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Minggu, 23 Oktober 2011

Sukhoi Su-47

Sukhoi Su-47

Su-47 Berkut
Role Technology demonstrator
Manufacturer Sukhoi
First flight 25 September 1997
Introduction January 2000
Status Under development
Primary user Russian Air Force
Number built 4 flight testing prototypes
The Sukhoi Su-47 Berkut (Russian: Су-47 Беркут - Golden Eagle) (NATO reporting name Firkin), also designated S-32 and S-37 (not to be confused with the twin-engined delta canard design[1] offered by Sukhoi in the early 1990s under the designation Su-37) during initial development, was an experimental supersonic jet fighter developed by Sukhoi Aviation Corporation. A distinguishing feature of the aircraft was its forward-swept wing[2] that gave the aircraft excellent agility and maneuverability. While serial production of the type never materialized, the sole aircraft produced served as a technology demonstrator prototype for a number of advanced techhnologies later used in the 4.5 generation fighter SU-35BM and current 5th generation fighter prototype Sukhoi PAK FA.

Development

Originally known as the S-37, Sukhoi redesignated its advanced test aircraft as the Su-47 in 2002. Officially nicknamed Berkut (Golden Eagle), the Su-47 was originally built as Russia's principal testbed for composite materials and sophisticated fly-by-wire control systems.
TsAGI has long been aware of the advantages of forward-swept wings, with research including the development of the Tsibin LL and study of the captured Junkers Ju 287 in the 1940s. Forward-swept wings yield a higher maximum lift coefficient, reduced bending moments, and delayed stall when compared to more traditional wing shapes. At high angles of attack, the wing tips remain unstalled allowing the aircraft to retain aileron control. Conversely, forward sweep geometrically creates increased angle of incidence of the outer wing sections when the wing bends under load. This creates more lift, more load, more angle of incidence, etc. This leads to a tendency for the wings to fail structurally at lower speeds than for a straight or aft-swept wing. Forward swept wings counter this by being designed to twist downward as they bend upward. This twisting-as-it-bends is done with composite materials on the S-37, but it can also be done, to an extent, with conventional materials.
The project was launched in 1983 on order from the Soviet Air Force. But when the USSR dissolved, funding was frozen and development continued only through funding by Sukhoi. Like its US counterpart, the Grumman X-29, the Su-47 was primarily a technology demonstrator for future Russian fighters; however, Sukhoi briefly attempted to market the Su-47 to the Russian military and foreign customers as a production fighter in its own right.[citation needed]

Design

Outline of the Sukhoi Su-47
The Su-47 is of similar dimensions to previous large Sukhoi fighters, such as the Su-35. To reduce development costs, the Su-47 borrowed the forward fuselage, vertical tails, and landing gear of the Su-27 family. Nonetheless, the aircraft includes reduced radar signature features,[citation needed] an internal weapons bay, and space set aside for an advanced radar. Though similar in overall concept to the Grumman X-29 research aircraft of the 1980s, the Su-47 is larger and far closer to an actual combat aircraft than the US design.
To solve the problem of wing-twisting, the Su-47 makes use of composite materials carefully-tailored to resist twisting while still allowing the wing to bend for improved aerodynamic behavior. Due to its comparatively large wingspan the Su-47 is to be equipped with folding wings in order to fit inside Russian hangars.
Like its immediate predecessor, the Su-37, the Su-47 is of tandem-triple layout, with canards ahead of wings and tailplanes. Interestingly, the Su-47 has two tailbooms of unequal length outboard of the exhaust nozzles. The shorter boom, on the left-hand side, houses rear-facing radar, while the longer boom houses a brake parachute.

Maneuverability

The Su-47 has extremely high agility at subsonic speeds, enabling the aircraft to alter its angle of attack and its flight path very quickly while retaining maneuverability in supersonic flight. The Su-47 has a maximum speed of Mach 1.6 at high altitudes and a 9g capability.[3]
Maximum turn rates, and the upper and lower limits on airspeed for weapon launch, are important criteria in terms of combat superiority. The Su-47 aircraft has very high levels of maneuverability with maintained stability and controllability at extreme angles of attack. Maximum turn rates are important in close combat and also at medium and long range, when the mission may involve engaging consecutive targets in different sectors of the airspace. A high turn rate of the Su-47 allows the pilot to turn the fighter aircraft quickly towards the next target to initiate the weapon launch. Like most other fighters with fly by wire controls, the Su-47 achieves some of its high maneuverability through relaxed stability[citation needed].
The swept-forward wing, compared to a swept-back wing of the same area, provides a number of advantages:
  • higher lift-to-drag ratio
  • higher capacity in dogfight maneuvers
  • higher range at subsonic speed
  • improved stall resistance and anti-spin characteristics
  • improved stability at high angles of attack
  • a lower minimum flight speed
  • a shorter take-off and landing distance

Fuselage

The Su-47s fuselage is oval in cross section and the airframe is constructed mainly of aluminium and titanium alloys and 13% (by weight) of composite materials. The nose radome is slightly flattened at the fore section, and has a horizontal edge to optimise the aircraft's anti-spin characteristics.

Wings

The forward-swept midwing gives the unconventional appearance of the Su-47. A substantial part of the lift generated by the forward-swept wing occurs at the inner portion of the wingspan. The lift is not restricted by wingtip stall. The ailerons - the wing's control surfaces - remain effective at the highest angles of attack, and controllability of the aircraft is retained even in the event of airflow separating from the remainder of the wings' surface.
The wing panels are constructed of nearly 90% composites. The forward-swept midwing has a high aspect ratio, which contributes to long-range performance. The leading-edge root extensions blend smoothly to the wing panels, which are fitted with deflectable slats on the leading edge; flaps and ailerons on the trailing edge. The all-moving and small-area trapezoidal canards are connected to the leading-edge root extensions.
A downside of such a forward-swept wing design is that it geometrically produces wing twisting as it bends under load, resulting in greater stress on the wing than for a similar straight or aft-swept wing. This requires the wing be designed to twist as it bends - opposite to the geometric twisting. This is done by the use of composites wing skins laid-up to twist. Despite this, the plane was initially limited to Mach 1.6. Recent engineering modifications have raised this limit, but the new limit has not been specified.

Thrust vectoring

The thrust vectoring (with PFU engine modification) of ±20° at 30°/second in pitch and yaw will greatly support the agility gained by other aspects of the design.

Cockpit

The cockpit's design has focused on maintaining a high degree of comfort for the pilot and also on the pilot being able to control the aircraft in extremely high g-load maneuvers. The aircraft is equipped with a new ejection seat and life support system. The variable geometry adaptive ejection seat is inclined at an angle of 60°, which reduces the impact of high g forces on the pilot. The seat allows dogfight and missile avoidance maneuvers with significantly higher g loadings than can normally be tolerable. The Su-47 pilot uses a side-mounted, low-travel control stick and a tensiometric throttle control. Pilots, however, claim that the cockpit gives them low visibility due to poor design.[citation needed] This reclined seating arrangement was first used in the American F-16.[citation needed]

Specifications (Su-47)

Data from World Aircraft & Systems Directory
General characteristics
  • Crew: 1
  • Length: 22.6 m (74 ft 2 in)
  • Wingspan: 15.16 m to 16.7 m (49 ft 9 in to 54 ft 9 in)
  • Height: 6.3 m (20 ft 8 in)
  • Wing area: 61.87 m² (666 ft²)
  • Empty weight: 16,375 kg (36,100 lbs)
  • Loaded weight: 25,000 kg (55,115 lb)
  • Max takeoff weight: 35,000 kg (77,162 lbs)
  • Powerplant: 2 × Lyulka AL-37FU(planned) prototypes used 2 Aviadvigatel D-30F6 afterburning, thrust-vectoring (in PFU modification) turbofans
    • Dry thrust: 83.4 kN (18,700 lbf) each
    • Thrust with afterburner: 142.2 kN (32,000 lbf) each
  • Thrust vectoring: ±20° at 30° per second in pitch and yaw
Performance

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