Lockheed U-2
1955
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Lockheed U-2

Development of the U-2 began in the spring of 1954 to meet a joint CIA/USAF requirement for a high-altitude strategic reconnaissance and special-purpose research aircraft. It took place in the Lockheed 'Skunk Works' at Burbank, California, where - after acceptance of the design in late 1954 - two prototypes were hand-built in great secrecy by a small team of engineers. The aircraft's true purpose was cloaked under the USAF U-for-Utility designation U-2, and the first flight took place on or about 1 August 1955.

At about the same time US President Dwight D. Eisenhower was proposing his 'Open Skies' policy, one of mutual East/West aerial reconnaissance of territories. President Eisenhower hoped that his policy would reduce tension between East and West, thus preventing the growth of the nuclear arms race. Unfortunately the Soviet Union would have nothing to do with this proposal. Consequently 'Kelly' Johnson's new 'spy plane' assumed greater importance. The prototypes were followed by production of about 48 single-seat U-2A and U-2B with differing power plant, and five two-seat U-2D. Some U-2B were converted later to U-2D standard. An additional batch of 12 U-2R was ordered in 1967. A new version, known as the TR-1, is currently in production as a tactical-reconnaissance aircraft, equipped with a variety of electronic sensors.

The requirement for high altitude and long range posed enormous problems: the former needed an aircraft with low wing loading, the latter large quantities of heavy fuel to confer the necessary range. Therefore the U-2 is of very lightweight construction, dispensing with conventional landing gear and pressurisation to save extra weight, and having wings of large area. Landing gear is of bicycle type with single wheels fore and aft, and balanced on the ground by wing-tip 'pogos' - a strut and wheel device which drops away when the U-2 becomes airborne - was selected. The pilot is accommodated on a light-weight seat, dressed in a semi-pressure suit with his head enclosed in an astronaut-type helmet, and forced to breathe pure oxygen for his survival. A medium-powered turbojet is adequate to lift this lightweight aircraft, and long range is possible by shutting it down and gliding for long periods.

In addition to photo and electronic reconnaissance, U-2 were used for weather reconnaissance, high-altitude research, measurement of radiation levels, and for the tracking and recovery of space capsules. They were used for reconnaissance during the Cuban crisis, in Vietnam and during the Arab-Israeli conflict.

3-View 
Lockheed U-2A three-view drawing (752 x 771)


Specification 
 MODELU-2C, on service with NASA
 CREW1
 ENGINE1 x Pratt-Whitney J75-P-13B, 7711kg
 WEIGHTS
    Take-off weight10225 kg22542 lb
 DIMENSIONS
    Wingspan24.38 m79 ft 12 in
    Length15.24 m50 ft 0 in
    Height4.57 m14 ft 12 in
    Wing area52.49 m2565.00 sq ft
 PERFORMANCE
    Cruise speed740 km/h460 mph
    Ceiling27000 m88600 ft
    Range4635 km2880 miles

3-View 
Lockheed U-2A three-view drawing (678 x 756)

Comments 
Ed Smart, edsmart(@)localnet.com, 15.05.2008

As the aircraft climbed enroute to its cruising altitude of 68,000 to 72,000 feet it passed through a "chimney" in the atmosphere wherein the aerodynamic characteristics of the aircraft caused the mach buffet and the stall buffet to approach to within less than 10 KIAS of each other. Since initial mach buffet and stall buffet are similar, the normal procedure was to reduce speed by 1 or 2 knots to see if the buffet got better or worse and airspeed was then adjusted accordingly. Once above the "chimney" the spread improved somewhat. (U-2 pilot, 1962-1966)

Don Burritt, flyboydjb(@)centurytel.net, 07.05.2008

Why did the pilot have only + or - 6 degrees of pitch or decent when flying at max alitude? It was stated by a pilot if that envolpe was exceeded it wou stall , or come apart.

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