New Russian single engine fighter jet

Dark Sorrow

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I think so I had come across an article which said that "The RCS of a clean FA-18 Super Hornet is the same as that of an SU-57".

I don't understand what is Wrong with these Westerners, I don't think so that the day is to far that they might even say that an F-16 is better and has less or comparible RCS to an SU-57. Let me Debunk this Propoganda:-

Here is Picture of an FA-18 Super Hornet:

View attachment 150772

Notice how there are 90 degree angles in so many places on the FA-18? 90 degree Angles are like the worst thing you can build into an aircraft and deflect radar the most and the Overall Airframe is not fully made to be Stealthy. It is a well known fact that the Americans have Definitely tried to implement some RCS reduction technics in the FA-18 but to a small degree and it cannot match the SU-57.

Here is SU-57:

View attachment 150775

SU-57 was From the starting designed in mind keeping stealth in mind and the Entire frame has been smoothed in order to give as little Radar return as possible. So SU-57 is Stealthier than American Aircrafts like FA-18, F-16, F-15 and has lower RCS than these. I don't think so that it is more stealthier than F-35 and F-22 but in reality it doesn't need to be.

But according to westerners ,a jet like FA-18 is Stealthier than an aircraft like SU-57 which has its nose Section, wings ,Stabilizers etc designed keeping stealth in mind and obviously more RAM paint etc!:lol:
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What kind of response are you talking about here?
We should avoid flaunting the term low RCS. What do you mean be term RCS?
RCS varies with variance of angle of incidence, RF-band, radar operating mode, radar frequency, ambient environmental condition, etc. Their are just too many factors.
The problem with Su-57 is that under certain condition its RCS is very bad, almost as bad as MKI, hence stealth is the biggest reasons why IAF rejected the fighter.
Their are also problem w.r.t. to infrared stealth capabilities of Su-57.
 

Super Flanker

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We should avoid flaunting the term low RCS. What do you mean be term RCS?
RCS varies with variance of angle of incidence, RF-band, radar operating mode, radar frequency, ambient environmental condition, etc. Their are just too many factors.
The problem with Su-57 is that under certain condition its RCS is very bad, almost as bad as MKI, hence stealth is the biggest reasons why IAF rejected the fighter.
Their are also problem w.r.t. to infrared stealth capabilities of Su-57.
What I was referring to above was the RCS of SU-57 when it would be carrying it's Armaments inside it's IWB. Basically it's stealth configuration.

I was Debunking the claim that an FA-18 in clean configuration has the same RCS as that of an SU-57.

Ofcourse RCS depends on several factors and RCS is never fixed. I would assume that the worst configuration for RCS would be when SU-57 is carrying something on its wing hardpoints (i.e droptanks ,missiles).

But could you please explain this "Certain condition" under which it's RCS be as bad as SU-30 MKI? Oh I would be eager to know it!
 

Dark Sorrow

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But could you please explain this "Certain condition" under which it's RCS be as bad as SU-30 MKI? Oh I would be eager to know it!
During the symposium I had also asked to elebrate on certain condition but the author diplomatically declined to get in details.
 

Super Flanker

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Russia intends to market & export Su-75 or produce it by joint effort if possible. In its video it showed people from different countries who have been its customers.
But now due to Ukrain conflict all nations are pressurized not to trade with Russia.
By the way, coming to production and Joint Effort, wasn't India and Russia in the original FGFA project meant to jointly produce components for the Fighter aircraft? From the Indian side, HAL would do it and From Russian side UAC would do it?
 

Bhartiya Sainik

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By the way, coming to production and Joint Effort, wasn't India and Russia in the original FGFA project meant to jointly produce components for the Fighter aircraft? From the Indian side, HAL would do it and From Russian side UAC would do it?
I'm not expert about that JV but what i read is Russia was demaning lots of money but not ready for tech transfer + our engineers didn't like certain design aspects.
 

blackjack

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got some news about the aircrafts patent, enjoy

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.

1652023027410.png

1652023129091.png

1652023162939.png
 

blackjack

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been awhile since there were news updated.

Названы сроки производства установочной партии перспективных истребителей Су-75 Checkmate (topwar.ru)

The United Aircraft Corporation confirmed plans for the development and production of the promising single-engine Fighter Su-75 Checkmate. The timing of the release of the installation batch of new fighters remains the same.


According to the plans of the Sukhoi company, which is part of the UAC, the installation batch of the Su-75 will be produced in 2026, as previously planned. Before that, the UAC plans to build four prototypes of the fighter, which will participate in the tests. As previously reported, prototypes will appear in 2024-2025, the installation batch in 2026, and serial deliveries of the new fighter will begin in 2026-2027. Recall that the installation batch is an industrial batch of some products, in this case fighters, manufactured to confirm readiness for mass production.


The presentation of the new Russian promising single-engine fifth-generation fighter Checkmate was held as part of the MAKS-2021 air show. The aircraft was designed taking into account the supply of both Russian Aerospace Forces and foreign customers. Declared characteristics: speed - up to 2M, flight range - up to 3 thousand km, mass of combat load - 7.4 thousand kg. Installed radar with AESA, circular optical and electronic reconnaissance system, built-in electronic interference system, optical sighting system, wide-band communication system.

The Checkmate single-engine lightweight fighter is initially created with an open architecture that allows it to be adapted to a specific customer.
 

Flying Dagger

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IAF wanted twin seater variant... That automatically means increase in RCS ... So no the RCS wasn't the only reason or the reason for backing out.


They reduced our workshare in the project to less than 10% that too namesake. While we were supposed to pay half of the development cost. Literally a Sukhoi 30 kind of deal .. but more risk and investment (engine and crucial tech still in dev phase ) with dependency on Russia for another 4-5 decades.

IAF wanted to use the money for Rafale like proven birds while Indian gov and agencies were in favour of AMCA and Tejas.

That is why we did, what we did.
 

Super Flanker

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Bro that 30 million gives you a freakin LO aircraft with decent A2A capabilities.

It's a great platform....not to forget we use mig-21s on the border with Pakis
I am quoting this post in this thread cause I think so that when talking about cheap LO aircrafts, the Su-75 is something that needs to be looked at. When the Su-75 was first unveiled to the world by Russia, then Chief executive of Rostec, Sergei Chemezov had said that Su-75 would have a price tag between the range of 20 and 30 million dollars which is really cheap for a plane of its class, but ofcourse this might simply be a marketing gimmick by the Russians to lure in buyers to purchase the Su-75, cause I have seen that while Russian defence hardware might be cheap in fly away condition but when we speak about their aircrafts especially then they are very maintenance intensive as compared to western planes. The Su-75 is primarily developed by Russia eyeing export to nations like India, Vietnam, China etc.

If that price tag of 20 to 30 million dollars for a LO aircraft like Su-75 which brings many goodies to the tables such as a good missile loadout (armaments), stealth capabilities, good radar, decent avionics etc were to turn out to be true then I see this aircraft becoming the Today's modern MiG-21, not in the sense of having a poor safety record but in the sense of the so many various countries that the Su-75 could be potentially exported to but ofcourse I cannot say much about the future of the Su-75 programme especially with the onset of several sanctions on Russia which have barred Russia from getting it's hands of crucial semiconductors needed for its hardware.
 

Gyyan

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I am quoting this post in this thread cause I think so that when talking about cheap LO aircrafts, the Su-75 is something that needs to be looked at. When the Su-75 was first unveiled to the world by Russia, then Chief executive of Rostec, Sergei Chemezov had said that Su-75 would have a price tag between the range of 20 and 30 million dollars which is really cheap for a plane of its class, but ofcourse this might simply be a marketing gimmick by the Russians to lure in buyers to purchase the Su-75, cause I have seen that while Russian defence hardware might be cheap in fly away condition but when we speak about their aircrafts especially then they are very maintenance intensive as compared to western planes. The Su-75 is primarily developed by Russia eyeing export to nations like India, Vietnam, China etc.

If that price tag of 20 to 30 million dollars for a LO aircraft like Su-75 which brings many goodies to the tables such as a good missile loadout (armaments), stealth capabilities, good radar, decent avionics etc were to turn out to be true then I see this aircraft becoming the Today's modern MiG-21, not in the sense of having a poor safety record but in the sense of the so many various countries that the Su-75 could be potentially exported to but ofcourse I cannot say much about the future of the Su-75 programme especially with the onset of several sanctions on Russia which have barred Russia from getting it's hands of crucial semiconductors needed for its hardware.
I am curious as to why Russian fifth gen and AMCA mk1 lack EOTS?
Is it so sophisticated to make or something else at play?
Wont the circular IRST return radar waves at all sides so why put IRST in a stealth fighter specially circular cause the turks are using hexagonal(? Don't know the shape exactly)
IMG_20230508_232547.jpg

Take each ray as a specific case so won't there be an angle at which there would be significant reflection?
 

Super Flanker

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I am curious as to why Russian fifth gen and AMCA mk1 lack EOTS?
Is it so sophisticated to make or something else at play?
Wont the circular IRST return radar waves at all sides so why put IRST in a stealth fighter specially circular cause the turks are using hexagonal(? Don't know the shape exactly)View attachment 203747
Take each ray as a specific case so won't there be an angle at which there would be significant reflection?
About AMCA MK-1 lacking EOTs, my knowledge about that is limited but from what I have seen in the most recent wind tunnel model of AMCA, we definitely don't see any sort of EOTS like sensor like the one found on the F-35, rather we see a conventional design IRST style sensor on the wind tunnel model of AMCA like that found on planes like Su-57, Su-30, Su-35, Rafale, Eurofighter etc. Maybe in near future they might further increment the design so as to add something like a Stealthy EOTS found on the F-35, this is something I hope to see happen from the side of the AMCA design team. On the part about EOTS then I remember correctly that DRDO's IRDE was working on an EOTS type sensor. If timeline of the completion of development of this sensor and AMCA clash together than the chances are very high that we might finally see an EOTS on the final design of AMCA.

Here is a computer representation of DRDO's EOTS on AMCA, you can search up on google for the same, you will get a lot more useful information about the same.

FNBqyABVUAM8dra.jpg


Now I would want to speak about the Su-57 and why I think it's history with the IAF might answer whether AMCA MK-1 will have an EOTS sensor or not. I will be going really brief on this part cause this thread is about the Su-75 and not about AMCA or Su-57 but yeah I will start. One of the reasons that India had dropped out of the FGFA program in 2018 was because of the poor Stealth characteristics of T-50's design (FGFA was supposed to be an Indian modification of Su-57 tailored for Indian requirements like how was done with Su-30MKI), now we call it as Su-57 though. So Su-57 at the time had a conventional IRST sensor near the cockpit window on upper side of the aircraft's nose, it still has that till now as seen with Su-57 in service with RuAF. I think because of this design, Su-57's stealth characteristics had been worsened to the point that Indian Airforce didn't have any more interest in it anymore. I don't think the IAF wants to repeat that very same mistake with AMCA by letting it have that same less stealthy design of IRST, IAF would rather want the better and more Stealthly EOTS on AMCA. Also as we have seen with various new Stealth fighters in service already around the world, and ones which have recently rolled out (I speak of Turkish TAI FX in this regard) then we observe that all them have EOTS style design on them.

Take the example of TAI-FX, it itself has a EOTS sensor over its nose, in the same place where old conventional IRST sensors would be found, only a bit more centred as to allow better alignment with the aircraft's frame and better stealth characteristics as a whole. On the F-35 it is below the nose but the shape of the sensor as to my knowledge and observation is like the same as that of the F-35.

Turkey-IRST-fighter.jpg


Now let us take another example, the J-20 in service with China's PLAAF. It too has the inclusion of the EOTS on it, similar to the one on the F-35. The design is almost identical in the case is J-20 and F-35 though with reference to EOTS.

IMG_20230509_000406.jpg


So I think that we can safely assume that this type of EOTS design would be the standard ones on any upcoming stealth plane and therefore AMCA MK-1 or MK-2 will have it but I have listed my reasons as to why AMCA MK-1 would have the EOTS type of sensor on it, whether we go with the conventional IRST design or not, that is upto the designers provided they want to compromised Stealth characteristics for something, they know better than us.

Now ask why Russian fifth generation planes lack EOTS, I don't know if you are asking about Su-57, Su-75 or both but as far as Su-75 is concerned then it is having an EOTS on it's underside. I will attach a picture and show you. Look closely at the mockup, the EOTS has been marked.

cd57fcac05ae44c982c70f7b92a9f7d5.png


Therefore Su-75 will have an EOTS sensor.

Now speaking about why Su-57 does not have EOTS, well I don't know, maybe the Russians thought that a conventional IRST was cheaper to develop, produce and maintain? That their air combat philosophy was such that they could do with a little compromise on stealth? I don't know the exact answer to this sorry.
 

Tshering22

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Some cool alien invader looking ship it is.
If they can really put it in export for 20-30 million as they say...Nothing will top it
What about the maintenance? Russian stuff costs cheap up-front but adding life-cycle costs makes them really bad. Remember, they have to export arms in a market where half the world fears sanctions and the other half is firmly in Anglo/American hands.

We are the only country that just picks and chooses whatever we want and rub it on both sides' faces when it suits us. Most of the planet is not like that.
 

Tshering22

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Russia needs development partners and an attitude adjustment. Turning us away was a disaster for their Su-57 program from a financing perspective. Su-75 will need takers but given the CAATSA scare everywhere, even traditional customers may not consider it except a handful.

Too much concept art and very less reality. Su-57 was also touted to have some crazy designs but the final product was a disappointment.
 

spacemarine2023

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Western sanctions will kill the Russian military advancements, in a decade or so Chinese will be reversing role of Russian defence supplier for next gen platforms…
India should try to grab few critical technologies specially in space and nuke subs from Russia
 

blackjack

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Russia needs development partners and an attitude adjustment. Turning us away was a disaster for their Su-57 program from a financing perspective. Su-75 will need takers but given the CAATSA scare everywhere, even traditional customers may not consider it except a handful.

Too much concept art and very less reality. Su-57 was also touted to have some crazy designs but the final product was a disappointment.
Nothing really beats a stealth aircraft that costs 20-30 million dollars along with photonic integrated circuits to hit production in 2024 for the use of photonic radars and best yet the aircraft offers compatibility options if countries feel like using their own avionics. There is also a drone version being made based on the progress from the su-70

Just because abhirup Sengupta is a fellow Indian means you have to trust everything at face value what was said on the su-57. https://www.russiadefence.net/t8640p575-su-57-stealth-fighter-news-8 that aside I am wondering when Ukraine will get more leopards and use f-35s.
 

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