Experimental Investigation of a Suborbital Reusable Booster Concept with a Body Flap

Reusable Boosters Systems (RBS) are potential concept for the future of responsive space access. This project investigates the static stability in the low subsonic flight regimes of a suborbital booster concept during the approach and pre-landing phases of flight prior to landing gear deployment. Subsonic wind tunnel testing is performed on a model of the reusable booster in order to determine the aerodynamic effects as well as static stability of the model for different control surface configurations. This model has some minor issues with longitudinal stability at higher angles of attack as well as directional stability which could be managed with feedback control systems. A body flap extending from the main fuselage is a design feature used to help control the vehicle’s pitch. The vehicle is capable of safe control through approach and landing using the control surfaces in place.