采用滚动伪谱优化的组合动力飞行器上升段制导方法
Ascent Guidance Method for Combined-cycle Vehicle Based on Receding Horizon Pseudo-spectral Optimization
查看参考文献17篇
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文摘
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为满足多约束条件下组合动力飞行器上升过程对制导自适应能力的需求,研究了采用滚动伪谱优化的闭路制导方法。在双层滚动优化框架下进行制导,运用分段伪谱法在线实时计算制导指令,根据状态反馈实现指令的快速迭代更新;引入了网格更新策略改进算法效率,基于实时偏差在线自适应调整制导周期。仿真结果表明,所提制导方法具有可行性,能有效抑制模型参数的不确定性及外界干扰的影响,制导精度满足任务需求;单次指令解算时间在百毫秒量级,该方法具备一定的工程应用价值。 |
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其他语种文摘
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To meet the requirement of adaptability of the ascent guidance of combined-cycle vehicle under multi-constraints,a closed-loop guidance method based on receding horizon pseudo-spectral optimization was studied. The guidance was carried out under the framework of the hierarchy-structure receding horizon optimization,which applied segmented pseudo-spectral method to generate the online real-time command, and the command can be updated iteratively with the state feedback. The mesh update strategy was introduced to improve the efficiency of the algorithm,and the guidance cycle was adjusted adaptively based on real-time state deviation. Simulation results show that the proposed guidance method is feasible,and it can effectively suppress the influence of model parameter uncertainty and external interference. The guidance accuracy meets the mission requirements. The calculation time is in the order of hundred milliseconds. Thus, the method is of certain value for engineering application. |
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来源
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弹道学报
,2021,33(4):1-8 【核心库】
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DOI
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10.12115/j.issn.1004-499X(2021)04-001
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关键词
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飞行器
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制导
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组合动力
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滚动优化
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分段伪谱法
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离散网格更新
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多约束
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地址
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国防科技大学空天科学学院, 湖南, 长沙, 410073
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1004-499X |
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学科
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航天(宇宙航行) |
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文献收藏号
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CSCD:7117788
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参考文献 共
17
共1页
|
|
1.
姚德清. 空天飞行器制导控制技术研究进展与展望.
宇航学报,2020,41(7):850-859
|
CSCD被引
13
次
|
|
|
|
|
2.
佘文学. 组合动力空天飞行器制导技术发展分析.
战术导弹技术,2020(5):52-65
|
CSCD被引
5
次
|
|
|
|
|
3.
Hanson J M. Ascent guidance comparisons.
Journal of the Astronautical Science,1995,43(3):307-326
|
CSCD被引
6
次
|
|
|
|
|
4.
张志国. 应用伪谱法的运载火箭在线制导方法研究.
宇航学报,2017,38(3):262-269
|
CSCD被引
25
次
|
|
|
|
|
5.
Lu P. Closed-loop endoatmospheric ascent guidance.
Journal of Guidance,Control,and Dynamics,2003,26(2):283-294
|
CSCD被引
32
次
|
|
|
|
|
6.
Lu P. Highly constrained optimal launch ascent guidance.
Journal of Guidance Control,and Dynamics,2010,33(2):404-414
|
CSCD被引
39
次
|
|
|
|
|
7.
杨良. 多约束在线高斯伪谱末制导方法.
弹道学报,2014,26(3):98-103
|
CSCD被引
4
次
|
|
|
|
|
8.
崔乃刚. 基于混合优化的运载器大气层内闭环制导方法.
中国惯性技术学报,2015,23(3):328-333
|
CSCD被引
7
次
|
|
|
|
|
9.
Ross I M. A review of pseudospectral optimal control: from theory to flight.
Annual Reviews in Control,2012,36(2):182-197
|
CSCD被引
25
次
|
|
|
|
|
10.
Ross I M. Optimal feedback control: foundations,examples,and experimental results for a new approach.
Journal of Guidance,Control,and Dynamics,2008,31(2):307-321
|
CSCD被引
11
次
|
|
|
|
|
11.
Bollino K P. Optimal nonlinear feedback guidance for reentry vehicles.
AIAA Guidance, Navigation, and Control Conference and Exhibit,2006:1-20
|
CSCD被引
1
次
|
|
|
|
|
12.
张友安. 基于伪谱法的自由采样实时最优反馈控制及应用.
控制理论与应用,2012,29(9):1151-1156
|
CSCD被引
10
次
|
|
|
|
|
13.
闫循良. 基于改进伪谱反馈控制的远程变轨闭环制导.
宇航学报,2016,37(1):84-93
|
CSCD被引
5
次
|
|
|
|
|
14.
许东欢. 基于伪谱法的空天飞行器上升段非线性闭环最优制导算法.
战术导弹技术,2017(4):57-65
|
CSCD被引
1
次
|
|
|
|
|
15.
Patterson M A. A ph mesh refinement method for optimal control.
Optimal Control Applications & Methods,2015,36(4):398-421
|
CSCD被引
21
次
|
|
|
|
|
16.
Murillo O J.
A fast ascent trajectory optimization method for hypersonic air-breathing vehicles,2010
|
CSCD被引
1
次
|
|
|
|
|
17.
Hager W W. Convergence rate for a Radau hp collocation method applied to constrained optimal control.
Computational Optimization and Applications,2019,74(1):275-314
|
CSCD被引
1
次
|
|
|
|
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