重复使用运载器基于轨迹线性化的俯仰角控制

孙春贞; 黄一敏; 郭锁凤

重复使用运载器基于轨迹线性化的俯仰角控制

南京航空航天大学自动化学院, 南京 210016

计量
- 文章访问数: 1499
- HTML浏览量: 2
- PDF量: 469
- 被引次数: 0
出版历程
- 收稿日期: 2007-08-11
- 修回日期: 2008-04-29
- 刊出日期: 2008-10-28

Reusable launch vehicle pitch attitude control system research by trajectory linearization

College of Automation Engineering, Nanjing University of Aeronautics and Astronautic, Nanjing 210016, China

摘要

摘要: 为了改善重复使用运载器末端区域能量管理段的控制系统性能,提出了一种基于轨迹线性化的俯仰角控制回路结构,该结构由伪逆模型前馈和反馈控制组成.根据瞬时平衡的定义,沿轨迹剖面线性化,获得了伪逆模型的设计方法,形成俯仰控制结构.以高空超声速飞行为例,进行了俯仰角控制设计,并与常规反馈控制相比较.结果表明,基于轨迹线性化的俯仰角控制,可以改善控制系统的动态性能,减小反馈回路的负担,降低积分饱和的可能性.
- 俯仰角控制 /
- 轨迹线性化 /
- 伪逆模型 /
- 重复使用运载器
Abstract: To improve the performance of terminal area energy management control system for reusable launch vehicle,the pitch attitude control system architecture based on trajectory linearization was developed,which includes two parts: pseudo-inverse model and feedback control system.Using the concept of instantaneous equilibrium,the pseudo-inverse model was designed by trimming the whole profile and the pitch attitude control system architecture was built.Take example for the flight phase of high altitude and super sonic,the system was designed and compared with traditional feedback control system.The results show that the control system by trajectory linearization can improve the transition performance,offload the feedback loop,and reduce the possibility of integrator saturation.
- pitch attitude control /
- trajectory linearization /
- pseudo-inverse model /
- reusable launch vehicle(RLV)

HTML

参考文献(10)

[1]	Moore T E.Space shuttle entry terminal area energy management[R].NASA-TM-104744,1991.
[2]	Carman G L.Shuttle TAEM guidance and flight control[R].NASA-TM-81100,1980.
[3]	孙春贞,黄-敏.重复使用运载器末端能量管理段制导系统仿真[J].系统仿真学报,2007,19(6):1260-1264.SUN Chunzhen.HUANG Yimin.Terminal area energy management guidance scheme simulation for reusable launch vehicle[J].Journal of System Simulation,2007,19(6):1260-1264.(in Chinese)
[4]	Zhu J J,Banker B D.X-33 ascent flight control design by trajectory linearization-A singular perturbation approach JR].AIAA-2000-4159.
[5]	WU Xiaofei.A nonlinear flight controller design for a UFO by trajectory linearization method Part I--Modeling[C]//Proceedings of the Thirty-Fourth Southeastern Symposium on System Theory,[S.1.];[s.n.],2002:97-102.
[6]	WU Xiaofei.A nonlinear flight controller design for a UFO by t raiectory linearization method PartⅡController design[C]//Proceedings of the Thirty-Fourth Southeastern Symposium on System Theory,[s.I.];[s.n.],2002:103-107.
[7]	Zhu J J.A type two troscetory linearization controller for a reusable launch vehicle-A singular perturbation approach[R].AIAA-2004-5184.
[8]	Tim B.Improved trajectory linearization flight controller for reusable launch vehicles[R].AIAA-2004-0875.
[9]	孙春贞,黄-敏,郭锁风.重复使用运载器末端能量管理段轨迹线设计[J],系统工程与电子技术,2007,29(6):909-9 14.SUN Chunzhen,HUANG Yimin,GUO Suofeng.Trajectory design for teminal area energy management of reusable launch vehicle[J].System Engineering and Eelectronics,2007,29(6):909-914.(in Chinese)
[10]	孙春贞,黄-敏,郭锁凤.无动力自动着陆轨道的鲁棒性分析[J].中国空间科学技术,2006,26(2):24-29.SUN Chunzhen,HUANG Yimin,GUo Suofeng.Robusthess assessing of unpowered autolanding trajectory[J].Chinese Space Science and Technology,2006,26(2):24-29.(in Chinese)