Gil-Fernández Jesús, Graziano Mariella, Gómez-Tierno M A, Milic E
GMV S.A., Isaac Newton 11, P.T.M. Tres Cantos, 28760 Madrid, Spain.
Ann N Y Acad Sci. 2004 May;1017:307-27. doi: 10.1196/annals.1311.017.
Several techniques have been developed to obtain optimum trajectories with low-thrust propulsion. However, few low-thrust guidance schemes have been investigated to fly the reference optimum trajectories. The guidance algorithm successfully employed in the DeepSpace1 mission was the first approximation through the presented guidance schemes, valid for various interplanetary low-thrust trajectories, independently of the optimization technique they result from. A method is presented to transform any given thrust profile to a thrust law defined by a finite set of control variables. This law allows the definition of a control vector to be optimized for the guidance purposes. Simulations were carried out to compare the performances of the algorithms to very different missions, such as SMART-1 and BepiColombo. The good performance of the enhanced guidance schemes prove the generic applicability of the algorithm. Parametric analysis allows the assessment of stability and robustness of the schemes and the sensitivity to certain parameters. Table.
已经开发了几种技术来获得低推力推进的最优轨迹。然而，很少有低推力制导方案被研究用于飞行参考最优轨迹。在深空1号任务中成功采用的制导算法是通过所提出的制导方案的一阶近似，适用于各种行星际低推力轨迹，与它们所源自的优化技术无关。提出了一种方法，将任何给定的推力曲线转换为由一组有限控制变量定义的推力定律。该定律允许定义一个控制向量，以便为制导目的进行优化。进行了仿真，以比较这些算法在诸如SMART-1和贝皮科伦坡等非常不同任务中的性能。增强制导方案的良好性能证明了该算法的通用适用性。参数分析允许评估方案的稳定性和鲁棒性以及对某些参数的敏感性。表。
