升力式飞行器助推段多约束弹道优化设计
Optimization Design of Trajectory in Boost Phase of Lift Vehicle With Multi-constraints
查看参考文献12篇
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文摘
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升力式飞行器助推段弹道设计面临着复杂大气飞行环境下多约束耦合条件下的运载能力优化难题,需要在满足分离高度、攻角量值与变化率限幅、入轨点高度与倾角等约束下,通过设计助推段程序角,使得入轨点速度最大。为了寻求一种快速解决这一问题的工程设计方法,以三级固体运载器为研究对象,提出了升力式飞行器助推段多约束弹道设计方法,通过设计助推段弹道模式制定了设计变量,梳理确定了助推段约束条件,建立了多约束下以入轨速度最大为目标的优化模型。通过分析设计变量与约束条件的耦合关系制定了高效的优化流程,并以牛顿迭代法确定优化初值,且以序列二次规划法开展优化仿真。仿真获得了满足多约束条件下的优化解,入轨速度提高了3.1%,验证了升力式飞行器助推段弹道设计方法的正确性和优化求解流程的有效性。升力式飞行器助推段多约束弹道优化设计方法具有较强的工程实用性,模型建立方法与优化求解流程可为其他优化问题提供参考。 |
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其他语种文摘
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The design of trajectory in boost phase of the lift vehicle is facing the difficult problem of carrying capacity optimization under the coupling condition of multiple constraints in the complex atmospheric flight environment. It is necessary to design the program angle of the boost phase to maximize speed of entering orbit under the constraints of stages separation height,angle of attack limit,height of the orbit entry point,etc. In order to find an engineering design method to quickly solve this problem, taking the three-stage solid launch vehicle as the research object, the multi-constraint trajectory design method in boost phase of the lift vehicle was put forward. The design variables were formulated by designing the flight trajectory mode of the boost phase,and the constraint conditions of the boost phase were determined. The optimization model aiming at the maximum orbital speed under multi constraints was built. By analyzing the coupling relationship between design variables and constraints,an efficient optimization process was formulated. The optimization initial value was determined by Newton iterative method,and the optimization simulation was carried out by sequential quadratic programming method. The optimal solution satisfies the multi-constraint conditions,and the orbit entry speed increases by 3.1%,which verifies the correctness of the trajectory design method and the effectiveness of the optimization process. The multi-constraint trajectory optimization design method in boost phase of lift vehicle has strong engineering practicability. The modeling method and optimization process can offer reference for other optimization problems. |
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来源
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弹道学报
,2022,34(1):17-21 【核心库】
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DOI
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10.12115/j.issn.1004-499X(2022)01-003
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关键词
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升力式飞行器
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助推段
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弹道优化
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地址
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北京宇航系统工程研究所, 北京, 100076
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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:7186186
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参考文献 共
12
共1页
|
|
1.
Gath P F. Optimization of launch vehicle ascent trajectories with path constraints and coast arcs.
Journal of Guidance Control & Dynamics,2001,24(2):296-304
|
CSCD被引
23
次
|
|
|
|
|
2.
Jiang Z. Reentry trajectory optimization for hypersonic vehicle satisfying complex constraints.
Chinese Journal of Aeronautics,2013,26(6):1544-1553
|
CSCD被引
54
次
|
|
|
|
|
3.
洪蓓. 升力式飞行器多阶段轨迹优化改进策略研究.
导弹与航天运载技术,2013(2):8-12
|
CSCD被引
2
次
|
|
|
|
|
4.
Guan Chengqi. Multiphase Path-Constrained Trajectory Optimization for the Boost-Glide Vehicle Via the Gauss Pseudospectral Method.
Journal of Astronautics,2010,31(11):2512-2518
|
CSCD被引
6
次
|
|
|
|
|
5.
崔乃刚. 助推-滑翔飞行器助推段最优轨迹快速生成方法.
弹道学报,2013,25(2):33-38
|
CSCD被引
4
次
|
|
|
|
|
6.
黄育秋. 升力式再入飞行器多约束多阶段弹道优化设计.
哈尔滨工业大学学报,2011,43(7):144-148
|
CSCD被引
6
次
|
|
|
|
|
7.
刘欣. 助推-滑翔导弹弹道优化与总体参数分析.
弹道学报,2012,24(3):43-48
|
CSCD被引
7
次
|
|
|
|
|
8.
李瑜. 助推-滑翔导弹最大射程优化.
弹道学报,2008,20(4):53-56
|
CSCD被引
9
次
|
|
|
|
|
9.
贾沛然.
远程火箭弹道学,2009
|
CSCD被引
12
次
|
|
|
|
|
10.
龙乐豪.
总体设计,1989
|
CSCD被引
16
次
|
|
|
|
|
11.
李新国. 基于修正Newton法的固体火箭能量管理弹道设计.
固体火箭技术,2013(1):1-5
|
CSCD被引
11
次
|
|
|
|
|
12.
Gill P E. SNOPT: an SQP algorithm for large-scale constrained optimization.
SIAM Review,2002,12(4):979-1006
|
CSCD被引
160
次
|
|
|
|
|
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