An orbit transfer mission concept has been studied for a Space-Based Radar (SBR) where 40 kW required for radar operation is assumed available for orbit transfer propulsion. Arcjet, pulsed electrothermal (PET), ion, and storable chemical systems are considered for the primary propulsion. Transferring two SBR per shuttle flight to 1112 km/60 deg using electrical propulsion systems offers an increased payload at the expense of increased trip time, up to 2000 kg each, which may be critical for survivability. Trade offs between payload mass, transfer time, launch site, inclination, and height of parking orbits are presented.
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机译：已经针对空基雷达（SBR）研究了轨道转移任务概念，其中假定雷达操作所需的40 kW可用于轨道转移推进。对于主要推进器，考虑使用Arcjet，脉冲电热（PET），离子和可存储化学系统。使用电动推进系统将每架航天飞机的两个SBR转移到1112 km / 60度，可以提供更大的有效载荷，但要花费更长的行程时间（每次最多2000 kg），这对于生存能力至关重要。提出了有效载荷质量，转移时间，发射地点，倾斜度和停车轨道高度之间的权衡。
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