High-vacuum condenser tank for ion rocket tests Patent
High-vacuum condenser tank for testing ion rocket engines
Childs, J. H.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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A method for computing extremal maximum-range thrust-limited rocket trajectories with application to lunar transport
Extremal, maximum-range, thrust limited rocket trajectory computing method with lunar transport applications
Armstrong, E. S.↗
Influence of suction on shock wave-turbulent boundary layer interactions for two- dimensional and axially symmetric flows, 16 September 1967 - 30 June 1969
Influence of suction on shock wave turbulent boundary layer interactions for two dimensional and axially symmetric flows
Childs, M. E.↗
Suboptimal attitude control of a spin- stabilized axisymmetric spacecraft
Fuel suboptimal attitude control of spin stabilized axisymmetric spacecraft
Childs, D. W.↗
Use of Coles' universal wake function for compressible turbulent boundary layers
Compressible turbulent boundary layers velocity profiles, Coles universal wake function, least squares methods, wake-wall representation, etc
Childs, M. E.↗
Conical shock-wave turbulent boundary-layer interaction including suction effects
Conical shock wave-turbulent boundary layer interaction data obtained for adiabatic wall conditions at supersonic free stream Mach numbers, including suction effects
Childs, M. E.↗
Electrical resistivity of some engineering alloys at low temperatures
Low temperature electrical resistivities of Al, Ni, Cu, Ti and Fe alloys for different heat treated conditions
Childs, G. E.↗
Direction-cosine attitude-control logic for spin-stabilized axisymmetric spacecraft
Direction cosine attitude control logic for spin stabilized axisymmetric spacecraft, using control torques generated by reaction jet system
Childs, D. W.↗
Metal alloy resistivity measurements at very low temperatures
High speed, automated system accurately measures to approximately one percent in three minutes. System identifies materials having constant thermal or electric conductivity, predicts new material properties, develops alloys in accordance with desired specifications, and develops nondestructive devices for measuring precipitation hardening.
Childs, G. E.↗
On the determination of near body orbits using mass concentration models
Mathematical model for near-body orbit calculation using mass concentration, perturbation theory, nonlinear equations, geopotentials, and least squares method
Childs, B.↗
Fuel-optimal direction-cosine attitude control for spin-stabilized axisymmetric spacecraft
Spin stabilized spacecraft fuel optimal direction cosine attitude control, considering relation to inertial system
Childs, D. W.↗
A movable-mass attitude-stabilization system for artificial-g space stations
Artificial g space station configurations, developing movable control mass attitude stabilization system
Childs, D. W.↗
A simulation model for flexible rotating equipment
Lumped parameter simulation model for flexible turbine rotor dynamics in nonspinning coordinate system, discussing bearing constraints modeling methods and eigenanalysis applicability
Childs, D. W.↗
Applications of a mathematical programming technique to finite thrust rocket trajectory optimization
Iterative solution of least squares programming problem for finite thrust rocket trajectory optimization
Armstrong, E. S.↗
Electrodes for sealed secondary batteries
Self-supporting membrane electrode structures, in which active ingredients and graphite are incorporated in a polymeric matrix, improve performance of electrodes in miniature, sealed, alkaline storage batteries.
Boies, D. B.↗
Comparison of a discrete steepest ascent method with the continuous steepest ascent method for optimal programing
A discrete steepest ascent method which allows controls which are not piecewise constant (for example, it allows all continuous piecewise linear controls) was derived for the solution of optimal programming problems. This method is based on the continuous steepest ascent method of Bryson and Denham and new concepts introduced by Kelley and Denham in their development of compatible adjoints for taking into account the effects of numerical integration. The method is a generalization of the algorithm suggested by Canon, Cullum, and Polak with the details of the gradient computation given. The discrete method was compared with the continuous method for an aerodynamics problem for which an analytic solution is given by Pontryagin's maximum principle, and numerical results are presented. The discrete method converges more rapidly than the continuous method at first, but then for some undetermined reason, loses its exponential convergence rate. A comparsion was also made for the algorithm of Canon, Cullum, and Polak using piecewise constant controls. This algorithm is very competitive with the continuous algorithm.
Childs, A. G.↗