航空兵器
航空兵器
항공병기
HANGKONG BINGQI
2012年
2期
3-8,21
,共7页
挠性模态%传感器容错%保性能控制器%高超声速飞行器
撓性模態%傳感器容錯%保性能控製器%高超聲速飛行器
뇨성모태%전감기용착%보성능공제기%고초성속비행기
flexible mode%sensor fault-tolerance%guarantee cost controller%hypersonic flight vehicle
针对一类带有挠性的吸气式高超声速飞行器设计具有传感器容错能力的控制器。飞行器机体的刚性模态和挠性模态之间的强耦合作用不仅仅会直接影响到气动力和气动力矩,而且还会造成传感器的测量误差,尤其是给攻角测量带来加性扰动的影响,这给基于状态反馈控制器的设计带来了极大挑战。因此,为了解决这个问题,引入了比例积分型状态观测器,利用系统的输入和受干扰的输出重构出原系统的状态,然后利用重构的状态设计保性能控制器,在稳定该高超声速飞行器模型的同时,也使得给定的二次性能指标达到其最小的上界。本文的主要贡献在于成功地改进了传统意义上的状态反馈方法,并消除了因为挠性模态影响造成的传感器测量误差所带来的影响,这在实际工程中具有重要的意义。文章最后给出的仿真结果显示出了比例积分型状态观测器具有较好的动态性能,以及保性能控制器出色地完成了该模型高度和速度通道对指令信号的跟踪任务。
針對一類帶有撓性的吸氣式高超聲速飛行器設計具有傳感器容錯能力的控製器。飛行器機體的剛性模態和撓性模態之間的彊耦閤作用不僅僅會直接影響到氣動力和氣動力矩,而且還會造成傳感器的測量誤差,尤其是給攻角測量帶來加性擾動的影響,這給基于狀態反饋控製器的設計帶來瞭極大挑戰。因此,為瞭解決這箇問題,引入瞭比例積分型狀態觀測器,利用繫統的輸入和受榦擾的輸齣重構齣原繫統的狀態,然後利用重構的狀態設計保性能控製器,在穩定該高超聲速飛行器模型的同時,也使得給定的二次性能指標達到其最小的上界。本文的主要貢獻在于成功地改進瞭傳統意義上的狀態反饋方法,併消除瞭因為撓性模態影響造成的傳感器測量誤差所帶來的影響,這在實際工程中具有重要的意義。文章最後給齣的倣真結果顯示齣瞭比例積分型狀態觀測器具有較好的動態性能,以及保性能控製器齣色地完成瞭該模型高度和速度通道對指令信號的跟蹤任務。
침대일류대유뇨성적흡기식고초성속비행기설계구유전감기용착능력적공제기。비행기궤체적강성모태화뇨성모태지간적강우합작용불부부회직접영향도기동력화기동력구,이차환회조성전감기적측량오차,우기시급공각측량대래가성우동적영향,저급기우상태반궤공제기적설계대래료겁대도전。인차,위료해결저개문제,인입료비례적분형상태관측기,이용계통적수입화수간우적수출중구출원계통적상태,연후이용중구적상태설계보성능공제기,재은정해고초성속비행기모형적동시,야사득급정적이차성능지표체도기최소적상계。본문적주요공헌재우성공지개진료전통의의상적상태반궤방법,병소제료인위뇨성모태영향조성적전감기측량오차소대래적영향,저재실제공정중구유중요적의의。문장최후급출적방진결과현시출료비례적분형상태관측기구유교호적동태성능,이급보성능공제기출색지완성료해모형고도화속도통도대지령신호적근종임무。
This paper is devoted to the controller design for a flexible air-breathing hypersonic flight vehicle （FAHFV） with sensor fault-tolerance. The curve-fit model of the FAHFV developed by Sigthorsson introduces strong bilateral coupling between the rigid and flexible modes. The flexible modes not only influence the aerodynamic forces and moments directly, but also create unexpected sensor measurement fault, especially for the additive turbulence for angle-of-attack measurement which brings great challenge for controller design. Thus, in order to solve this problem, firstly, a linear model is established by using small-perturbation method around the given trim condition. Secondly, a PI observer is introduced to recortfigure all the states without static error on the basis of the system inputs and contaminated outputs. Finally, a guarantee cost controller based on the recortfigured states feedback is designed to make the FAHFV stabilized and make the given quadratic performance index function get to its least upper boundary. What contributes is that the traditional state feedback method is ameliorated and the effects of sensor fault caused by flexible modes are eliminated successfully, which is great significance in actual engineering. Simulation results show that the PI observer achieves good transient performance and the guarantee cost controller successfully makes the altitude and the velocity of the FAHFV track the reference trajectory excellently.
