Flight dynamics and stability and control characteristics of the X-33 technology demonstrator vehicle

Abstract

This paper presents the flight dynamics and stability and control characteristics of the X-33 vehicle. The vehicle model is based on aerodynamic data obtained from wind tunnel testing which includes power effects during ascent phase of the flight. Mathematical modeling of the Aerospike propulsion system and the reaction control systems are also included. Stability characteristics of the vehicle are presented for various flight regimes. Flight dynamic characteristics of the vehicle is based on linearized models of the vehicle. They are shown in this paper for the second flight trajectory which is to be flown from Edwards Air Force Base in California to Michael Army Air Field in Utah. This trajectory, designated as Michael-C, is designed to provide a flight profile with sufficient hypersonic Mach numbers to generate an aerothermal environment that produces the maximum catalytic aeroheating for the validation of the X-33 technology development. Analytical results are provided for three phases of the flight: Ascent, Entry and Terminal Area Energy Management (TAEM). Metiiods for estimating control power requirements to achieve desirable level of static stability are presented.