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Rockwell - MBB X-31

rock-mbb-x31


The X-31 began as an Enhanced Fighter Manoeuvrability (EFM) demonstrator at NASA's Dryden Flight Research Center at Edwards AFB. Designed to break the “stall barrier,” allowing it to flight at angles of attack which would typically cause an aircraft to stall with a complete loss of control, the X-31 employs thrust vectoring paddles that are located in the jet exhaust and small computer-controlled canards to help keep the aircraft stable at high attack angles. It incorporates an unusual delta wing design and three thrust-vectoring paddles made of graphite epoxy and located on the aircraft's aft fuselage. These direct the engine exhaust to provide control in pitch (up and down) and yaw (right and left) thereby increasing the aircraft's manoeuvrability. In addition, the X-31 is configured with movable forward canards, wing control surfaces and fixed aft strakes. Coupled with advanced flight control systems, the result confers a significant advantage over conventional fighters in a close-in-combat situation.

The X-31 is the first co-operative international X-plane. At Dryden, the International Test Organization (ITO) expanded the flight test envelope. The ITO, managed by the Advanced Research Project Agency (ARPA), includes NASA, the US Navy, the US Air Force, Rockwell Aerospace, the Federal Republic of Germany and Deutsche Aerospace, formerly Messerschmitt-Bolkow-Blohm.

To reduce costs, several parts of existing aircraft were used in the X-31. Canopy, ejection seat and control stick were taken from an F/A-18 while several parts of the landing gear and rudder are from an F-16. Brakes and wheels were provided by Cessna and are the same as those used on the Cessna Citation. Piloted by Rockwell chief test pilot Ken Dyson, the first aircraft, serial 164584, flew from Air Force Plant 42, Palmdale, Calif, on October 11, 1990. The second aircraft, 164585, made its first flight on January 19, 1991, with Deutsche Aerospace chief test pilot Dietrich Seeck at the controls. Powered by a single General Electric P404-GE-400 turbofan engine, known to be tolerant in disturbed air and capable to produce 16,000 lb of thrust with afterburner, the maximum speed achieved by the X-31 is Mach 1.28. Controlled flight at 70 degrees angle of attack was accomplished at Dryden on November 6, 1992. On April 29, 1993, the X-31 successfully executed a rapid minimum radius, 180o turn using a post-stall manoeuvre, flying well beyond the aerody-namic limits of any conventional aircraft. Later that summer, the first simulated dog-fights were performed against a NASA F/A-18 Hornet. This resulted in 63 victories for the X-31.

The first X-31 was lost in an accident on January 19, 1995, on its 292nd flight. Due to miscommunication between pilot and air traffic control and a missing pitot tube heating system the German pilot, Karl-Heinz Lang, had to eject from his uncontrollable aircraft at 18,000ft. The aircraft crashed near Edwards AFB.

The second X-31 completed the 580th and last flight of its original research program on 13 May 1995 and was placed in storage.

In February 1998, the participating contractors started VECTOR Risk Reduction and Requirements Definition. The aircraft was shipped to NAS Patuxent River in April 2000, where it was largely rebuilt for the Vector (Vectoring Extremely Short Take-Off and Landing Control Tailless Operation Research) program.

VECTOR stands for Vectoring Extremely Short Take-Off and Landing Control and Tailless Operational Research and is being used to research extremely short take-off and landing capabilities and also the aerodynamic characteristics of tailless flight using integrated thrust vector control. Three technology areas are involved:
- Extremely Short Take-Off and Landing (ESTOL) using thrust vectoring control
- Flush Air Data System (FADS)
- Tailless/reduced vertical tail configurations

This incorporated a new flight control software system was installed together with an auto-throttle system, a belly-mounted video camera and components of inertial navigation and global positioning systems. The revised aircraft made its first flight for Vector on 24 February 2001. After two months of basic flight testing, the aircraft began a year of upgrading and ground testing to perform ESTOL landings to a “virtual runway” at 5,000 feet. The X-31 took to the air again on 17 May 2002.

 

 

 

In these flights the aircraft flew thrust vectored, high precision ESTOL landings at reduced speeds and at high angles of attack.

To perform the automated approach, the pilot must fly into an invisible engagement box in the sky, then activate the ESTOL mode. Once successfully engaged, the pilot is not in control but is able to override the approach at any point. A video camera under the belly of the aircraft will allow the pilot to view the runway prior to landing because a pilot loses sight at anything above 15 degrees angle of attack, so during final approach the aircraft will be controlled by autopilot. Coming in with its nose pointed high above the horizon, the first part of the aircraft to touch the runway would be the engine nozzle and not the landing gear. To prevent such an event, the X-31 performs [an automatic] derotation manoeuvre when the tail is just two feet above the runway, dropping onto its main landing gear. Timing of this manoeuvre is crucial; if the aircraft derotates early and drops too far, the landing gear could fail; if the aircraft derotates too late or too low, the tail could strike the runway. The aircraft is guided during approach by an Integrity Beacon Landing System (IBLS) which uses differential GPS data together with ground-based beacons to determine the aircraft's position ensuring accurate positioning within two centimetres.

After 51 flights, the X-31 completed its first test phase on March 22, 2003, with two supersonic flights focussing on FADS performance. Pilot Knoptel reached speeds of Mach 1.06 and 1.18, in full afterburner at 39,000ft. While supersonic, he induced combinations of angle of attack and sideslip to tax the FADS. By night, engineers had processed the data and were able to confirm that the FADS was performing as desired throughout the flight regime.

This cleared the way for the final phase of flight tests that began in early April 2003 and ended on April 29 when the last ESTOL landing was performed by Maj Allee following a week of successful testing the world's first fully automated, thrust vectoring landings. This landing was performed with an angle of attack of 24 degrees and a speed of 121kt, a reduction of 31% compared with the normal landing speed of 175kt. The X-31 requires a normal runway length of 8,000ft to stop after a conventional landing, but after the final ESTOL landing, the aircraft needed just 1,700ft to slow down enough to turn around on the runway.

Sponsors: DARPA, USN, German MoD
Fastest Flight: Mach 1.28 (900 mph)
Highest Flight: 40,000 feet (approx)

X-31
Powerplant: One General Electric P404-GE-400 turbofan, 16,0001b thrust with afterburner
Span; 23,83ft (7.3m)
Length, 43.33ft (12.8m)
Take-off weight, 16,1001b (7,303kg)
Max achieved speed, Mach 1,28 at 35,000ft
Max achieved altitude, 40,000ft (12,200m)

X-31A
Powerplant: one 10,600-lb (4808-kg) thrust General Electric F404-GE-400 non-afterburning turbofan
Wingspan 23 ft 10 in (7.26 m)
Length 43 ft 4 in (13.21 m) excluding probe
Height 14 ft 7 in (4.44 m)
Wing area 226.3 sq ft (21.02 sq.m)
Canard foreplane area 23.6 sq ft (2.19 sq.m)
Maximum speed 597 mph (961 km/h) or Mach 0.9 at 35,000 ft (10,670 m)
Empty weight 10,212 lb (4632 kg)
Maximum take-off 13,968 lb (6335 kg)
Crew: 1

 

 


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