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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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White primer for coating 2219 aluminum alloy supplies a base for a top coating of enamel. A formulation of pigments and vehicle results in a primer with high corrosion resistance and minimum film thickness.
Mathematical formulas are used to determine if, and to what extent, an instrumentation system that has been exposed to the elements should be dried out to restore minimum permissible leakage resistance to ground. Formulas are also derived and used for an intermediate number of systems that are exposed to moisture penetration.
Identification of regions between 65 and 120 km by different loss mechanisms - study of lower ionosphere at solar minimum based on measurements by Nike-Apache rockets
IBM-F04 Fortran program to design minimum weight fuel cell power systems for space vehicles
Linear PAM regulator minimum energy design by geometric interpretation and graphical solution
Minimum propellant consumption trajectories to Mars for constant-thrust, constant-specific impulse vehicles with optimum coasting periods
Primary cosmic ray charge and energy spectra determination for helium through neon during solar minimum
Technique based on order statistics to determine minimum confidence level for signal detection by using correlator bank
Simplified criteria for minimum load and drift control of large booster vehicle
Minimum weight design of symmetrically stiffened orthotropic cylinders under axial compression
Discrete minimum principle to derive feedback control law for linear discrete-time systems
Mean atmospheric densities during minimum solar activity derived from energy changes of Explorer XIX Satellite
Dosimetric evaluation of flare produced proton beams at solar minimum, and flare exposure behind Gemini and Apollo shield systems
Calculus of variations used to determine minimum time aircraft trajectories between two fixed points in range-altitude space
Hypersonic aerodynamic characteristics of zero lift minimum-wave-drag body
Minimum impulse time free transfer between elliptic orbits
Minimum fuel consumption two impulse soft lunar landing trajectories
Optimum transfer between two terminal points for minimum initial impulse under arbitrary initial velocity vector