| 伴随方法在亚轨道飞行器预测制导中的应用 |
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| 引用本文： | 马广富,佘智勇.伴随方法在亚轨道飞行器预测制导中的应用[J].哈尔滨工业大学学报,2011,43(7):6-11. |
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| 作者姓名： | 马广富 佘智勇 |
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| 作者单位： | 哈尔滨工业大学航天学院;哈尔滨工业大学航天学院 |
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| 基金项目： | 国家自然科学基金资助项目(60774062) |
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| 摘 要： | 提出了一种求解最优两点边值问题的改进型伴随方法,并将其应用于一类以固体火箭发动机为动力的亚轨道飞行器轨迹优化问题中,间接得到一组平滑控制量;利用标称轨迹线性化概念,对该飞行器在标称轨迹附近做一阶泰勒展开,在给定可用姿态指令和摄动、干扰的上界条件下,利用滚动时域控制技术,得到了在系统摄动和干扰存在情况下拥有高精度、快速鲁...
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| 关 键 词： | 制导 伴随方法 滚动时域控制 轨迹线性化 预测校正 |
Rapid optimal predictive guidance via enhanced adjoint method for suborbital launch vehicles |
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| MA Guang-fu and SHE Zhi-yong.Rapid optimal predictive guidance via enhanced adjoint method for suborbital launch vehicles[J].Journal of Harbin Institute of Technology,2011,43(7):6-11. |
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| Authors: | MA Guang-fu and SHE Zhi-yong |
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| Affiliation: | School of Astronautics,Harbin Institute of Technology,150001 Harbin,China;School of Astronautics,Harbin Institute of Technology,150001 Harbin,China |
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| Abstract: | An enhanced adjoint method for solving two point boundary value problems is proposed and applied to trajectory optimization problems for a rocket based high speed suborbital launch vehicle,and smooth control serials are obtained indirectly.The first order Taylor Expansion is used to the nominal trajectory which is calculated by the enhanced adjoint method.High robust,high accurate tracking result is obtained under disturbance boundary constrains by receding horizon control technology which is featuring prediction ability.The simulation results demonstrate the capacity and reliability of this proposed method. |
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| Keywords: | guidance adjoint method receding horizon control trajectory linearization prediction |
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