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首页> 外文期刊>Journal of Spacecraft and Rockets >Maximizing Payload Mass Fractions of Spacecraft for Interplanetary Electric Propulsion Missions
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Maximizing Payload Mass Fractions of Spacecraft for Interplanetary Electric Propulsion Missions

机译：最大化用于行星际电动推进任务的航天器的有效载荷质量分数

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摘要

Optimization of a spacecraft's interplanetary trajectory and electric propulsion system remains a complex and difficult problem. Simultaneously solving for the optimal trajectory, power level, and exhaust velocity can be difficult and time consuming. If the power system's technology level is unknown, multiple optimizations must be conducted to map out the trade space. Trajectories with constant-power, solar-power, variable-specific-impulse, and constant-specific-impulse low-thrust propulsion systems are analyzed and optimized. The technological variables, power system specific mass, propellant tank coefficient, structural coefficient, and the launch vehicle are integrated into the cost function allowing for maximization of the payload mass fraction. A classical solution is reviewed that allows trade studies to be conducted for constant-power, variable exhaust velocity systems. The analysis is expanded to include bounded-power constant specific impulse systems and solar electric propulsion spacecraft with constant and variable exhaust velocity engines. The cost function and mass fractions are dimensionless to allow for scaling of the spacecraft systems.
机译：优化航天器的行星际轨迹和电力推进系统仍然是一个复杂而困难的问题。同时求解最佳轨迹，功率水平和排气速度可能既困难又耗时。如果电力系统的技术水平未知，则必须进行多次优化以规划交易空间。分析并优化了具有恒定功率，太阳能，可变比冲量和恒定比冲量低推力推进系统的轨迹。技术变量，电力系统的特定质量，推进剂储罐系数，结构系数和运载火箭被集成到成本函数中，从而使有效载荷质量分数最大化。回顾了经典的解决方案，该解决方案允许对恒定功率，可变排气速度系统进行贸易研究。分析扩展到包括有功功率恒定比脉冲系统和具有恒定和可变排气速度发动机的太阳能推进航天器。成本函数和质量分数是无量纲的，以允许对航天器系统进行缩放。

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