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XSM-73 Goose : ウィキペディア英語版
XSM-73 Goose

The Fairchild SM-73 (originally Bull Goose) was a sub-sonic, jet-powered, ground-launched Decoy Cruise missile.
==Development==
Starting in December 1952 Fairchild began concept studies for a ground-launched long range decoy missile that could simulate strategic bombers on radar.〔''SM-73'', Directory of U.S. Military Rockets and Missiles - Appendix 1: Early Missiles and Drones, by Andreas Parsch (), retrieved November 10, 2007.〕
In March 1953, the United States Air Force released General Operational Requirement (GOR) 16 which called for a long range decoy missile to increase the effectiveness of Strategic Air Command bombers by confusing and saturating an air defense system.〔〔''SM-73 Bull Goose'', 1997 Web Page by the Federation of American Scientists, (), retrieved November 10, 2007.〕
Multiple SM-73 missiles would be ground-launched from Strategic Air Command bases located in the continental United States. Fifty percent of the deployed SM-73 missiles would be launched within the first hour after an alert and the remaining missiles would be launched one hour later.〔''Fairchild B-73 Bull Goose'', Fact Sheet from the National Museum of the USAF, (), Retrieved on November 10, 2007.〕 The requirement called for 85 percent of the decoy missiles to arrive at the target area within 115 nm (185 km).〔〔Historical Essay by Andreas Parsch, ''Goose'', (), retrieved on November 10, 2007.〕 The SM-73 was to fly 4,000 nm (7,408 km) at speed of at least 0.85 Mach at an operating altitude of 50,000 ft (15,240 m) with a payload of 500 lb (227 kg).〔 After flying 2,500 nm (4,650 km), the SM-73' would simulate the performance of the B-47 Stratojet or B-52 Stratofortress over the final 1,500 nm (2,780 km) of flight.〔
Study contracts were awarded to Convair and Fairchild in July 1954 by the United States Air Force under the project designation MX-2223.
The Fairchild MX-2223 design called for a non-metallic fuselage with swept wings and a v-tail. Radar reflectors were located in the fuselage and on pods positioned on the wing tips to simulate the radar return of a bomber.

抄文引用元・出典: フリー百科事典『 ウィキペディア(Wikipedia)
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