Combined System-Trajectory Design for Geostationary Orbit Platforms on Hybrid Transfer

被引:4
作者
Ceccherini, Simone [1 ]
Mani, Karthik, V [1 ]
Topputo, Francesco [1 ]
机构
[1] Polytech Univ Milan, Dept Aerosp Sci & Technol, I-20156 Milan, Italy
关键词
PROPULSION; OPTIMIZATION; DEGRADATION; SPACE;
D O I
10.2514/1.A35012
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
A novel methodology for a combined systems-trajectory optimization for a geostationary equatorial orbit (GEO) platform is proposed to obtain comprehensive design solutions. A combined chemical-electric propulsion system is used to execute hybrid high-thrust/low-thrust trajectory transfer to GEO, thereby balancing the overall system mass and transfer time. A systematic and payload-centric mission design provides a new set of design options to deliver tailored solutions to customized payloads. The hybrid trajectory characterization and spacecraft systems design find the required platform launch mass to deliver a GEO platform with a defined final mass and operational power. Elements of the system design are combined with those of multispiral low-thrust trajectory optimization as well as radiation absorption and solar array degradation to provide a comprehensive design solution. The result is a wide set of solutions to reach GEO, where fully chemical and fully electric transfers represent the boundaries of the hybrid transfer trade space. A payload throughput power of 20 kW entails a spacecraft mass in GEO between 4000 and 4550 kg, an initial thrust-to-mass ratio range of 1.7 - 2.3 x 10(-4) m/s(2), and a cover-glass thickness between 4 and 24 mils to guarantee a minimum end-of-life/beginning-of-life power ratio of 85%. In addition, all-electric solutions from different injection orbits yield transfers to GEO with a time of flight of 60-150 days and an initial mass for the platform of 4400-5500 kg.
引用
收藏
页码:448 / 466
页数:19
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