered wing panels and the trailing edges of the side beams tail sections are ail arranged in parallel. . .

   10 9. The aircraft as claimed in claim l. wherein the side surfaces of the fuselage lower parts are deflected from the vertical plane for an increased angle, preferably 12° - 50°. 10. The aircraft as claimed in claim l, wherein the lower side surfaces of the fuselage and the outer side surfaces of the all-moving V-shaped vertical empennage are deflected from the vertical plane for the same angle.