|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 2 인용 특허 : 4|
A method of providing an angular rate signal for attitude control in a missile flight control system by linearly mixing a derived rate signal generated from the measured attitude angle and a simulated rate signal generated from the measured nozzle angle. The derived rate is generated from the differentiation of missile attitude data and the simulated rate is generated by simulating the missile attitude dynamics based on the actual nozzle angle. The derived rate, which is filtered to remove the effects of quantization and noise is dominant at low frequenc...
A method for providing an angular rate signal for use in attitude control of a missle in a missle flight control system, said missile having an attitude angle between the missile direction of motion and a vertical, said missile having a centerline and a nozzle angle through which thrust is applied with respect to the centerline, which comprises: (a) measuring the attitude angle; (b) generating a first estimated rate signal from the measured attitute angle; (c) measuring the nozzle angle; (d) generating a second estimated rate signal from the measured noz...