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49 posters

    Sukhoi LTS "Checkmate" #2

    LMFS
    LMFS


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    Sukhoi LTS "Checkmate" #2 - Page 17 Empty Re: Sukhoi LTS "Checkmate" #2

    Post  LMFS Fri May 06, 2022 8:06 am

    A bunch of patents for the LTS has been published recently, thanks to Letun, flateric, lazutchik and paralay:

    RU2770885 --> Description of the plane's features
    https://disk.yandex.ru/i/gy-SQNk9lmyltg

    RU130988 --> Drawings
    https://disk.yandex.ru/d/ekuJ73OeVWqMBg

    The rest are related to some international claims for the single and twin seater and the UCAV

    RU2021503626
    https://disk.yandex.ru/i/ZmqufNqCbHm-_Q

    RU2021503629
    https://disk.yandex.ru/i/X-IbJa2NSuDucQ

    RU2021503627
    https://disk.yandex.ru/i/UvmlOhuoweaODQ

    RU2021503628 --> no link found
    STEALTH SUPERSONIC SINGLE - ENGINE, TWO SEAT AIRCRAFT


    RU2770885
    https://www.fips.ru/cdfi/fips.dll/ru?ty=29&docid=2770885

    (54) MULTI-PURPOSE SUPERSONIC SINGLE-ENGINE AIRCRAFT

    (57) Abstract:

    The invention relates to aviation, in particular to supersonic aircraft with a low level of radar visibility. SUBSTANCE: multifunctional supersonic single-engine aircraft contains fuselage, trapezoidal wing, V-shaped all-rotating tail unit, developed side beams, lower-side air intake engine located under the nose of the fuselage, the channel of which is located along the axis of symmetry of the aircraft, central and side cargo compartments, single-engine power plant, including an engine with a jet rotary nozzle located along the axis of symmetry the plane. The design and layout scheme of the aircraft provides a reduction in the geometric and weight dimensions of the aircraft, a decrease in aerodynamic drag, a decrease in ESR and radar visibility, high flight performance, maneuverability characteristics, high stability and controllability characteristics of the aircraft, an increase in the relative volume of cargo compartments, the ability to accommodate large-sized cargo for various purposes and versatility. -ly, 7 il.


    The invention relates to aviation, in particular to supersonic aircraft with a low level of radar visibility.

    A multi-mode highly maneuverable aircraft of an integrated aerodynamic layout is known from the state of the art patent RU 2400402 C1, published. 27.09.2010, Class B64C 30/00, B64C 1/22. The aircraft contains a fuselage, the middle part of which is smoothly mated with swept wing consoles, a head and tail section, an all-rotating vertical tail and an all-rotating horizontal tail, which have the possibility of in-phase and differential deflection, a two-engine power plant and two main cargo compartments. In this case, the fuselage, the middle part of which is made flattened, has an increased width in cross-section.

    From patent RU 2440916 C1, published. 27.01.2012, Class B64D 27/20, B64D 33/02, known aircraft integrated aerodynamic layout. The aircraft contains a fuselage, a wing whose consoles are smoothly mated with the fuselage, an all-rotating vertical tail and an all-rotating horizontal tail, a twin-engine power plant and cargo compartments.

    From patent RU 2502643 C2, published. 27.12.2013, Class B64D 7/00, B64D 27/16, B64D 33/02, B64D 45/00, B64D 39/04, B64C 1/36 multifunctional aircraft with reduced radar visibility. The aircraft contains a glider, a twin-engine powerplant and a set of avionics.

    From patent RU 2583824 C2, published. 10.05.2016, Class B64D 7/08, B64C 30/00 supersonic aircraft with in-fuselage cargo compartments. The aircraft contains a fuselage, in the lower part of which large-sized longitudinal cutouts are made for tandem cargo compartments.

    The disadvantages of aircraft known from the prior art include a large geometric and weight dimension that occurs in connection with the use of two engines. The presence of two main cargo compartments makes it impossible to place bulky cargo in the side compartments. In addition, placing the main and side cargo compartments, air intake channels and wheel niches of the main landing gear supports at the same distance increases the area of the mid-section of the aircraft, which, together with a large number of aerodynamic control surfaces, increases the area of the washed surface of the aircraft, leads to an increase in weight and aerodynamic drag of the aircraft. The presence of an all-rotating horizontal tail, which forms an acute angle with an all-rotating vertical tail, leads to an increase in the ESR in the lateral hemisphere, which requires special coatings to reduce. The direct channels of the power plant's air intakes make it necessary to install special devices in them that reduce the effective dispersion area (ESR) of engines in the front hemisphere, which also leads to an increase in the weight of the aircraft. The location of the air intakes for purging heat exchangers of aircraft systems and motor compartments on the front part of the pylons of the all-rotating vertical tail unit leads to an increase in the ESR in the front hemisphere and side hemisphere, which requires the use of special measures to reduce the ESR, which causes an increase in the weight of the aircraft.

    The technical task to achieve which the invention is aimed is to eliminate the disadvantages of aircraft known from the prior art and create a light tactical aircraft with a smaller geometric and weight dimension, low radar visibility, and the ability to accommodate large-sized cargo.

    The technical result of the claimed invention is to reduce the geometric and weight dimensions of the aircraft, reduce aerodynamic drag, reduce the ESR and radar visibility of the aircraft, provide high flight and maneuverability characteristics, stability and controllability characteristics of the aircraft, increase the relative volume of cargo compartments, provide the ability to accommodate bulky cargo for various purposes and ensure the versatility of the aircraft.

    The specified technical result is achieved by the fact that the aircraft contains a fuselage, a trapezoidal wing, a V-shaped all-rotating tail unit, developed side beams, a lower-side engine air intake located under the nose of the fuselage, the channel of which is located along the axis of symmetry of the aircraft, central and side cargo compartments, a single-engine power plant including an engine with a jet rotary nozzle, located along the plane's axis of symmetry.

    The consoles of the V-shaped all-rotating tail of the aircraft are mounted on pylons and deviate from the vertical plane by an increased angle, preferably 12°-50°, and perform the functions of horizontal and vertical tail.

    The channel of the lower-side air intake of the aircraft engine has a bend in the vertical plane and a changing cross-sectional shape from U-shaped to round.

    Under the channel of the lower-side air intake of the aircraft engine is the central cargo compartment.

    Side cargo compartments, niches of the main landing gear supports, and equipment compartments are sequentially placed in the side beams of the aircraft.

    The side beams of the aircraft include controlled rotary tail parts located on the tail parts of the beams, and performing the function of an elevator.

    On the inner sides of the pylons of the installation of the V-shaped all-rotating tailplane consoles, there are air intakes for purging engine compartments and heat exchangers of aircraft systems.

    In one embodiment, the front horizontal edges of the lower-side air intake, the leading edges of the trapezoidal wing consoles and the trailing edges of the rotary tail parts of the side beams are made parallel.

    The side surfaces of the lower fuselage sides are deflected from the vertical plane by an increased angle, preferably 12°-50°.

    The side surfaces of the lower parts of the fuselage side and the outer side surfaces of the consoles of the V-shaped all-rotating tail unit are deflected by the same angle from the vertical plane.

    The invention is explained by the following drawings:

    Figure 1 - side view of the aircraft,

    Figure 2 - view of the plane from above,

    3 - view of the plane from below,

    4 - front view of the aircraft,

    5 - section A-A,

    6 - section B-B,

    7 - section B-B.

    In the presented drawings, the positions are indicated by:

    1-fuselage;

    2-side beams;

    3-trapezoid wing consoles;

    4-cantilevers of the V-shaped all-turn tail unit;

    5-jet rotary nozzle;

    6-rotating tail parts of the beam;

    7-pylons;

    8-air intakes for purging engine compartments and heat exchangers of aircraft systems;

    9-lower side engine air intake;

    10-channel of the lower side air intake of the engine;

    11-central cargo bay;

    12-side cargo bays;

    13-niches of the main landing gear supports;

    14 - equipment compartments.

    The multifunctional supersonic single-engine aircraft is a monoplane made according to the "tailless" balancing scheme with a V-shaped tail. The aircraft contains a fuselage 1, developed side beams 2, a trapezoidal wing, the consoles 3 of which are smoothly mated with the fuselage 1, a V-shaped all-rotating tail unit, the consoles 4 of which are deviated from the vertical plane of the aircraft, a single-engine power plant, including an engine with a jet rotary nozzle 5 located along the axis of symmetry of the aircraft in the engine nacelle.

    The consoles 3 of the trapezoidal wing are smoothly mated with the fuselage 1 and are equipped with mechanization of the front and rear edges, including rotary socks, elevons, flappers.

    Trapezoidal wing mechanization is used to provide control in the roll and pitch channels, improve aerodynamic quality,and increase lift.

    The consoles 4 of the V-shaped all-rotating tail unit are mounted on pylons, deviate from the vertical plane by an increased angle, preferably 12°-50°, and perform the functions of both horizontal and vertical tail units, providing the necessary stability and controllability characteristics of an aircraft that does not have a horizontal tail unit.

    Thus, in the proposed aircraft, instead of the central rotary horizontal tail unit, an all-rotating tail unit is used, combining the functions of vertical and horizontal tail units. The V-shaped all-rotating tail unit is used as a longitudinal, transverse and track control system and provides effective control and balancing of the aircraft in the longitudinal and transverse channel in all flight modes.

    In addition, the absence of a horizontal tail eliminates the sharp angle between the vertical and horizontal tail, reduces the number of edges of aircraft elements, thereby reducing the overall level of ESR of the aircraft both in the azimuthal plane and in the lateral hemisphere.

    Consoles 4 of the V-shaped all-rotating tail unit are mounted on fixed pylons 7 fixed to the side beams 2 of the fuselage 1.

    The side beams 2 include controllable rotary tail parts 6 located in the tail parts of the side beams 2.The rotary tail parts 6 are used as a longitudinal control element, i.e. they serve as elevators for controlling and balancing in the longitudinal channel.

    All available controls with simultaneous deflection can be used to increase the aerodynamic drag to perform the function of brake pads.

    On the inner sides of the pylons 7 there are air intakes 8 for purging engine compartments and heat exchangers of aircraft systems. In addition, the pylons 7 are fairings of hydraulic drives of the all-rotating tail unit.

    The lower-side air intake 9 of the engine is located under the nose of the fuselage, under the crew cabin. The inlet of the lower-side air intake 9 of the engine is located below and on the sides of the nose of the fuselage 1.

    The channel 10 of the lower-side air intake 9 of the engine has a bend in the vertical plane and a changing cross-sectional shape from U-shaped to round. This design of the channel 10 eliminates direct visibility of the engine input guide device in the front hemisphere.

    Under the channel 10 of the lower-side air intake 9 of the engine, a central cargo compartment 11 is located. In the front part of the side beams 2 of the fuselage 1 there are side cargo compartments 12, behind them in the middle part of the side beams 2 there are niches 13 of the main supports, behind them in the rear part of the side beams 2 there are equipment compartments 14. Behind the equipment compartments 14, the rotating tail parts 6 of the side beams are placed.

    The proposed design of the aircraft, embodied in a number of interrelated layout elements and the mutual arrangement of elements, namely: the use of a V-shaped all-rotating tail unit that performs the functions of both horizontal and vertical tail units, instead of an all-rotating horizontal tail unit, the location of the lower-side engine air intake under the nose of the fuselage, the use of a single-engine power plant and the presence of central and side cargo it reduces the geometric and weight dimensions of the aircraft, reduced aerodynamic drag, reduced ESR and radar visibility of the aircraft, and high flight performance, maneuverability, and stability and controllability characteristics of the aircraft.

    In addition, the use of a lower-side air intake with a channel curved in a vertical plane, changing the shape of the cross-section from U-shaped to round, eliminates direct visibility of the engine input guide device and additionally reduces the ESR of the aircraft in the front and side angles, and also allows you to place a large-volume central cargo compartment under the lower-side air intake and ensures stable engine operation in all flight modes of the aircraft.

    The location of the niches of the main landing gear supports behind the side cargo compartments allows you to reduce the area of the midsection, while at the same time allowing you to get a significant volume of side cargo compartments, ensuring the placement of bulky cargo in them. At the same time, the number of cargo compartments is reduced while maintaining the ability to accommodate the same number of bulky cargo in comparison with known analogues.

    The proposed design and arrangement of cargo compartments and niches allows you to perform them with a large volume while maintaining the small dimension of the aircraft and even reducing the geometric dimension of the aircraft. The presence of large cargo swells ensures the placement of bulky cargo for various purposes, which makes the aircraft multifunctional.

    Making the front horizontal edges of the lower-side air intake of the engine, the consoles of the trapezoidal wing and the rear edges of the rotary tail parts of the side beams parallel allows you to localize the peaks of electromagnetic waves reflected from the bearing surfaces of the airframe and, thereby, reduce the overall level of radar visibility of the aircraft in the azimuth plane.

    The side surfaces of the lower parts of the aircraft side and the outer side surfaces of the console of the all-rotating tail unit are deflected by the same angle from the vertical plane of symmetry of the aircraft (see Figure 4). This orientation of the aircraft elements contributes to the reflection of electromagnetic waves falling on the airframe elements from side angles, in the upper and lower hemispheres, thereby reducing the overall level of EPR plane in the side hemisphere.

    Thanks to the proposed structural and layout scheme of the aircraft, a reduction in radar visibility in the front and side hemispheres is achieved.

    Thus, the claimed multifunctional supersonic single-engine aircraft is a new technical solution for volume-weight and structural-power layout and is a light tactical aircraft with high key characteristics: low weight and geometric dimension, low visibility in the radar wavelength range, high flight performance and maneuverability characteristics, so it performs tasks in a wide range of applications. a range of altitudes and flight speeds.

    Claim of the invention

    1. A multifunctional supersonic single-engine aircraft containing a fuselage, a trapezoidal wing, a V-shaped all-rotating tail unit, developed side beams, a lower-side engine air intake located under the nose of the fuselage, the channel of which is located along the axis of symmetry of the aircraft, central and side cargo compartments, a single-engine power plant including an engine with a jet rotary nozzle located along the plane's axis of symmetry.

    2. The aircraft according to claim 1, characterized in that the consoles of the V-shaped all-rotating tail unit are mounted on pylons, deviate from the vertical plane by an increased angle, preferably 12-50°, and perform the functions of horizontal and vertical tail units.

    3. The aircraft according to claim 1, characterized in that the channel of the lower-side air intake of the engine has a bend in the vertical plane and a changing cross-sectional shape from U-shaped to round.

    4. The aircraft according to claim 1, characterized in that the central cargo compartment is located under the channel of the lower-side air intake of the engine.

    5. The aircraft according to claim 1, characterized in that the side beams are consistently placed side cargo compartments, niches of the main landing gear supports, equipment compartments.

    6. The aircraft according to claim 1, characterized in that the side beams include controlled rotary tail parts located on the tail parts of the beams, performing the function of an elevator.

    7. The aircraft according to claim 1, characterized in that it contains air intakes for purging engine compartments and heat exchangers of aircraft systems located on the inner sides of the pylons of the installation of V-shaped all-rotating tail units.

    8. The aircraft according to claim 1, characterized in that the front horizontal edges of the lower-side air intake, the leading edges of the trapezoidal wing consoles and the trailing edges of the rotating tail parts of the beams are made parallel.

    9. The aircraft according to claim 1, characterized in that the side surfaces of the lower parts of the fuselage side are deviated from the vertical plane by an increased angle, preferably 12-50°.

    10. The aircraft according to claim 1, characterized in that the side surfaces of the lower parts of the fuselage side and the outer side surfaces of the consoles of the all-rotating tail unit are deflected by the same angle from the vertical plane.

    Enlarged image (opens in a separate window)

    Sukhoi LTS "Checkmate" #2 - Page 17 00000001
    Sukhoi LTS "Checkmate" #2 - Page 17 00000002
    Sukhoi LTS "Checkmate" #2 - Page 17 00000003

    GarryB, dino00, Big_Gazza, zepia, Gomig-21, thegopnik, Hole and like this post

    thegopnik
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    Sukhoi LTS "Checkmate" #2 - Page 17 Empty Re: Sukhoi LTS "Checkmate" #2

    Post  thegopnik Sun May 08, 2022 5:11 pm

    I wish I studied aviation to know what the **** is being talked about lol, thanks for the source LMFS

    GarryB, Big_Gazza, LMFS and Broski like this post

    LMFS
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    Sukhoi LTS "Checkmate" #2 - Page 17 Empty Re: Sukhoi LTS "Checkmate" #2

    Post  LMFS Today at 12:37 am

    Serial production of Checkmate fighters will begin in 2027

    Head of Rostec Chemezov: serial production of Checkmate fighters will begin in 2027

    MOSCOW, May 18-RIA Novosti. The fifth-generation Checkmate light fighter will be mass-produced in Russia from 2027, Rostec CEO Sergey Chemezov said at a meeting with President Vladimir Putin on Wednesday.
    The first flight model should be created at the turn of 2023-2024.
    "We plan to start mass-producing it in 2027," Chemezov said.
    According to him, the aircraft is being created at the corporation's own expense, without attracting budget money.
    Checkmate-the first inRussian single-engine aircraft of the fifth generation, created by the company "Sukhoi "(part of the "United Aircraft Corporation")"Rostec"). The fighter was presented in July 2021 at the MAKS-2021 Aerospace Salon.
    The key features of the machine are stealth, low cost per flight hour, open architecture and high performance according to the "cost-effectiveness" criterion.

    https://ria.ru/20220518/checkmate-1789227882.html

    “Work is in progress on the design documentation for the light fighter,” adds Rostec, which hopes to sell the new model to Russia’s defence ministry, plus international customers.

    “We borrowed the onboard equipment and engine from the fifth-generation Su-57, but reconfigured them,” Chemezov notes.

    https://www.flightglobal.com/defence/russia-to-launch-su-75-checkmate-production-in-2027-rostec-says/148705.article

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