RS-Satellites Propulsion Subsystem Performance Sizing Via Design Plane Technique, a Generic Method

Remote sensing satellites propulsion subsystem preliminary design based on performance sizing is discussed. The process is a fairly complicated one considering a variety of operational as well as performance requirements. This research aims to reduce the number of iterations required by the current practice to reach a compromise. It is based on a rapid-sizing method that helps lessen lengthy iteration cycles. The proposed technique, similar to such class of preliminary design processes, leads to an acceptable approximation that must be properly conveyed to other disciplines involved for further elaborations. With proper selection of design and performance parameters together with fundamental relations, design boundaries are established; while the role of boundaries is to limit the design space, and to minimize the number of design cycles as a result. With the help of a suitable case-study, we demonstrate the effectiveness of the approach. Further investigations might be necessary for the cases where a greater number of uncertainties are involved.