;wherein u is a vector containing the values of the quantities of each control surface, x is a vector including an estimated angle of attack, an estimated angle of sideslip, an estimated rolling speed, an estimated pitching speed and an estimated yawing speed, δy is an error vector including the errors between the measured speeds and the respective estimated speeds, y is a measure vector including the values of the measured speeds, A, B, C, D are matrixes representative of the behaviour of the aircraft in unperturbed motion and L is a feedback matrix including the gains of a predetermined numeric control filter. The estimated angle of attack and the estimated angle of sideslip are obtained from the model to use as angle of attack and angle of sideslip of the aircraft."/>
公开/公告号US2010185345A1
专利类型
公开/公告日2010-07-22
原文格式PDF
申请/专利权人 ALBERTO CHIESA;
申请/专利号US20090636545
发明设计人 ALBERTO CHIESA;
申请日2009-12-11
分类号G05D1/08;
国家 US
入库时间 2022-08-21 18:54:33