Investigation into more complete use of structural materials through a study of the stress-temperature-time conditions of a re-entry vehicle

Mode of access: Internet.

Synthesis of flight control systems subject to vehicle parameter variations.

Mode of access: Internet.

14th Aerospace Mechanisms Symposium : proceedings of a symposium held at NASA Langley Research Center, Hampton, Virginia, May 1-2, 1980 /

Includes bibliographies.

Mass flow measurement techniques for a flight enthalpy probe. Contract no. P.O.33-531174-G48.

Mode of access: Internet.

Chemical kinetics in a reentry flow field, by M. H. Bortner.

At head of title: Space Sciences Laboratory. Aerophysics Section.

Anthropometric source book /

Includes bibliographies and indexes.

Structural design of missiles and spacecraft

Mode of access: Internet.

Antiproton annihilation propulsion /

Mode of access: Internet.

Study of an inorganic system for the recovery of oxygen (30-day evaluation program)

Cover title.

Concepts of operations for a reusable launch vehicle /

"September 1997."

Dynamics and thermodynamics of planetary entry.

Includes bibliography.

Interlevel correlations of temperature and density, surface to 60 km. /

"Meteorology Division. Project 6670."

Investigation of ablation effects on hypersonic dynamic stability of a 10⁰ cone

Mode of access: Internet.

High temperature radome design techniques.

Caption title.

Numerical heat transfer analysis of carbon-based foams for use in thermal protection system

The applicability of carbon-based foams as an insulating or active cooling material in thermal protection systems (TPSs) of space vehicles is considered using a computer modeling. This study focuses on numerical investigation of the performance of carbon foams for use in TPSs of space vehicles. Two kinds of carbon foams are considered in this study. For active cooling, the carbon foam that has a thermal conductivity of 100 W/m-k is used and for the insulation, the carbon foam having a thermal conductivity of 0.225 W/m-k is used. A 3D geometry is employed to simulate coolant flow and heat transfer through carbon foam model. Gambit has been used to model the 3D geometry and the numerical simulation is carried out in FLUENT. Numerical results from this thesis suggests that the use of CFOAM and HTC carbon foams in TPS's may effectively protect the aluminum structure of the space shuttle during reentry of the space vehicle.