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2 edition of Study of a fail-safe abort system for an actively cooled hypersonic aircraft found in the catalog.

Study of a fail-safe abort system for an actively cooled hypersonic aircraft

C. J. Pirrello

Study of a fail-safe abort system for an actively cooled hypersonic aircraft

volume I--technical summary

by C. J. Pirrello

  • 205 Want to read
  • 20 Currently reading

Published by U.S. National Aeronautics and Space Administration, for sale by the National Technical Information Service in Washington, Springfield, Va .
Written in English

    Subjects:
  • Airframes.,
  • Hypersonic planes.

  • Edition Notes

    StatementC. J. Pirrello and R. L. Herring; prepared by McDonnell Aircraft Company, St. Louis, Mo., for Langley Research Center.Center.
    SeriesNASA contractor report ; NASA CR-2652, NASA contractor report -- NASA CR-2652.
    ContributionsHerring, R. L., Langley Research Center., McDonnell Douglas Corporation., United States. National Aeronautics and Space Administration.
    The Physical Object
    Paginationx, 75 p. :
    Number of Pages75
    ID Numbers
    Open LibraryOL15210644M

    Thermal protection systems (TPSs) for space and hypersonic vehicles encompass a wide range of materials and design designs. In any particular vehicle, a variety of materials may be : Frances Hurwitz. Start studying chapter Learn vocabulary, terms, and more with flashcards, games, and other study tools.

    Surprising though it may seem, the concept of hypersonic flight surfaced relatively early. In the late s Eugene Sänger had conceived a rocket-powered boost-glide vehicle in Germany, named Silbervogel (Silver bird) which could have been used to attack the United States, and land safely in Japan afterwards. Although the project was cancelled by the Reich Air Ministry in , Sänger never Cited by: STUDY. Flashcards. Learn. Write. Spell. Test. PLAY. Match. Gravity. Created by. rachel_mascari. Abnormal Psychology. Terms in this set (25) People with psychological disorders may inherit a predisposition to developing behavioral disturbances. This provides evidence that _____ causes are responsible for many of the prevalent abnormalities.

    Start studying Chapter 5 Psychology Learn vocabulary, terms, and more with flashcards, games, and other study tools. a. No, an interlock fail-safe system is provided by each system’s Pressure Switch. This prevents the pilot from being able to turn off both flight hydraulic systems at the same time. (1). The opposite system’s Pressure Switch makes the ground that allows the pilot to shut off the Pilot Solenoid Valve (PSV) on the system to be turned off. (2).


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Study of a fail-safe abort system for an actively cooled hypersonic aircraft by C. J. Pirrello Download PDF EPUB FB2

Analysis Program, FASTEMP. This program was used to analyze fail-safe abort sys-tems for an actively cooled hypersonic aircraft (Contract NASA-Langley, NASJJ. FASTEMP analyzes the steady state or transient temperature response of a thermal model defined in rectangular, cylindrical, conical and/or spherical coordinate system.

Study of a fail-safe abort system for an actively cooled hypersonic aircraft. Washington: U.S. National Aeronautics and Space Administration ; Springfield, Va.: For sale by the National Technical Information Service, STUDY OF A FAIL-SAFE ABORT SYSTEM FOR AN ACTIVHLY COOLED HYPERSONIC AIRCRAFT, VOLUME I, TECHNICAL SUMMARY by C.

Pirrello and R. 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.

Pirrello, joint author. 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.

Herring and C. 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.

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. 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.

A preliminary study was made of a fail-safe-system concept 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 aircraft structure. NASA Images Solar System Collection Ames Research Center.

Brooklyn Museum. Full text of "A cumulative index to the issues of Aeronautical Engineering, a special bibliography". NASA Images Solar System Collection Ames Research Center.

Brooklyn Museum. Full text of "NASA Technical Reports Server (NTRS) A cumulative index to the issues of Aeronautical Engineering, a special bibliography". Fuel is routed from the aircraft's main fuel tank through heat exchangers with a secondary cooling loop, to the actively- cooled fuselage leading edge, and then to the propulsion active cooling system including the intemal propulsion flowpath and the initial part of.

Aircraft accident report: McDonnell Douglas Corporation, DC, NG, Yuma, Arizona, J by United States (Book) Presiding officer's report to the administrator on the investigation of the McDonnel Douglas Corporation and the model DC aircraft by Carl B Schellenberg (Book).

New Approaches to Hypersonic Aircraft_ Seventh Congress of International Council of the Aeronautical Sciences, Rome, Italy, Sept. ] Hypersonic Vehicle Wing Structure Evaluation. Co., NASA CR, Lockheed.; Missiles and Space Anon.: Study of Structural Active Cooling and Heat Sink Systems for Space.

Aerodynamic Performance Analysis of A New Conception Hypersonic Aircraft. Xiaoyong Ma, Shidong Zhong, Yu Xiao, Wei Li, Zhigang Experimental Study of Hypersonic Flutter of a Blunt-leading-edge Trapezoidal Wing. Chen Ji, Wei Performance Analysis and Enhancement of Magnetohydrodynamic Heat Shield System For Hypersonic Vehicles.

Kai Li, Jun.A passive non-ablating thermally protective structure body is disclosed. An improved-reliability heat pipe edge comprises a non-porous material formed into a wedge-shaped chamber, and a porous layer.

The porous layer extends from interior surfaces of the non-porous material to provide capillary by: American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA