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High-altitude balloon-launched aircraft - A piloted simulation studyA real-time piloted simulation at the NASA Dryden Flight Research Facility was used to study the feasibility of launching a research aircraft from a high-altitude balloon. In the study, the simulated aircraft was launched in a nosedown attitude at zero airspeed from 110,000 ft. After launch, the pilot flew the aircraft through a near-maximum-lift pullout and then through a zoom climb to a trimmed, l-g flight condition at the test altitude. The study included parametric variations to measure the effects of launch altitude, gross weight, Mach number limit, and parachute size on the test altitude attained. The aerodynamic model of the simulated aircraft was based on flight test results, low Reynolds number windtunnel tests, and computational models; the model included significant Mach number and Reynolds number effects at high altitude. A small parachute was included in the simulation to limit Mach number during the pullout to avoid adverse transonic effects and their resultant energy losses. A small rocket motor was included in the simulation and was investigated for boosting the aircraft to a higher test altitude. In the study, a test altitude of approximately 95,000 ft was attained without rocket boost, and a test altitude in excess of 100,000 ft was attained using small rocket boost.
Document ID
19930046936
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Murray, James E.
(NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Moes, Timothy R.
(NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Norlin, Ken
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
August 16, 2013
Publication Date
February 1, 1993
Subject Category
Aeronautics (General)
Report/Patent Number
AIAA PAPER 93-1019
Meeting Information
Meeting: AIAA, AHS, and ASEE, Aerospace Design Conference
Location: Irvine, CA
Country: United States
Start Date: February 16, 1993
End Date: February 19, 1993
Sponsors: AHS, AIAA, ASEE
Accession Number
93A30933
Distribution Limits
Public
Copyright
Other

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