关键词: 离子推力器;有效载荷比;深空探测;等离子体特性;性能曲线

Abstract: In order to estimate and improve the payload capacity of spacecraft, combined with the space transportation system theory and the ion thruster discharge model, the spacecraft payload capacity of the deep space exploration mission with the ion propulsion system as the main power source was analyzed. Through the theoretical derivation, the potential relationship between the payload fraction and the parameters of the deep space exploration mission and the performance parameters of the electric propulsion system are constructed and revealed. The results show that the smaller power plant specific mass, the larger the optimal payload fraction that can be achieved by the spacecraft. The payload fraction is positively correlated with the extracted ion fraction, the primary electron utilization factor and the length of the task time. When the ion-thruster system can achieve a higher payload fraction, higher working fluid utilization is required as a support.

Key words: Ion thruster;Payload fraction;Deep space exploration;Plasma performances;Characteristic curve