Abstract
The highly reliable design methodology is strongly required at the conceptual design phase to achieve the highly reliable space transportation systems, especially the propulsion systems. Some catastrophic failures did affect severely the schedule delays and cost overrun at the later development phase, moreover caused some losses of mission and vehicle (LOM/LOV) at the operational phase. This design methodology for highly reliable liquid rocket engine has been preliminarily established and studied. It is applied to develop the conceptual design process of the health monitoring and management system (HM/MS) at the operational phase in this paper. The critical failure modes in the whole engine system are clarified to estimate the design reliability and to prevent failure occurrence. Some variables associated with them are extracted to monitor whether the critical functions will be lost or not during the engine or mission operation. The conceptual design process of health monitoring and management system for liquid rocket engine is proposed and discussed in this paper.
