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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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Fast, accurate technique for simulating the Saturn Flight Control System was devised. The technique is simple to implement and can be readily substituted for slower or less accurate techniques. This technique can be applied to a large class of problems that require a rapid accurate calculation of the response of linear differential equations to a continuous input.
Force feedback compensation concept for improved manual control system performance
Effect of control system nonlinearities on human operator single loop compensatory tracking performance
Analog computer for determining pilot response in manual control systems
Methods and analyses for flight evaluation of control systems for multistage launch vehicles
Subsystems of Mariner Venus 67 spacecraft guidance and control system
Necessary conditions for optimal control systems with adjustable delay time obtained from first order variation of performance index
Control systems design for in-core thermionic reactor space power plants, using variable feedback analysis and analog simulation
Model reference adaptive control system redesign by Liapunov second method for linear systems
Apollo lunar module pressure-fed bipropellant reaction control system design requirements and system description
Design technology of attitude control systems for large launch vehicles
Computation of regions of constrained stability for nonlinear control systems
Translational forces on Mariner 5 stemming from attitude control system studied to determine trajectory for scientific and operational purposes
Translational forces on Mariner 5 stemming from attitude control system, determining trajectory for scientific and operational purposes
Performance index includes a model representing linear control-system design specifications. Based on a geometric criterion for approximation of the model by the actual system, the index can be interpreted directly in terms of the desired system response model without actually having the model's time response.
Analysis of Saturn launch vehicle navigation, guidance, and control system
Saturn S-4B orbital workshop attitude control system analysis
Terminal states and time specifications influence on optimum control systems, using Pontryagin principle for boundary value problems application