摘要
近空间飞行器具有广泛的军事用途。飞行控制系统是保证近空间飞行器飞行安全、可靠、有效完成复杂战术/战略任务的关键系统之一。由于飞行控制系统存在多种不确定性,飞行器本身也易于受到大气紊流等强干扰的作用,设计满足特定性能要求的鲁棒控制器十分重要。本课题基于LMI将近空间飞行器的控制问题转化为线性矩阵不等式系统的可行性问题,以有效推动LMI方法在飞行控制领域中的应用。
As great benefits are got from the applications of the near space vehicle, especially the applications in military and civilian field, more and more attention is paid to the development of the near space vehicle in the world. To accomplish the complicated missions safely and effectively, there must be an advanced flight control system for near space vehicle. To reduce the effects of the uncertainties and disturbances on flight performances for the near space vehicle, it is inapor^t to design a controller with good performances, classical H^robust control methods have been replaced with other advanced control methods gradually. This issue of I_MI-based converted the conlrol problem of near space vehicle to the feasibility problem of linear matrix inequalities system, in order to effectively promote the application of LMI method in the field of flight control.
出处
《自动化与仪器仪表》
2012年第5期42-44,共3页
Automation & Instrumentation
基金
江苏省创新基金
