Vertical Ascent to Geosynchronous Orbit with Constrained Thrust Angle
Vertical Ascent to Geosynchronous Orbit with Constrained Thrust Angle
复制标题
受约束推力角垂直上升至地球同步轨道
DOI：
10.2514/2.3527
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发表时间：
2000
影响因子：
1.6
通讯作者：
J. Chern
中科院分区：
文献类型：
--
作者：
Z. Hong;Fu;J. Chern
本文讨论了固体火箭助推激光推进系统在地球同步轨道有效载荷发射时，在推力角约束条件下的总有效载荷比。提出了一种轨道成形方法，用于在赤道面内建立垂直上升轨道。存在一个推力角，在该推力角下，有效载荷比（最终质量与初始质量之比）将最大化。只有当地面站能够提供所需的峰值激光功率时，才能获得这一最大有效载荷。现在，如果峰值激光功率被限制在较低水平，则可以获得的有效载荷比也将较低。当可以提供的峰值激光功率太低时，在发射的初始阶段推重比将小于1。为了保持发射系统的性能，我们在模型中包括一个捆绑式固体火箭助推器，以补偿系统的推力损失。结果表明，该方法可以显著降低罚金。
A discussion is presented about the overall payload ratio of a solid-rocket-booster-assisted laser propulsion system forgeosynchronous-Earth-orbit payload launch with thrust-angleconstraint. A trajectory shaping method is used for constructing the vertical ascent trajectory in the equatorial plane. There is a thrust angle under which the payload ratio (ratio of e nal mass to initial mass ) is to be maximized. This maximum payload can be obtained only when the ground station can provide the required peak laser power. Now, if the peak laser power is limited to a lower level, the payload ratio that can be obtained will also be lower. When the peak laser power that can be provided is too low, the thrust-to-weight ratio will be less than one at the initial phase of the launch. To keep the performance of the launching system, we include in the model a strap-on solid rocket booster to compensate the system for thrust loss. It is found that the penalty can be reduced signie cantly.