Primary propulsion of electrothermal, ion, and chemical systems for space-based radar orbit transfer | Zendy

Suhang Wang | Zendy; P. J. Staiger | Zendy

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Primary propulsion of electrothermal, ion, and chemical systems for space-based radar orbit transfer

Author(s) -

Suhang Wang,

P. J. Staiger

Publication year - 1985

Publication title -

21st joint propulsion conference

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1985-1477

Subject(s) - propulsion , orbit (dynamics) , primary (astronomy) , aerospace engineering , ion thruster , radar , electrically powered spacecraft propulsion , space (punctuation) , remote sensing , astrobiology , physics , computer science , engineering , astronomy , geology , operating system

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 eiectrical 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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