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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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In a normal coordinate system { y 𝑎 } , the identity 𝜕 2 𝑥 𝑝 /∂y 𝑛 ∂y 𝑚 = ∂ 2 𝑥 𝑝 /∂y 𝑚 ∂y 𝑛 is used to obtain expressions, involving the components of the metric tensor in this coordinate system, for the derivatives of the unit tangent vectors to the parametric curves. An example is given for a normal coordinate system in the De Sitter universe.
Intermediate vector bosons as unobservable particles described by renormalizable Lagrangian in indefinite metric space
Existence theorems for optimal control problems with vector valued cost function
Contributions from scalar mesons in derivation of nucleon axial vector form factor
Comparative analysis of several advanced thrust vector control system designs applied to large, solid propellant launch vehicles
Systems design and guidance and control analyses of thrust vector control systems for large, solid propellant launch vehicles
Staged vortex amplifier with integral gas generators for liquid rocket secondary injection thrust vector control
Liapunov theorem for range of unbound vector valued measure
Performance characteristics of gaseous secondary injection thrust vector control in overexpanded primary nozzles under sea level conditions
Probability of thrust vector misalignment in ion thrustor array
Thrust vector deflection stability analysis for minimum control requirements of booster vehicles during atmospheric flight
Thrust vector control for large launch vehicles with solid propellant first stages
Vector representation of rotations and their algebra
Vector calculations using crossed beam data and detector arrangement for measuring horizontal winds
Ion beam current and direction changes due to electrode misalignment, and analysis of electrode temperature distribution and thermal stresses in ion engine thrust vector
Load relief autopilot to minimize launch vehicle thrust vector deflection angle required for vehicle stability during flight through design winds
Constrained minimization under vector valued criteria in linear topological spaces
Performance of vortex valve controlled secondary injection thrust vector system for solid propellant rocket motor control