|Artist's concept of the Virtus|
|Role||Outsized cargo aircraft|
|National origin||United States|
|Designer||John M. Conroy|
|Built by||Turbo-Three Corporation|
US$12.5 million (est.)
|Developed from||Boeing B-52 Stratofortress|
The Conroy Virtus was a proposed American large transport aircraft intended to transport the Space Shuttle. Designed beginning in 1974 by John M. Conroy of the Turbo-Three Corporation, it was to incorporate a pair of Boeing B-52 Stratofortress fuselages to form a new craft utilizing existing parts for cost-savings.
The Space Shuttle was originally designed to utilize on-board turbofan engines for propulsion within the atmosphere, both upon re-entry and for ferry flights between landing sites, such as Edwards Air Force Base, the White Sands Missile Range, or contingency landing sites such as Easter Island, to the launch site at Kennedy Space Center at Cape Canaveral. When the air-breathing engines were deleted from the Shuttle design due to cost and weight concerns, a requirement arose for a transport aircraft capable of carrying the Shuttle from landing sites back to the Kennedy Space Center. One early design for a shuttle carrier aircraft was proposed by John M. Conroy, developer of the Pregnant Guppy and Super Guppy oversized cargo aircraft, in cooperation with the NASA Langley Research Center; named Virtus, a contract was issued for design and development work in 1974.
Expected to cost US$12.5 million each, Virtus was a twin-fuselage design powered by four large jet engines; it was intended for these to be Pratt & Whitney JT9D turbofans. Conroy proposed extensive use of 'off the shelf' military parts in the design to reduce costs; this included the use of fuselages from Boeing B-52 Stratofortress strategic bombers to form the aircraft's main fuselage pods, added to the new-design wing and tail section. The Space Shuttle Orbiter would be carried under the center section of the Virtus aircraft's wing, between the fuselages; other large cargos, including the Space Shuttle external tank, the Space Shuttle Solid Rocket Boosters, or dedicated cargo pods, could be alternatively carried.
The Virtus design was tested in the NASA Langley wind tunnel; while the results of the wind tunnel tests were considered promising, the drawbacks of such a large design, including the cost of developing an entirely new aircraft, flight testing the design, and the sheer size of the aircraft requiring the development and/or expansion of infrastructure to support it, militated against further development of Virtus. The Lockheed Corporation, which had proposed a twin-fuselage version of its C-5 Galaxy airlifter to carry the Shuttle, also saw its proposal rejected for the same reasons. A more modest conversion of existing C-5s was proposed, and nearly taken up by NASA, but it was determined that having aircraft continually available was preferable to being restricted by the United States Air Force on the use of C-5s, and Boeing's proposal for a conversion of the 747 airliner was selected, becoming the Shuttle Carrier Aircraft. A proposed commercial version of the Virtus design, named Colossus, also failed to gain any further interest, and the Virtus design was abandoned.
- Conroy, John M. (February 28, 1974). "Feasibility Study to Consider an Aircraft for the Launch and Air Transportation of the Space Shuttle Orbiter". Turbo-Three Corporation.
Data from Lowther 2012
- Wingspan: 450 ft (140 m)
- Wing area: 22,166 sq ft (2,059.3 m2)
- Aspect ratio: 9
- Max takeoff weight: 850,000 lb (385,554 kg)
- Powerplant: 4 × Pratt & Whitney JT9D-3A high-bypass turbofans, 45,800 lbf (204 kN) thrust each
- Cruise speed: 300 mph (483 km/h; 261 kn)
- Range: 3,000 mi (2,607 nmi; 4,828 km)
- Service ceiling: 35,000 ft (11,000 m)
- Related development
- Aircraft of comparable role, configuration and era
- Jenkins, Dennis R. (2001). Space Shuttle: The History of the National Space Transportation System - The First 100 Missions. Stillwater, MN: Voyageur Press. ISBN 0-9633974-5-1.
- Lowther, Scott (March–April 2012). "Virtus" (PDF). Horizons. Houston, TX: American Institute of Aeronautics and Astronautics Houston Section. 37 (5).