Patent ID: 9677504
Date: 2017-06-13
CPC Classifications: F02K,F05D

Claim:
1. A method of controlling a rocket, the method comprising: measuring a combustion chamber pressure within a combustion chamber of the rocket; calculating a logarithm of the measured combustion chamber pressure; calculating a difference between the logarithm of the measured combustion chamber pressure and a logarithm of a reference combustion chamber pressure value to generate an error signal; filtering the error signal to generate a compensated total flow area control signal in a logarithm domain with a controller, wherein the filtering the error signal comprises filtering the error signal with a proportional-plus-integral filter; exponentiating the compensated total flow area control signal in the logarithm domain to provide a compensated total flow area control signal in a physical domain; moving at least one valve in communication with the combustion chamber in response to the compensated total flow area control signal in the physical domain; and changing a gain of an integrating filter of the proportional-plus-integral filter as a free volume of the combustion chamber increases.