Online Trajectory Optimization Based on Successive Convex Optimization
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- 英文论文题名：Online Trajectory Optimization Based on Successive Convex Optimization
- 论文作者：Chaoyue Liu ; Cheng Zhang ; Huan Jiang ; Fenfen Xiong
- 英文论文作者：Chaoyue Liu ; Cheng Zhang ; Huan Jiang ; Fenfen Xiong ; Beijing Institute of Technology
- 年：2017
- 作者机构：Beijing Institute of Technology;
- 英文论文关键词：successive convex optimization ; trajectory optimization ; online
- 会议召开时间：2017-07-26
- 会议录名称：第36届中国控制会议论文集（B）
- 英文会议录名称：Proceedings of the 36th Chinese Control Conference（B）
- 语种：英文
- 分类号：TJ013;TJ765
- 学会代码：KZLL
- 会议名称：第36届中国控制会议
- 会议地点：中国辽宁大连
- 主办单位：中国自动化学会控制理论专业委员会
- 学会名称：中国自动化学会控制理论专业委员会
- 页数：6
- 文件大小：420k
- 原文格式：D
- 会议级别：全国
摘要
The traditional trajectory optimization methods are often difficult to achieve the rapid requirements of online planning. Therefore, the convex optimization method is applied to trajectory optimization of a missile to reduce the computational cost in this paper. With the convex optimization theory, the missile nonlinear motion model is firstly convexified based on the small perturbation linearization theory and then discretized using the Euler method, which is then solved by the successive convex optimization method. Simulation results show that the convex optimization technique can greatly reduce the computational time, while yields comparable optimal solutions compared to the well-known Gauss pseudospectral method.
The traditional trajectory optimization methods are often difficult to achieve the rapid requirements of online planning. Therefore, the convex optimization method is applied to trajectory optimization of a missile to reduce the computational cost in this paper. With the convex optimization theory, the missile nonlinear motion model is firstly convexified based on the small perturbation linearization theory and then discretized using the Euler method, which is then solved by the successive convex optimization method. Simulation results show that the convex optimization technique can greatly reduce the computational time, while yields comparable optimal solutions compared to the well-known Gauss pseudospectral method.
The traditional trajectory optimization methods are often difficult to achieve the rapid requirements of online planning. Therefore, the convex optimization method is applied to trajectory optimization of a missile to reduce the computational cost in this paper. With the convex optimization theory, the missile nonlinear motion model is firstly convexified based on the small perturbation linearization theory and then discretized using the Euler method, which is then solved by the successive convex optimization method. Simulation results show that the convex optimization technique can greatly reduce the computational time, while yields comparable optimal solutions compared to the well-known Gauss pseudospectral method.
引文
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[11]Acikmese B,Ploen S R.Convex programming approach to powered descent guidance for mars landing.Journal of Guidance,Control,and Dynamics,2007,30(5):1353-1366.
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[13]Hanger M,Johansen T A,Mykland G K,et al.Dynamic model predictive control allocation using CVXGEN.Control and Automation(ICCA),2011 9th IEEE International Conference on.IEEE,2011:417-422.
[2]S.Hu,Y.Chen,Analysis of pseudospectral methods applied to aircraft trajectory optimization.Journal of Rocket Propulsion,2014(5):61-68.
[3]Re-entry trajectory optimization using Radau pseudospectral method.Control Theory&Applications,2013,30(8).
[4]On-Line predictor-corrector reentry guidance law based on Gauss pseudospectral method.Journal of Astronautics,2011,(06):1249-1255.
[5]E.Yong,G.Tang,L.Chen.Rapid trajectory optimization for hypersonic reentry vehicle via Gauss pseudospectral method.Journal of Astronautics,2008,6(29):1766-1772.
[6]Jorris T,Schulz C,Friedl F,et al.Constrained trajectory optimization using pseudospectral methods.AIAA Atmospheric Flight Mechanics Conference and Exhibit.2008:6218.
[7]Benson D.A Gauss pseudospectral transcription for optimal control.Massachusetts Institute of Technology,2005.
[8]Q.Chen,Z.Wang,S.Chang,et al.Multiphase trajectory optimization for gun-launched glide guided projectiles.Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,2016,230(6):995-1010.
[9]F.Tan,H.Chen,M.Hou,et al.Model predictive trajectory tracking of a reentry hypersonic vehicle based on convex optimization.Control Conference(CCC),2013 32nd Chinese.IEEE,2013:4167-4171.
[10]Z.Lu,F.Tan.Online trajectory optimization for the terminal stage of reentry hypersonic vehicles.Harbin institute of technology,2014.6.
[11]Acikmese B,Ploen S R.Convex programming approach to powered descent guidance for mars landing.Journal of Guidance,Control,and Dynamics,2007,30(5):1353-1366.
[12]X.Liu,Z.Shen,P.Lu.Closed-Loop optimization of guidance gain for constrained impact.Journal of Guidance,Control,and Dynamics,2016.
[13]Hanger M,Johansen T A,Mykland G K,et al.Dynamic model predictive control allocation using CVXGEN.Control and Automation(ICCA),2011 9th IEEE International Conference on.IEEE,2011:417-422.