Today's rocket chemical propulsion systems for in-orbit use rely on toxic liquid rocket propellants. The need for environmentally-friendly spacecraft and upper-stage high-performance engines can be seen. This paper covers the topic of optimisation of Geostationary Transfer Orbit apogee bipropellant rocket engines, using highly concentrated hydrogen peroxide as oxidiser and kerosene as fuel. Performance, structural and heat transfer analyses are described. In particular a detailed mass model for hydrogen peroxide kerosene rocket propulsion systems is discussed. Special care is given to bipropellant rocket systems using staged combustion configurations where a catalyst bed is utilised. The optimisation process was conducted using Matlab software. The ultimate goal of this work was the development of a tool for hydrogen peroxide hydrocarbon bipropellant rocket propulsion system optimisation in terms of given requirements and design constraints. The presented software may enable the development of advanced, environmentally-friendly satellites and highly-efficient architectures utilising storable green propellants, including small upper-stage propulsion systems. (C) 2018 Elsevier Masson SAS. All rights reserved.
展开▼
