Published 1976
by U.S. National Aeronautics and Space Administration, for sale by the National Technical Information Service in Washington, Springfield, Va .
Written in English
Edition Notes
| Statement | C. J. Pirrello and R. L. Herring; prepared by McDonnell Aircraft Company, St. Louis, Mo., for Langley Research Center.Center. |
| Series | NASA contractor report ; NASA CR-2652, NASA contractor report -- NASA CR-2652. |
| Contributions | Herring, R. L., Langley Research Center., McDonnell Douglas Corporation., United States. National Aeronautics and Space Administration. |
| The Physical Object | |
|---|---|
| Pagination | x, 75 p. : |
| Number of Pages | 75 |
| ID Numbers | |
| Open Library | OL15210644M |
STUDY OF A FAIL-SAFE ABORT SYSTEM FOR AN ACTIVHLY COOLED HYPERSONIC AIRCRAFT, VOLUME I, TECHNICAL SUMMARY by C. J. Pirrello and R. L. Herring McDonnell Aircraft Company 1. SUMMARY A detailed study was conducted to conceptually design and evaluate a fail-safe actively cooled structural system which will be used in an abort mode from cruise Mach numbers of 3 to 6. Study of a fail-safe abort system for an actively cooled hypersonic aircraft: volume I--technical summary / By C. J. Pirrello, joint author. R. L. Herring, United States. National Aeronautics and Space Administration., McDonnell Douglas Corporation. and Langley Research Center. The fail-safe concept depends on basically three factors: (1) a reliable method of detecting a failure or malfunction in the active cooling system, (2) the optimization of abort trajectories which minimize the descent heat load to the aircraft, and (3) fail-safe thermostructural concepts to minimize both the weight and the maximum temperature the structure will reach during descent. The fail-safe concept depends on basically three factors: (1) a reliable method of detecting a failure or malfunction in the active cooling system, (2) the optimization of abort trajectories which minimize the descent heat load to the aircraft, and (3) fail-safe thermostructural concepts to minimize both the weight and the maximum temperature the structure will reach during : R. L. Herring and C. J. Pirello.
The Fail-Safe Abort System TEMPerature Analysis Program, (FASTEMP), user's manual is presented. This program was used to analyze fail-safe abort systems for an actively cooled hypersonic aircraft. FASTEMP analyzes the steady state or transient temperature response of a thermal model defined in rectangular, cylindrical, conical and/or spherical coordinate : Sr. L. A. Haas. Conceptual designs of a fail-safe abort system for hydrogen fueled actively cooled high speed aircraft are examined. The fail-safe concept depends on basically three factors: (1) a reliable method. The detection of a serious system malfunction in an actively-cooled hypersonic aircraft of course requires the effective emergency action be taken to slow the aircraft to a speed at which the radiation equilibrium temperature does not exceed the allowable temperature of the aircraft structure. () Study of a fail-safe abort system for an Cited by: 9. A Fuselage/Tank Structure Study for Actively Cooled Hypersonic Cruise Vehicles - Summary. Study of a Fail-Safe Abort System for an Actively Cooled Hypersonic Aircraft - Volume I, Technical Summary. NASA CR, Jan. Herring, R. L. and Stone, J. E.: Thermal Design for Areas of Interference Heating on Actively Cooled Hypersonic.
The Fail-Safe Abort System TEMPerature Analysis Program, (FASTEMP), user's manual is presented. This program was used to analyze fail-safe abort systems for an actively cooled hypersonic aircraft. NASA Images Solar System Collection Ames Research Center. Brooklyn Museum. Full text of "NASA Technical Reports Server (NTRS) A cumulative index to Aeronautical Engineering: A special bibliography". A fail-safe-system concept was studied as an alternative to a redundant active cooling system for supersonic and hypersonic aircraft which use the heat sink of liquid-hydrogen fuel for cooling the. Conceptual designs' of a fail-safe abort system for hydrogen fueled actively cooled high speed aircraft are examined. The fail-safe concept depends on basically three factors: (1) a reliable method of detecting a failure or malfunction in the active cooling system, (2) the optimization of abort trajectories which minimize the descent heat load to the aircraft, and (3) fail-safe thermostructural'concepts to .
