| Integrated Entry Guidance for Reusable Launch Vehicle |
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| 作者姓名： | NING Guo-dong ZHANG Shu-guang FANG Zhen-ping |
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| 作者单位： | School of Aeronautical Science and Technology，Beijing University of Aeronautics and Astronautics，Beijing 100083，China |
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| 基金项目： | 国家高技术研究发展计划(863计划) |
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| 摘 要： | A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor, and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty. Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertain-ties are presented to demonstrate the capacity and reliability of this method.
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| 关 键 词： | 鲁棒性 轨道 运载火箭 导航系统 |
| 收稿时间： | 24 August 2006 |
| 修稿时间： | 2006-08-24 |
Integrated Entry Guidance for Reusable Launch Vehicle |
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| NING Guo-dong ZHANG Shu-guang FANG Zhen-ping.Integrated Entry Guidance for Reusable Launch Vehicle[J].Chinese Journal of Aeronautics,2007,20(1):1-8. |
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| Authors: | NING Guo-dong ZHANG Shu-guang FANG Zhen-ping |
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| Institution: | School of Aeronautical Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
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| Abstract: | A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor,and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty.Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertainties are presented to demonstrate the capacity and reliability of this method. |
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| Keywords: | guidance trajectory generation entry onboard constraint robustness Launch Vehicle Reusable Entry Guidance Fast profiles simulations modeling uncertainties capacity reliability algorithm lateral guidance system wide range reliable good performance presence significant |
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