|The X-31 aircraft returns from a test flight for VECTOR.|
|National origin||United States / Germany|
|Manufacturer||Rockwell / Messerschmitt-Bölkow-Blohm|
|First flight||11 October 1990|
The Rockwell-Messerschmitt-Bölkow-Blohm X-31 Enhanced Fighter Maneuverability program was designed to test fighter thrust vectoring technology. Thrust vectoring provides additional control authority in pitch and yaw, resulting in significantly more maneuverability than most conventional fighters. An advanced flight control system provides controlled flight at high angles of attack where conventional aircraft would stall or lose control.
Design and development
Two X-31s were built, with the first flying on October 11, 1990. Over 500 test flights were carried out between 1990 and 1995. The X-31 is an early canard delta, a delta wing aircraft which uses canard foreplanes for primary pitch control, with secondary thrust-vectoring control. The canard delta has since become common on fighters such as the Eurofighter Typhoon, Dassault Rafale and Saab Viggen and Gripen. It featured a cranked-delta wing (similar to the Saab J35 Draken and F-16XL prototype), and fixed strakes along the aft fuselage, as well as a pair of movable computer-controlled canards to increase stability and maneuverability. There are no moveable horizontal tail surfaces, only the vertical fin with rudder. Pitch and yaw are controlled by the canard with the aid of the three paddles directing the exhaust (thrust vectoring). Eventually, simulation tests on one of the X-31s showed that flight would have been stable had the plane been designed without the vertical fin, because the thrust-vectoring nozzle provided sufficient yaw and pitch control.
During flight testing, the X-31 aircraft established several milestones. On November 6, 1992, the X-31 achieved controlled flight at a 70° angle of attack. On April 29, 1993, the second X-31 successfully executed a rapid minimum-radius, 180° turn using a post-stall maneuver, flying well outside the range of angle of attack normal for conventional aircraft. This maneuver has been called the "Herbst maneuver" after Dr. Wolfgang Herbst, an MBB employee and proponent of using post-stall flight in air-to-air combat. Herbst was the designer of the Rockwell SNAKE, which formed the basis for the X-31.
In the mid-1990s, the program began to revitalize and a $53 million VECTOR program was initiated capitalizing on this previous investment. VECTOR is a joint venture that includes the US Navy, Germany’s defense procurement agency BWB, Boeing's Phantom Works, and the European Aeronautic, Defense and Space Company in Ottobrunn, Germany. As the site for the flight testing, Naval Air Station Patuxent River in Maryland was chosen. From 2002 to 2003, the X-31 flew extremely short takeoff and landing approaches first on a virtual runway at 5,000 feet in the sky, to ensure that the Inertial Navigation System/Global Positioning System accurately guides the aircraft with the centimeter accuracy required for on the ground landings. The program then culminated in the first ever autonomous landing of a manned aircraft with high angle of attack (24 degree) and short landing. The technologies involved a differential GPS System based on pseudolite technology from Integrinautics and a miniaturized flush air data system from Nordmicro.
- BuNo 164584, 292 flights – crashed on January 19, 1995, north of Edwards AFB, California. The crash was caused by ice inside the pitot tube, sending incorrect airspeed data to the flight control computers. Contributing factors included the replacement of a heated pitot tube with an unheated Kiel probe, and ground crew/pilot ignorance of an option to override computer control. The pilot ejected safely.
- BuNo 164585, 288 flights, the last one being in 2003. Put on Permanent Display at Deutsches Museum Flugwerft Schleissheim in Germany.
Data from Jane's All The World's Aircraft 1993–94
- Crew: 1
- Length: 43ft 4 in (13.21m)
- Wingspan: 23 ft 10 in (7.26 m)
- Height: 14 ft 7in (4.44m)
- Wing area: 226.3 sq ft (21.02 m²)
- Aspect ratio: 2.51:1
- Empty weight: 11,410 lb (5,175 kg)
- Loaded weight: 14,600 lb (6,622 kg)
- Max. takeoff weight: 15,935 lb (7,228 kg)
- Powerplant: 1 × General Electric F404-GE-400 turbofan, 16,000 lbf (71 kN)afterburning
- Maximum speed: Mach 1.28 (900 mph, 783 knots, 1,449 km/h)
- Service ceiling: 40,000 ft (12,200 m)
- Rate of climb: 43,000 ft/min (218 m/s)
- Wing loading: 64.5 lb/ft² (315 kg/m²)
- Aircraft of comparable role, configuration and era
- Related lists
- Dorr 1996, p.42.
- Smith, R. E.; Dike, B. A.; Ravichandran, B.; El-Fallah, A.; Mehra, R. K. (2001). "Discovering Novel Fighter Combat Maneuvers in Simulation: Simulating Test Pilot Creativity" (PDF). United States Air Force. Retrieved 2007-01-16.
- "Partners in Freedom: Rockwell-MBB X-31." Langevin, G. S.; Overbey, P. NASA Langley Research Center. October 17, 2003.
- "The Crash of the X-31A". Retrieved 21 November 2008.
- Destroyed in Seconds, Discovery Channel, aired: 19 December 2008, 1:30 A.M. EST
- "Loss of the X-31A". Retrieved 10 August 2009.
- Lambert 1993, pp. 176–77.
- Jenkins, Landis and Miller 2003, p. 39.
- Dorr, Robert F. (1996). "Rockwell/MBB X-31". World Air Power Journal (London: Aerospace Publishing) (Volume 24 Spring 1996): pp. 34–47. ISBN 1-874023-66-2. ISSN 0959-7050.
- Jenkins, Dennis R., Tony Landis, and Jay Miller. SP-2003-4531, "American X-Vehicles, An Inventory—X-1 to X-50". NASA, June 2003.
- Lambert, Mark (1993). Jane's All The Worlds Aircraft 1993-94. Coudsdon, UK: Janes's Data Division. ISBN 0-7106-1066-1.
- USAF & NATO Report RTO-TR-015 AC/323/(HFM-015)/TP-1 (2001)
|Wikimedia Commons has media related to Rockwell-MBB X-31.|
- NASA Dryden: X-31
- James Schombert's X-Plane history
- NASA X-31 image gallery
- Flap Splitting and Setting of the X-31 Wing