Flame spread over fuel beds - Solid phase energy considerations, part 2
Flame spread over surface of solid-fuel bed in oxygen-inert environment
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Flame spread over surface of solid-fuel bed in oxygen-inert environment
Interfacial stability at thin flexible partition between fuel and propellant flows for gas core nuclear rockets
Space shuttle electric power distribution system design and development
NASTRAN computer program used to calculate lateral deflections of weak spacecraft antenna boom to determine stiffness at small strains
Design, development, and characteristics of open cycle, gas core nuclear rocket engine
Comparison of logistics problems and cost aspects in selection of aircraft for earth resources surveys
N-port networks interconnection by NASAP-70 transfer function capability for large scale circuit problems, considering Laemmel and Cascade Parameter methods
Laboratory test set for integration of data compression and error correction encoding of digital communications system
Error correction coding/decoding techniques integration, discussing convolutional and block coding and Viterbi, Sequential and Threshold decoding algorithms
Hadley Rille origin as lava channel and partly collapsed lava tube, taking into account topographic configuration, terrestrial analogs, geomorphology and meteoroid bombardment
Jet transport aircraft stability and controllability under atmospheric turbulence conditions, discussing longitudinal and lateral- directional characteristics with particular attention to unstable spiral mode
Orbital nonpropulsive vent system to remove excess or residual propellant vapors and waste gases with minimum impulse imbalances imparted to vehicle
Safe disposal for nuclear zirconium hydride reactors for manned space base mission
Milky Way galaxy poloidal magnetic field generation with hydromagnetic dynamos, showing galactic cosmic rays as major driving force
Statistical phase space cross sections for helium ion-nitrogen molecule reactions, including dispersion and short range forces in intramolecular potential energy function
Apollo 11 and 12 lunar rocks and soil chemical composition, considering petrogenesis and major and trace elements abundance
The preceding papers have discussed the aerodynamics and heating of several vehicles designed for atmospheric reentry from satellite orbits. Because of large heating inputs, some fundamental questions about the structure of these vehicles are also raised. Although there are many factors which influence structural design, only a brief examination of the relationship between heating input and structural weight is discussed here. For this purpose the heating inputs associated with the four vehicles shown in figure 1 are employed.
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