摘要
为了得到洲际助推-滑翔导弹的最优弹道,给出了弹道分段准则,分析了适合的弹道形式;建立了纵平面运动模型、推力模型、气动模型与气动热模型.针对其弹道优化问题,在考虑级间分离、跨声速区、控制、动压、法向过载、突防、弹头鼻头滞点热率与壁温等约束条件下,建立了助推段与滑翔段的多约束多阶段弹道优化模型.利用直接打靶法将此最优控制模型转化为非线性规划问题,并采用序列二次规划算法进行解算.仿真给出并比较了3种情况的弹道优化结果.分析表明,助推-滑翔-弹跳弹道更适合于尖鼻头洲际助推-滑翔导弹.
To obtain the optimal trajectory for intercontinental boost-glide missile, the trajectory was divided into three phases by flight states. A feasible and novel trajectory was proposed. The dynamic model, the propulsion model, the aerodynamic model and the aerothermodynamie model were built. With the constraints of stage separation, transonic phase, control, dynamic pressure, normal overload, anti-defense, heating rate and wall temperature at stagnation point of nose tip for warhead, the trajectory optimization models of boost and glide phases were established, i. e. , multi-constraints multi-phase trajectory optimization model. By direct shooting method, the associated optimization problem was converted into a nonlinear programming problem, which was solved through a sequential quadratic programming solver. The numerical results of the trajectory optimization were compared among three cases. Results show that boost-glide-skip trajectory is more suitable for intercontinental boost-glide missile with sharp-nose glide-warhead.
出处
《弹道学报》
EI
CSCD
北大核心
2010年第2期52-56,共5页
Journal of Ballistics
关键词
洲际助推-滑翔导弹
弹道优化
非线性规划
intercontinental boost-glide missile
trajectory optimization
nonlinear programming
