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Assume that the lander DPS is characterized by the given constant \(I_{sp}\) and \(F_{max}\) . Then the exhaust velocity, c and the maximum mass-flow rate, \(\beta _{max}\) are \(c = I_{sp}g_0, ~ \beta _{max} = F_{max}/c.\) Similar to the Apollo DPS constraints, it is assumed that the maximum allowable thrust is not achievable on the descent trajectory. A constant exhaust velocity implies that the mass-flow rate satisfies the condition \(\beta \le \beta _{max}.\) Consider the planar motion of the lander center of mass in a Newtonian field.

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Optimal Control Problem and Extremals

  • 章节

  • 发表日期：

    2026年

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  • Dilmurat M. Azimov,
  • Robert H. Bishop

摘要

Assume that the lander DPS is characterized by the given constant \(I_{sp}\) and \(F_{max}\) . Then the exhaust velocity, c and the maximum mass-flow rate, \(\beta _{max}\) are \(c = I_{sp}g_0, ~ \beta _{max} = F_{max}/c.\) Similar to the Apollo DPS constraints, it is assumed that the maximum allowable thrust is not achievable on the descent trajectory. A constant exhaust velocity implies that the mass-flow rate satisfies the condition \(\beta \le \beta _{max}.\) Consider the planar motion of the lander center of mass in a Newtonian field.