The invention discloses a modeling reachable orbit element calculation and degraded orbit decision-making method and device, a medium and a product, and relates to the field of rocket reachable orbit element calculation, and the method comprises the steps: obtaining an initial flight state parameter, a target orbit element and a safety height constraint of a rocket under a non-fatal thrust descending condition; establishing a modeled optimal control problem model by combining a rocket dynamics differential equation and an operation process constraint condition, performing convexity to obtain a convex optimal control sub-problem, performing discretization on the convex optimal control sub-problem, and introducing a slack variable to obtain a convex optimization sub-problem; and setting mode coefficients of the rocket in different modes, performing iterative solution on the convex optimization sub-problem by adopting a convex optimization algorithm to obtain reachable orbit elements of different modes, performing decision making on rocket orbit degradation, obtaining final rocket reachable orbit elements, and determining a reference trajectory of rocket operation. According to the method, the calculation efficiency of reachable orbit elements and the task adaptability can be improved.
本发明公开一种模式化可达轨道要素计算与降级轨道决策方法、装置、介质及产品,涉及火箭可达轨道要素计算领域,方法包括获取火箭在非致命推力下降情况下初始飞行状态参数和目标轨道要素与安全高度约束,并结合火箭动力学微分方程和运行过程约束条件建立模式化最优控制问题模型并凸化,得到凸最优控制子问题,对凸最优控制子问题进行离散化,引入松弛变量得到凸优化子问题;设定火箭在不同模式的模式系数,采用凸优化算法对凸优化子问题进行迭代求解,得到不同模式的可达轨道要素,对火箭轨道降级进行决策,得到最终的火箭可达轨道要素,确定火箭运行的参考轨迹。本发明可提高可达轨道要素的计算效率和提高任务适应性。
Modeling reachable orbit element calculation and degraded orbit decision method and device, medium and product
一种模式化可达轨道要素计算与降级轨道决策方法、装置、介质及产品
2024-09-10
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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