NASA NTRS · 19720052669
Digital controller for high pressure rocket engine.
Abstract
Description of a general approach for the design of an adaptive digital control system for liquid bipropellant rocket engines. The technique employs linearized transfer functions derived from perturbations of an engine simulation. The linear models serve as a basis on which to develop candidate closed-loop control laws quickly and economically.
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Thompson, Z., Cummings, W. J., Hall, D. M.. 1972-01-01. Digital controller for high pressure rocket engine.. https://ntrs.nasa.gov/citations/19720052669
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