Solid upper stage design process using finite burn maneuvers for low Earth orbit–geosynchronous Earth orbit transfer phase

Abstract

This article proposes a new approach in designing a two-stage solid propulsion transfer vehicle. The upper stage’s function is to deliver satellites or cargoes to the final orbit in space to accomplish the mission of transfer. The upper stage comprises a two-stage solid propulsion system. The disciplines of propulsion, mass properties and trajectory are integrated based on finite burn assumption to produce a high integrity model of the entire vehicle. Propulsion is designed in such a way so as to deliver optimum burn time, thrust magnitude history and thrust direction history. Fuel mass is the impetus driver on performance and weight, and so considered as core of design process. Therefore, we want to minimize gross mass through optimization of fuel consumption. In this article, sizing the vehicle uses a unique finite burn assumption. The novel approach considered here, produced satisfactory results for test case. This method provides designers with an efficient and powerful approach in space systems designing.

Keywords

Space systems engineering design process upper stage optimal control

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