Aviation holding company "dry". Integral aerodynamic aircraft Sagittarius Mikhail Yurievich biography

The company provides a full cycle of work in the aircraft industry - from design to effective after-sales service. Holding products - combat aircraft Su brand.

Contact faces

Slyusar Yuriy Borisovich - Chairman of the Board of Directors
Ozar Igor Yakovlevich - General Director

Projects

Fifth generation program - The main program in this area is the project to create a promising aviation complex front-line aviation
- Su-34 - By order of the Ministry of Defense of the Russian Federation, mass production modern multifunctional fighter-bomber Su-34
- Modernization of the Su-24M - A program to create a modernized Su-24M2 front-line bomber in order to modernize aircraft in service with the Russian Air Force
- Modernization of the Su-27SM and Su-27UB - The program is aimed at a deep modernization of aircraft in service with the Russian Air Force in order to create a fighter with a significantly increased combat effectiveness and new characteristics in terms of aerodynamics, avionics, control systems and other systems
- Modernization of the Su-25SM - The main direction of the Su-25SM modernization is to improve the accuracy characteristics and modes of application of ASP
- Su-35S - By order of the Russian Air Force, a program is being implemented to create a deeply modernized super-maneuverable multifunctional 4++ generation fighter
- Sukhoi civil programs - A subsidiary of Sukhoi Company PJSC - Sukhoi Civil Aircraft JSC, in broad international cooperation, is implementing a program to create a family of regional passenger aircraft Sukhoi Superjet 100

Historical reference:

The history of the "Sukhoi Design Bureau" originates from the brigade No. 4 of the TsAGI AGOS, which in October 1930. headed by P.O. Dry. It was from this moment that the formation of the design team of the future OKB began.

In the next nine years, this team created: experienced fighters - I-3, I-14, DIP;
- a record RD aircraft, on which the crews of V.P. Chkalov and M.M. Gromov made a number of outstanding flights, and the crew of M.M. Gromova set an absolute world record for straight-line flight distance - 10148 km, covering this distance in 62 hours 17 minutes;
- long-range bomber DB-2, on a modified version of this aircraft - "Motherland" female crew V.S. Grizodubova made a non-stop flight from Moscow to the Far East;
- multi-purpose aircraft BB-1 (since 1940 - Su-2), which was the first of the "Sukhikh family" to be built in a large series (910 aircraft) and took an active part in the Great Patriotic War in versions of a short-range bomber and artillery reconnaissance spotter.

To introduce the BB-1 into the series, by a government decree of July 29, 1939, P.O. Sukhoi is appointed Chief Designer. He, together with the design bureau team, which received the status of an independent one, is transferred to the serial aircraft plant No. 135 in Kharkov.

Further activities of the team are aimed at creating: modifications of the Su-2 aircraft;
- an experienced armored attack aircraft Su-6 in single and double versions, for which in 1943, P.O. Sukhoi was awarded the Stalin Prize, 1st class;
- an experienced cannon fighter Su-1 (Su-3);
- an experienced long-range double armored attack aircraft Su-8;
- experimental Su-5 and Su-7 fighters with combined power plants.

Since 1945, the Design Bureau has been developing and building:

Jet fighters Su-9, Su-11, Su-15, Su-17 (the first with these names);
- Su-10 jet bomber;
- twin-engine piston reconnaissance spotter Su-12.

On the basis of the Tu-2 bomber, the UTB-2 training bomber is being created and put into mass production, in addition, passenger and air cargo aircraft, the Su-14 jet attack aircraft and a number of other aircraft are being designed.

For five post-war years in the OKB for the first time in domestic practice were created and implemented: booster aircraft control system;
- brake landing parachute;
- ejection seat with telescopic trolley;
- detachable forward fuselage with pressurized cabin.

E.A. Ivanov In November 1949, by decision of the government, the Design Bureau was liquidated and restored again only in May 1953, but already on a new production base. The "second birth" of the design bureau coincided in time with the advent of supersonic jet aviation. Therefore, the main directions in the work of the design team at the initial stage were the supersonic S-1 and T-3 fighters. On the basis of the S-1, a family of Su-7, Su-17 fighter-bombers and more than 20 of their modifications is being created, moreover, the Su-17 became the first aircraft in the USSR with a variable sweep wing. The experimental T-3 served as the basis for the first domestic aviation missile system interception of Su-9-51 targets and the Su-11-8M and Su-15-98(M) complexes created later. In the 1960s, the list of equipment developed at the design bureau was expanding. Since 1962, work has been underway to create a long-range strike and reconnaissance complex T-4, the first flight of an experimental vehicle took place on August 22, 1972. For the first time in our country, this aircraft was equipped with an electric remote control system and an autothrottle, and the airframe was made of welded titanium and high-strength steel.

In 1969, the Su-24 front-line bomber with a variable sweep wing, the first domestic all-weather strike aircraft, took off. The Su-24 was mass-produced and had several modifications. It is currently in service with the Air Force of the Russian Federation and a number of other countries.

In 1975, the Su-25 armored attack aircraft, designed to destroy targets on the battlefield, made its first flight. The Su-25 is the first domestic serial jet attack aircraft, has several modifications and currently forms the basis of the Russian army aviation.

In 1969, the Design Bureau began to develop a fourth-generation fighter, and in 1977 the prototype of the Su-27 fighter made its first flight. In subsequent years, on the basis of the Su-27, the following were created: Su-27UB, Su-30, Su-32, Su-33.

M.P. Simonov For the implementation of developments in design solutions, the development of new materials and technological processes, an experimental Su-47 aircraft is being created (first flight in 1997).

The experience in the creation of aviation equipment, accumulated by the OKB team over many decades, made it possible to create a family of aerobatic aircraft Su-26, Su-29, Su-31. Speaking on these machines, the USSR and Russian national aerobatics team won 156 gold medals at the World and European Championships, and a total of 330 medals.

In the early 90s, the Design Bureau launched work on civilian topics; in 2001, the Su-80GP cargo-passenger aircraft and the Su-38L agricultural aircraft made their first flights.

Currently, JSC "Sukhoi Civil Aircraft" is developing a family of regional aircraft Sukhoi Superjet 100.

IN different years the team was headed by P.O. Sukhoi, E.A. Ivanov, M.P. Simonov, from 1999 to July 30, 2007, the General Director was M.A. Pogosyan. From July 31, 2007 Executive Director JSC Sukhoi Design Bureau was appointed Igor Yakovlevich Ozar, who until that time had held the position of Deputy Director General in economics and finance - financial director OAO Sukhoi Design Bureau.

On June 30, 2011, the Board of Directors of OAO Sukhoi Company appointed I.Ya. Ozar as General Director of OAO Sukhoi Company.

Since January 1, 2015, Mikhail Yuryevich Strelets has become Deputy General Director - Director of Sukhoi Design Bureau, a branch of OAO Sukhoi Company.

Over many decades, the OKB team has created about 100 types of aircraft and their modifications, of which more than 60 types were mass-produced, and the total number of serially produced aircraft exceeds 10,000 copies. Over 2,000 aircraft have been delivered to 30 countries around the world. More than 50 world records have been set on Su aircraft.

OAO Sukhoi Company completed all stages of reorganization in the form of merger of three subsidiaries - OAO Sukhoi Design Bureau, OAO KnAAPO named after Yu.A. Gagarin and OAO NAPO named after V.P. Chkalov and received a notice of termination from January 1, 2013, the activities of the listed companies as independent legal entities. into the structure of a unified legal entity now included as branches - Novosibirsk Aviation Plant. V.P. Chkalov, Komsomolsk-on-Amur Aviation Plant. Yu.A. Gagarin, Sukhoi Design Bureau, as well as the company's representative offices in the Republic of India, Vietnam and China.

Other:

PJSC "Company" Sukhoi "is the leading aircraft manufacturing holding in Russia, which produces about a quarter of the products of Russian aviation industry. The holding is one of the top three world exporters of modern combat fighters.
The history of the Sukhoi Design Bureau dates back to the 1930s, when a design team was formed under the leadership of Pavel Osipovich Sukhoi. In 1939, a bureau was organized in which for 65 years projects of first-class aircraft have been created, bringing world fame to domestic aviation.
The leadership of Sukhoi Company in the field of designing aviation equipment for various purposes has been largely achieved due to many years of experience in conducting research and development work in various areas.
The holding includes leading Russian design bureaus and serial aircraft manufacturing plants. The company provides a full cycle of work in the aircraft industry - from design to effective after-sales service.

Participation in associations

Public Joint Stock Company "United Aircraft Corporation" (PJSC "UAC") was established in accordance with the Decree of the President of the Russian Federation of February 20, 2006 No. 140 "On the Open Joint Stock Company "United Aircraft Corporation". Registration of the Corporation as a legal entity took place on November 20, 2006 The Society is established Russian Federation by adding to it authorized capital state-owned stakes in aviation enterprises (according to Appendix 1 to Decree of the President of the Russian Federation No. 140 dated February 20, 2006), as well as private shareholders of Irkut Corporation OJSC. , production, sales, operation support, warranty and service maintenance, modernization, repair and disposal of aviation equipment for civil and military purposes.

Companies in the group: 19

Non-commercial partnership"Union of Aviation Industry" of Russia (until April 2009 - international union aviation industry) is a sectoral industrial association that promotes the development of the aircraft industry, improving social and legal status enterprises of the industry, providing legal and methodological assistance, protecting the corporate interests of the aviation industry at all levels of legislative and executive power, as well as in relevant international organizations. SAP was established in 2002 on the initiative of the leading Russian aviation enterprises with the support of Rosaviakosmos and the Interstate Aviation Committee and unites more than 80 leading enterprises in the aircraft manufacturing, engine building, instrument and unit building, repair plants, design bureaus, research institutes, insurance companies and banks, associations, foundations, joint-stock companies associated with the aviation industry. The enterprises that are members of the Union in 2011 produced more than 70% of the total volume of products of the aircraft industry.

Companies in the group: 60

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1. A beautiful wooden coat of arms hangs in the foyer of the museum.

2. In the first room meets the bust of Pavel Osipovich Sukhoi.

3. The exposition of the museum is rather laconic, not overloaded with unnecessary information.

4. Genealogy of all aircraft created under the leadership of Sukhoi (click on the picture to enlarge).

5. Chinese gift.

6. Our guide Pavel Plunsky.

7. Development of the OKB territory. It all started with an old hangar built before 1929.

8. Here is the layout of this hangar, it has survived to this day.

9. Heads of the enterprise.

10. The first serial fighters - I-4 (1927) and I-14 (1933)

11. Experienced double cannon fighter DIP (1935)

12. Long-range bomber DB-2 (1936)

13. On a modified version of this aircraft - "Motherland" the female crew of V.S. Grizodubova made a non-stop flight from Moscow to the Far East.

14. Su-2 bomber prototype (1940)

15. Experienced armored attack aircraft Su-6 (1943)

16. Experimental Su-5 and Su-7 fighters (1944)

17. In the pre-war years and the first years of the Great Patriotic War, the Sukhoi team ensured the serial production of Su-2 aircraft. A total of 893 copies were produced, they successfully fought on the fronts.

18. After the war, the era of jet aviation began.

19. Experienced reconnaissance spotter Su-12 (1947) and jet bomber Su-10 (1947)

20. From the Su-10, in 1948 transferred to the MAI as study guide, only the steering column with pedals remained.

21. In 1949, the Sukhoi Design Bureau was liquidated, but restored already in 1953.

22. In 1955, a Su-7 jet fighter took off into the sky.

23. Ski chassis from the S-26 aircraft - an experimental modification of the Su-7.

24. All-weather fighter-interceptor Su-9 and its prototype T-3. Nearby is the Su-15 fighter-interceptor, which for a long time formed the basis of the USSR air defense.

25. Su-17 - the first Soviet aircraft with a variable sweep wing.

26. Assembly of the Su-17 at the factory.

27. A semi-disassembled Su-15 is all the photos on the museum stands.

28. The most important milestone in the history of the Design Bureau was the creation of the Su-25 armored attack aircraft.

29. Model of one of its modern modifications.

30. The fuel tanks of the Su-25 were filled with foam rubber, protecting against the explosion of fuel vapors.

31. A piece of armor that has passed the tests.

32. In 1969, the design bureau began to develop a fourth-generation fighter. Here is the first purge model for TsAGI.

33. Compare with what happened in the end.

34. Helmet of the pilot of the Su-27.

35. Su-27 without paint - a record P-42 aircraft.

36. Personal belongings of test pilots of design bureaus.

37. Suit of testers.

38. Su-33 - a version of the Su-27 for ship-based.

39. The latest development of the Sukhoi Design Bureau is the Su-34 multifunctional fighter-bomber.

40. But not only military aircraft and the passenger SSJ-100 were developed in this design bureau.

41. Into the Su-38 light agricultural aircraft, which did not go into the series.

42. S-82 - an army version of the experimental Su-80.

43. But the most amazing machine created in the Sukhoi Design Bureau is, without a doubt, the T-4 strike and reconnaissance complex, or “project 100”. For the first time in the practice of aircraft construction, it was introduced: a welded airframe made of titanium and high-strength steels, an electrical remote control system, a high-temperature multiple redundant hydraulic system ultra-high pressure, autothrottle, adjustable mixed-compression air intake, internal weapons bays and many other original devices and technological solutions.

44. As you know, in 1974 the “weaving” project was closed, the only flying copy of the car ended up in Monino.

45. And in the OKB Museum you can see the Sokol aviation spacesuit, developed at Zvezda Research and Production Enterprise.

46. It was designed to control high-altitude aircraft systems with a long range.

47. T-4 pilots were supposed to fly in such vestments.

48.

49.

50. If the “weaving” is known to almost all aviation lovers, then few people know that passenger supersonic aircraft were also designed on its basis. Salon SPS T-4 was designed for 64 passengers.

For the invitation to the tour, I thank the staff of the OKB im. Sukhoi and Evgeny Lebedev.

The company provides a full cycle of work in the aircraft industry - from design to effective after-sales service. The holding's products are combat aircraft of the Su brand.

Contact faces

Slyusar Yuriy Borisovich - Chairman of the Board of Directors
Ozar Igor Yakovlevich - General Director

Projects

Fifth generation program - The main program in this area is the project to create a promising front-line aviation complex
- Su-34 - By order of the Ministry of Defense of the Russian Federation, serial production of the modern multifunctional fighter-bomber Su-34 is underway
- Modernization of the Su-24M - A program to create a modernized Su-24M2 front-line bomber in order to modernize aircraft in service with the Russian Air Force
- Modernization of the Su-27SM and Su-27UB - The program is aimed at a deep modernization of aircraft in service with the Russian Air Force in order to create a fighter with a significantly increased combat effectiveness and new characteristics in terms of aerodynamics, avionics, control systems and other systems
- Modernization of the Su-25SM - The main direction of the Su-25SM modernization is to improve the accuracy characteristics and modes of application of ASP
- Su-35S - By order of the Russian Air Force, a program is being implemented to create a deeply modernized super-maneuverable multifunctional 4++ generation fighter
- Sukhoi civil programs - A subsidiary of Sukhoi Company PJSC - Sukhoi Civil Aircraft JSC, in broad international cooperation, is implementing a program to create a family of regional passenger aircraft Sukhoi Superjet 100

Historical reference:

Since 1945, the Design Bureau has been developing and building:

Jet fighters Su-9, Su-11, Su-15, Su-17 (the first with these names);
- Su-10 jet bomber;
- twin-engine piston reconnaissance spotter Su-12.

For the five post-war years, the Design Bureau for the first time in domestic practice created and implemented: a booster aircraft control system;
- brake landing parachute;
- ejection seat with telescopic trolley;
- detachable forward fuselage with pressurized cabin.

E.A. Ivanov In November 1949, by decision of the government, the Design Bureau was liquidated and restored again only in May 1953, but already on a new production base. The "second birth" of the Design Bureau coincided in time with the advent of supersonic jet aviation. Therefore, the main directions in the work of the design team at the initial stage were the supersonic S-1 and T-3 fighters. On the basis of the S-1, a family of Su-7, Su-17 fighter-bombers and more than 20 of their modifications is being created, moreover, the Su-17 became the first aircraft in the USSR with a variable sweep wing. The experimental T-3 served as the basis for the first domestic aviation missile system for intercepting Su-9-51 targets and the Su-11-8M and Su-15-98(M) complexes created later. In the 1960s, the list of equipment developed at the design bureau was expanding. Since 1962, work has been underway to create a long-range strike and reconnaissance complex T-4, the first flight of an experimental vehicle took place on August 22, 1972. For the first time in our country, this aircraft was equipped with an electric remote control system and an autothrottle, and the airframe was made of welded titanium and high-strength steel.

M.P. Simonov To implement the developments in design solutions, the development of new materials and technological processes, an experimental Su-47 aircraft is being created (first flight in 1997).

In the early 90s, the Design Bureau launched work on civilian topics; in 2001, the Su-80GP cargo-passenger aircraft and the Su-38L agricultural aircraft made their first flights.

Currently, JSC "Sukhoi Civil Aircraft" is developing a family of regional aircraft Sukhoi Superjet 100.

Over the years, the team was headed by P.O. Sukhoi, E.A. Ivanov, M.P. Simonov, from 1999 to July 30, 2007, the General Director was M.A. Pogosyan. On July 31, 2007, Igor Yakovlevich Ozar was appointed Executive Director of Sukhoi Design Bureau, who until that time held the positions of Deputy General Director for Economics and Finance - Financial Director of Sukhoi Design Bureau.

On June 30, 2011, the Board of Directors of OAO Sukhoi Company appointed I.Ya. Ozar as General Director of OAO Sukhoi Company.

Since January 1, 2015, Mikhail Yuryevich Strelets has become Deputy General Director - Director of Sukhoi Design Bureau, a branch of OAO Sukhoi Company.

OAO Sukhoi Company completed all stages of reorganization in the form of merger of three subsidiaries - OAO Sukhoi Design Bureau, OAO KnAAPO named after Yu.A. Gagarin and OAO NAPO named after V.P. Chkalov and received a notice of termination from January 1, 2013, the activities of the listed companies as independent legal entities. The structure of a single legal entity now includes, as branches, the Novosibirsk Aviation Plant. V.P. Chkalov, Komsomolsk-on-Amur Aviation Plant. Yu.A. Gagarin, Sukhoi Design Bureau, as well as the company's representative offices in the Republic of India, Vietnam and China.

Other:

PJSC "Company" Sukhoi "is the leading aircraft manufacturing holding in Russia, which produces about a quarter of the products of the Russian aviation industry. The holding is one of the top three world exporters of modern combat fighters.
The history of the Sukhoi Design Bureau dates back to the 1930s, when a design team was formed under the leadership of Pavel Osipovich Sukhoi. In 1939, a bureau was organized in which for 65 years projects of first-class aircraft have been created, bringing world fame to domestic aviation.
The leadership of Sukhoi Company in the field of designing aviation equipment for various purposes has been largely achieved due to many years of experience in conducting research and development work in various areas.
The holding includes leading Russian design bureaus and serial aircraft manufacturing plants. The company provides a full cycle of work in the aircraft industry - from design to effective after-sales service.

Participation in associations

Public Joint Stock Company "United Aircraft Corporation" (PJSC "UAC") was established in accordance with the Decree of the President of the Russian Federation of February 20, 2006 No. 140 "On the Open Joint Stock Company "United Aircraft Corporation". Registration of the Corporation as a legal entity took place on November 20, 2006 The Company was established by the Russian Federation by contributing state-owned stakes in aviation enterprises to its authorized capital (according to Appendix 1 to Decree of the President of the Russian Federation No. 140 of February 20, 2006), as well as by private shareholders of Irkut Corporation OJSC. The priority activities of PJSC "UAC" and the companies that are part of the Corporation are: development, production, sales, operation support, warranty and after-sales service, modernization, repair and disposal of civil and military aviation equipment.

Companies in the group: 19

The non-profit partnership "Union of the Aviation Industry" of Russia (until April 2009 - the International Union of the Aviation Industry) is an industrial association that promotes the development of the aircraft industry, raising the social and legal status of enterprises in the industry, providing legal and methodological assistance, protecting the corporate interests of the aviation industry at all levels of legislative and executive power, as well as in relevant international organizations. SAP was established in 2002 on the initiative of the leading Russian aviation enterprises with the support of Rosaviakosmos and the Interstate Aviation Committee and unites more than 80 leading enterprises in the aircraft manufacturing, engine building, instrument and unit building, repair plants, design bureaus, research institutes, insurance companies and banks, associations, funds, joint stock companies associated with the aviation industry. The enterprises that are members of the Union in 2011 produced more than 70% of the total volume of products of the aircraft industry.

Companies in the group: 60

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In contact with	Facebook

The invention relates to aviation, namely to the air intakes of the power plants of supersonic aircraft. The supersonic adjustable air intake contains an inlet, which is a flow deceleration system - a supersonic diffuser (22), consisting of two multi-stage swept deceleration wedges (7) and (20), forming a dihedral angle, a shell, also forming a dihedral angle, while all the edges of the inlet lie in one plane, the air intake throat located behind the braking system, and behind it a subsonic diffuser (23). When viewed from the front, the air intake inlet has the shape of a rectangle or parallelogram. The number of steps on the swept wedges (7) and (20) may not match, and their sweep may not match between themselves and the corresponding entrance edges. All steps, except for the first one, one of the two multi-stage arrow-shaped wedges (7) and (20) are rotatable around an axis located at the intersection of the first and second steps of the mentioned wedge, with the formation of a movable front panel (11). A movable rear panel (12) is located in the subsonic diffuser. Provides stable operation of the engine in all flight modes up to the Mach number M=3.0. 7 w.p. f-ly, 5 ill.

Drawings to the RF patent 2472956

SUBSTANCE: invention relates to aircraft engineering, namely to air intakes of power plants of supersonic aircraft. The preferred field of application of the invention are aircraft with turbofan engines with a maximum Mach number of not more than 3.

Creation of inconspicuous in the radar range aircraft(LA) implies that the shape of all its elements helps to reduce the level of the effective scattering area (ESR) of the aircraft. This also applies to the shape of the engine air intake inlet. To achieve the desired result, all edges of the air intake must be swept and parallel to any elements of the aircraft (wing edges, plumage, etc.). The creation of such a supersonic air intake for the Mach number M>2.0, which has high internal characteristics, is a non-trivial task.

Known supersonic adjustable flat (two-dimensional) air intake, flow braking which is carried out on an adjustable multi-stage straight wedge in a series of oblique shock waves. To improve the characteristics of the air intake, perforation can be performed on the wedge, and in the throat area - a transverse slit to drain the boundary layer (Remeev N.Kh. Aerodynamics of air intakes of supersonic aircraft. Published by TsAGI, Zhukovsky, 2002, 178 p.).

The analogues include the supersonic air intake of the F-22 aircraft, in which the spatial compression scheme of the supersonic flow is implemented (Aerodynamics, stability and controllability of supersonic aircraft, edited by G.S. Byushgens. - M .: Nauka. Fizmatlit, 1998). To reduce the radar visibility of the F-22 aircraft, the air intake is made to sweep all the edges of the entrance. In front view, the inlet to the air intake has the shape of a parallelogram. The air intake has one braking stage each on perforated vertical and horizontal wedges, air bypass flaps in the channel. The air intake duct is S-shaped. There is no possibility of regulating the area of the minimum flow section (throat). The disadvantages include the lack of regulation of the throat of the air intake of the F-22 aircraft. For this reason, its characteristics in supersonic flight conditions are below the level characteristic of adjustable air intakes ( System analysis technical appearance of the aircraft F / A-22 "Raptor", report of the Federal State Unitary Enterprise "GosNIIAS" No. 68 (15396), 2005). Apparently, the air intake is not designed for flight with a Mach number of more than M=2.0 (Aerodynamics, stability and controllability of supersonic aircraft, edited by G.S. Byushgens. - M.: Nauka. Fizmatlit, 1998).

As a prototype of the invention, an air intake is adopted, containing an entrance to the air intake, which is a flow deceleration system - a supersonic diffuser, consisting of two multi-stage swept deceleration wedges forming a dihedral angle, a shell, also forming a dihedral angle, while all the edges of the entrance lie in the same plane, air intake throat located behind the braking system, and behind it - a subsonic diffuser (RU 2343297 C1). The prototype implements spatial flow deceleration through the use of a V-shaped wedge (i.e., two adjoining swept wedges oriented towards each other in front view at an obtuse angle) and control of the throat area using two pairs of adjustable panels. The air intake is made to sweep all the edges of the entrance. When adjusting each pair of panels, transverse slots appear between their adjacent end sides, and longitudinal slots appear between their sides both at the joints with the side walls and at the joints with each other. The slots serve to reduce the adverse effect of the boundary layer on the characteristics of the air intake, incl. boundary layer growing along the dihedral angle. This technical solution has the following disadvantages:

The air intake control does not provide the required throat area at subsonic and low supersonic flight speeds, because the amplitude of movement of the movable panels is small. Otherwise, the mentioned cracks of unacceptable sizes appear. This means that the air intake does not ensure the operation of the turbofan engine in the entire operational speed range and is not multi-mode,

Technically complex implementation of air intake control.

The technical result, to which the invention is directed, is to ensure, by adjusting the opening angle of the steps of one of the swept wedges and the minimum area of the flow section of the air intake, stable operation of the engine in all flight modes up to the Mach number M = 3.0 with a recovery factor of the total pressure at the inlet to the the engine at a level not lower than typical for adjustable flat air intakes and the total flow heterogeneity is below the maximum allowable value (Aerodynamics, stability and controllability of supersonic aircraft, edited by G.S. Byushgens. - M .: Nauka. Fizmatlit, 1998). At the same time, due to the parallelogram shape of the air intake inlet in the front view and giving all its edges a sweep, a decrease in the radar visibility of the object on which it is installed should be achieved. The greatest effect of reducing radar visibility will be achieved when the edges of the air intake are parallel to some elements of the object (leading or trailing edges of the wing, plumage, etc.).

The specified technical result is achieved by the fact that in the supersonic adjustable air intake, which contains the entrance to the air intake, which is a flow deceleration system - a supersonic diffuser, consisting of two multistage arrow-shaped deceleration wedges, forming a dihedral angle, a shell, also forming a dihedral angle, while all the edges of the inlet lie in the same plane, the air intake throat, located behind the braking system, and behind it is a subsonic diffuser, when viewed from the front, the air intake inlet has the shape of a rectangle or parallelogram with an arbitrary ratio of its height and the length of the corresponding side, the number of steps on swept wedges may not match, but also, their sweep between themselves and the corresponding edges of the entrance may not coincide, all steps, except for the first one, one of the two multi-stage swept wedges are made with the possibility of rotation around an axis located at the intersection of the first and second steps of the mentioned wedge, with the formation of a movable front panel, with At the same time, a reciprocal movable rear panel is located in the subsonic diffuser, which is part of the subsonic diffuser, and is made with the possibility of rotation around an axis located in the area of the rear end of this panel, and when the front and rear panels are synchronously rotated, a transverse slot is formed between them, the shape of which is close to rectangular .

Behind the oblique shocks from the stagnation wedges, air can be passed into the external flow in the region of the dihedral angle formed by the shell.

On a fixed swept wedge in the throat area, it is possible to place an additional transverse slot closed by a rotary shutter.

When viewed from the front, it is possible to round or trim the corners of the air intake inlet, except for the angle formed by the swept wedges.

In the subsonic diffuser, there may be holes closed by make-up shutters.

A cutout can be made in the edge of the air intake inlet in the area of the dihedral angle formed by the shell.

Holes of arbitrary shape can be made in the shell. The brake wedges can be perforated.

The invention is illustrated by drawings, where figure 1 shows a supersonic adjustable air intake when viewed from below; figure 2 - supersonic adjustable air intake - side view; figure 3 - supersonic adjustable air intake - front view; figure 4 - section A-A figure 1; figure 5 - diagram of the deceleration of the flow in the supersonic adjustable air intake in the design flight mode.

Supersonic adjustable air intake contains the following elements:

1 - the edge of the braking wedge containing the front adjustable panel,

2 - edge of the fixed braking wedge,

3, 4 - edges of the shell,

5 - air intake channel,

6 - cylindrical section,

7 - braking wedge containing the front adjustable panel,

8 - air supply flaps,

9 - axis of rotation of the front adjustable panel 11,

10 - axis of rotation of the rear adjustable panel 12,

11 - front adjustable panel in the maximum throat position (the position of the minimum throat is shown by a dotted line),

12 - rear adjustable panel in the maximum throat position (the position of the minimum throat is shown by a dotted line),

13 - transverse slot between the front and rear adjustable panels for draining the boundary layer,

14 - break line between the first and second stages of the braking wedge 7 containing the front adjustable panel,

15 - break line between the first and second stages of the fixed braking wedge,

16 - break line between the second and third stages of the braking wedge 7 containing the front adjustable panel,

17 - trimming the dihedral angle formed by the shell,

18 - rounding of the entrance at the junction of the braking wedge 7, containing the front adjustable panel, and the shell,

19 - trimming the dihedral angle formed by the fixed braking wedge 20 and the shell,

20 - fixed braking wedge 20,

21 - leaf regulating additional transverse slot in the throat area on the fixed braking wedge 20,

22 - supersonic diffuser (braking system),

23 - subsonic diffuser,

24 - oblique shock wave from the first stages of swept wedges 7 and 20,

25 - oblique shock wave from the second stages of swept wedges 7 and 20,

26 - oblique shock wave from the third stages of swept wedges 7 and 20,

27 - closing direct shock wave,

28 - bypass area behind oblique and direct shock waves to increase the range of air flow through the air intake, in which its stable operation is ensured.

The shape of the air intake inlet when viewed from the front is a parallelogram or its special case - a rectangle with an arbitrary ratio of its height and the length of the corresponding side. At the air intake inlet, it is possible to have undercuts 17 and 19 or rounding of corners 18, except for the angle formed by swept wedges 7 and 20. The edges of the air intake inlet lie in a plane oriented to the flow direction at an acute angle. Thus, all entry edges are swept.

The supersonic diffuser 22 is a flow deceleration system consisting of a pair of swept wedges 7 and 20 forming a dihedral angle and shells (3, 4 - shell edges). Swept wedges 7 and 20 have at least one step, while the number of steps on these wedges may not match. As an example, in Fig.1, 2, 3, 4 shows an air intake, which has three steps on one swept wedge, and two on the second. The fractures of the respective steps of the swept wedges 14, 15, 16 intersect at a point lying on the line of intersection of the surfaces of the respective steps of the wedges 7 and 20, forming a dihedral angle. The sweep angles of the steps on each of the swept wedges 7 and 20 may differ from the sweep angle of the edge of the corresponding wedge, as well as between each other. The opening angles of the steps of the swept wedges 7 and 20 are determined when constructing the braking system from the condition of creating a single oblique shock of a given intensity from each pair of the corresponding steps of the wedges, i.e. the principles of gas-dynamic design are used (Schepanovsky V.A., Gutov B.I. Gas-dynamic design of supersonic air intakes. Nauka, Novosibirsk, 1993). The shell, as well as swept wedges 7 and 20, forms a dihedral angle. characteristic feature is such an orientation of the shell at which it additionally slows down the flow, i.e. the shell is not oriented along the streamlines behind the shock waves from swept wedges 7 and 20. The shell undercut angle can be variable. In the area of the dihedral angle formed by the shell, it is possible to organize a cutout in the edge of the air intake inlet, and holes of arbitrary shape can be placed in the shell itself.

The front adjustable panel 11 contains the steps of one of the swept wedges, except for the first one, and rotates about the axis 9, located at the intersection of the first and second stages of the wedge 7. The rear adjustable panel 12 is part of the subsonic diffuser 23 and rotates around the spatially located axis 10. The axis passes above the back of the panel.

When adjusting the air intake, the front 11 and rear 12 adjustable panels, rotating, simultaneously change their position in accordance with a given law, while changing the throat area of the air intake, the opening angle of the moving steps of the swept wedge 7, and it is also possible to form a transverse slot 13 to drain the boundary layer between front and back adjustable panels. The axis of rotation 10 of the rear adjustable panel 12 is oriented in such a way that when the panels are adjusted, said transverse slot 13 has a shape close to rectangular. On a fixed swept wedge 20 in the throat area, it is possible to place an additional transverse slot for draining the boundary layer, closed by a flap 21. On some steps of the swept wedges 7 and 20, perforation can be made to suck the boundary layer accumulating on these steps in order to prevent it from entering the engine .

Said slots and perforations improve the air intake performance at supersonic speeds by preventing the highly turbulent boundary layer from entering the engine.

In the subsonic diffuser 23, it is possible to have air supply flaps 8, which provide access to the external air flow flowing around the air intake into the subsonic diffuser. The make-up flaps 8 help to improve the characteristics of the air intake at low speeds (take-off modes and flight modes at high angles of attack).

The inventive supersonic adjustable air intake operates as follows.

At subsonic flight speeds, the adjustable air intake panels are in the retracted positions 11 and 12, providing a throat area at which no supersonic flow velocities are present in channel 5.

At supersonic flight speeds, efficiency power plant of the aircraft is related to the effectiveness of the flow braking in the air intake.

The deceleration of the supersonic flow in the air intake of the scheme under consideration occurs in the shock waves 24, 25, 26 that occur when the swept wedges 7 and 20 of the braking system are flowed around.

As the flight speed increases to supersonic, the adjustable panels (front 11 and rear 12) synchronously deviate from the position corresponding to subsonic flight. With the deflection of the front panel 11, the opening angles of the steps of the wedge 7 increase, which leads to an increase in the intensity of flow deceleration in the shock waves from these steps. When the rear panel 12 is deflected, the area of the throat is reduced. An increase in the intensity of flow deceleration and a decrease in the throat area have a positive effect on the characteristics of the air intake.

Upon reaching the calculated (usually maximum) flight speed in the supersonic diffuser 22, the calculated flow pattern (Fig. 5) is implemented, in which spatial shock waves 24, 25, 26 arise from each pair of corresponding stages of the wedges 7 and 20, which form a dihedral angle. deceleration - supersonic diffuser 22, corresponding to the calculated configuration, is designed using the principles of gas-dynamic design (Schepanovsky V.A., Gutov B.I. Gas-dynamic design of supersonic air intakes. Nauka, Novosibirsk, 1993).

At flight speeds less than the calculated one in the air intake deceleration system, the flow pattern differs from the calculated one.

The flow is decelerated to subsonic speed in the direct closing shock wave 27, which should be located at the inlet to the air intake behind oblique shock waves. Finally, the subsonic flow is decelerated in the subsonic diffuser 23 and consumed by the engine.

Stable operation of the air intake in all modes of flight and engine operation is ensured by the presence of air bypass in oblique shock waves 28, a boundary layer drain system in the form of perforation on the steps of wedges 7 and 20 of the braking system and a transverse slot 13 between the front 11 and rear 12 adjustable panels. Drainage of the boundary layer is additionally possible through an additional transverse slot, adjustable by flap 21 and located in the throat area behind a fixed braking wedge 20 containing unregulated steps.

The boundary layer drain system also contributes to improved air intake performance.

To increase the range of stable operation of the air intake when the air flow through it changes, a cutout can be additionally implemented in the air intake inlet edge in the area of the dihedral angle formed by the shell, and (or) holes in the shell of arbitrary shape.

Experimental and computational studies of the characteristics of an air intake of this type on various modes work and speeds of the oncoming flow showed the effectiveness of the proposed design solutions and the fulfillment of the requirements for air intakes.

Providing high internal gas-dynamic characteristics, the configuration of the air intake at the same time helps to reduce the radar visibility of the object on which it is installed. This effect is achieved due to the parallelogram shape of the air intake inlet in the front view and the presence of a sweep of all the edges of the inlet. The orientation of the mentioned elements is performed in such a way that the number of directions in which the radar signal is reflected from the object is minimal.

CLAIM

1. Supersonic adjustable air intake, containing an entrance to the air intake, which is a flow deceleration system - a supersonic diffuser, consisting of two multi-stage swept deceleration wedges forming a dihedral angle, a shell, also forming a dihedral angle, while all the edges of the inlet lie in the same plane, the throat air intake located behind the braking system, and behind it - a subsonic diffuser, characterized in that, when viewed from the front, the air intake inlet has the shape of a rectangle or parallelogram with an arbitrary ratio of its height and length of the corresponding side, the number of steps on swept wedges may not match, and may also do not coincide with their sweep between themselves and the corresponding edges of the input, all steps, except for the first, one of the two multi-stage swept wedges are made with the possibility of rotation around an axis located at the intersection of the first and second steps of the said wedge, with the formation of a movable front panel, while in In the subsonic diffuser, there is a reciprocal movable rear panel, which is part of the subsonic diffuser and is made with the possibility of rotation around an axis located in the area of the rear end of this panel, and with the synchronous rotation of the front and rear panels, a transverse slot is formed between them, the shape of which is close to rectangular.

2. The air intake according to claim 1, characterized in that behind the oblique shock waves from the braking wedges, air is bypassed into the external flow in the region of the dihedral angle formed by the shell.

3. The air intake according to claim 1, characterized in that an additional transverse slot is placed on the fixed swept wedge in the throat area, which is closed by a rotary flap.

4. The air intake according to claim 1, characterized in that, when viewed from the front, the corners of the air intake inlet are rounded or trimmed except for the angle formed by swept wedges.

5. The air intake according to claim 1, characterized in that holes are made in the subsonic diffuser, which are closed by the make-up flaps.

6. The air intake according to claim 1, characterized in that a cutout is made in the edge of the air intake inlet in the area of the dihedral angle formed by the shell.

7. The air intake according to claim 1, characterized in that holes of arbitrary shape are made in the shell.

8. The air intake according to claim 1, characterized in that the braking wedges are perforated.