|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 5 인용 특허 : 2|
The present invention relates to a solid rocket motor control system that uses state of the art electrically ignited, extinguishable and throttleable propellants. In embodiments, the control system is implemented by a software algorithm embedded in missile flight controllers and contains all control system elements and control compensation that performs thrust control for many defense and space rocket motor applications, for example.
1. A method comprising: receiving a thrust command;controlling electrical power provided to a solid propellant to cause the solid propellant to output a thrust corresponding to the thrust command;monitoring a chamber pressure corresponding to the thrust output; andadjusting the electrical power in accordance with the monitored chamber pressure. 2. A method according to claim 1, wherein the solid propellant is an electric solid propellant comprising electrodes embedded therein, and the electrical power is provided to the electrodes. 3. A method according ...