Optimization of Launch Vehicle Energy Storage 2002-01-3207
An innovative approach is presented to reduce the required energy storage mass for reusable launch vehicle (RLV) applications that plan to use electrically powered actuation of flight control surfaces.
Results from trade studies are presented to show the benefits of new configurations to reduce mass and meet both reliability and fault tolerance requirements. Results will show how the optimum configuration can be determined.
Extensions to this original work have demonstrated its practicality for aerospace applications. This includes reducing the complexity of the control required to manage the power system interconnects. The distribution system allows autonomous operation and better power quality during transient events and fault clearing. Additional control elements can be added to improve system efficiency during nominal operating conditions.
Possible applications include RLV designs with high peak-power requirements such as electro-mechanical actuators (EMAs) and electro-hydraulic actuators (EHAs). The results presented will include data on how the system provides high reliability and yet also minimizes mass and thermal heat generation.