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首页> 外文会议>AIAA Guidance, Navigation and Control Conference Pt.2, Aug 1-3, 1994, Scottsdale, AZ >ALTITUDE - PATH ANGLE CONTROL DURING AEROSPACE PLANE ASCENT
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ALTITUDE - PATH ANGLE CONTROL DURING AEROSPACE PLANE ASCENT

机译：海拔-航空航天飞机上升过程中的航迹角控制

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The ascent problem for an aerospace plane is addressed. Only the post-transonic portion of the atmospheric ascent and only the translational longitudinal motion are considered. The two time-scale structure of the dynamics allows the separation of the energy and mass dynamics and control on a slow time-scale from the altitude and flight-path angle dynamics and control on a fast time-scale according to the singular perturbation method. The focus in this paper is the control of the fast variables, altitude and flight path angle, in the left boundary-layer. Zeroth-order, minimum-fuel solutions are computed for a one-parameter family of soft dynamic pressure constraints. As the parameter is decreased toward zero, the constraint approaches a hard inequality constraint and the corresponding solution approaches the finite time hard constraint solution. An operationally desirable solution from the soft constraint family is selected and used as a basis for constructing a feedback control. The nature of the soft constraint formulation facilitates the construction of the feedback control which approximates the optimal control but is much easier to compute. Comparisons of the optimally controlled boundary-layer trajectories and the sub-optimally, feedback controlled boundary-layer trajectories are presented for a particular aerospace plane model. The performance of the feedback control is essentially as good as that of the optimal control.
机译：解决了航空航天飞机的上升问题。仅考虑大气上升的跨音速后部分，并且仅考虑平移纵向运动。动力学的两个时标结构允许将能量和质量动力学分开，并根据奇异摄动法从海拔高度和飞行路径角度动力学中控制慢时标，并在快速时标中进行控制。本文的重点是在左侧边界层控制快速变量，高度和飞行路径角度。针对软动态压力约束的一参数系列计算零阶最小燃料解。当参数朝零减小时，约束接近硬不等式约束，相应的解决方案接近有限时间硬约束解决方案。从软约束族选择​​可操作的解决方案，并将其用作构建反馈控制的基础。软约束公式的性质有利于构建反馈控制，该反馈控制近似于最佳控制，但更易于计算。针对特定的航空航天飞机模型，给出了最优控制边界层轨迹与次优反馈控制边界层轨迹的比较。反馈控制的性能基本上与最佳控制的性能一样好。

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