Optimum deorbit positioning for minimum impulse reentry.
Optimum deorbit positioning on planetocentric elliptic orbit for single impulse reentry treated by two coupled quartic polynomials
ELLIPTICAL ORBIT↗
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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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The heliocentric intensity gradients of cosmic- ray protons and helium during minimum solar modulation.
Cosmic ray protons and helium nuclei intensity measured as function of energy or magnetic rigidity, determining particle intensity gradient under equilibrium conditions for diffusion
DIFFUSION COEFFICIENT↗
Optimum deorbit positioning for minimum impulse reentry.
Optimum deorbit positioning on planetocentric elliptic orbit for single impulse reentry treated by two coupled quartic polynomials
REENTRY PHYSICS↗
Study of minimum pressure loss in high velocity duct systems Quarterly report
Bellows configurations design, pressure loss, and vibration tests to minimize pressure drop and improve gas and liquid flow in spacecraft high velocity duct systems
Gerlach, C. P.↗
A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight Final report, Jul. 1964 - Sep. 1967
Electrolytes, anodes, and cathodes for high energy density battery with 200 watt hours per pound of total battery weight
Amlie, R. F.↗
Application of multivariable search techniques to the shaping of minimum total heat re-entry bodies at hyberbolic velocity
Heat minimization and optimal shapes for bodies of revolution entering earth atmosphere at hyperbolic speeds
Hague, D. S.↗
Low-temperature resistance minimum and magnetoresistance for dilute alloys of iron in copper
Predictions for magnetoresistivity temperature dependence of dilute alloys of iron in copper
Hudson, W. R.↗
Evaluation of certain minimum boom concepts
Sonic boom efficiency factor analyses for rectangular configuration, high aspect ratio arrow wing, and delta wing models
Henderson, H. R.↗
Minimum fuel control of a pitch motion of a satellite in circular orbit
Time function analysis for optimal control of satellite attitude and control jet fuel consumption in circular orbits
Fluegge-Lotz, I.↗
On minimum time and fuel orbital transfer.
The problem of a maneuverable spacecraft, with limited thrust capability, moving between two coplanar circular earth orbits is considered. Thrusting is performed in the plane defined by the circles, so that the nonlinear dynamics and subsequent optimization problem are simplified. The approach used in this paper differs from the approaches of Edelbaum and Goetz in that the equations of motion are not linearized before formulating the optimization problem. An averaging approximation is used to determine the structure of the significant co-state variables.
Stuart G. Greenberg↗
Minimum detectable limit of lithium in the upper atmosphere.
Lithium emission rate limits in upper atmosphere, discussing high altitude thermonuclear explosions effects /1958-1963/
Gardner, J. A.↗
Minimum time control of a nonlinear system.
Time optimal control for nonlinear systems, expressing optimal control law as function of state variables
Fluegge-Lotz, I.↗
The matrix minimum principle.
Pontryagin maximum principle restated to apply to systems described by matrix, optimizing performance of linear system
Athans, M.↗
Changes in the lower exosphere since solar minimum.
Satellite measurements of atmospheric densities during period of increasing solar activity
Keating, G. M.↗
Minimum detectable limit of lithium in the upper atmosphere.
Lithium emission rate limits in upper atmosphere, discussing high altitude thermonuclear explosions effects /1958-1963/
Gardner, J. A.↗
Minimum sensitivity design of attitude control systems Semiannual report, period ending 31 Aug. 1968
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Bongiorno, J. J., Jr.↗
Minimum thrust for correcting Keplerian orbits with application to interplanetary guidance
Thrust requirements for correcting Keplerian orbits with interplanetary guidance application
Boltz, F. W.↗
The landing task and pilot acceptance of displays for landing in reduced weather minimums
Landing task and pilot acceptance of displays for landing in reduced weather minima
Behan, R. A.↗