A multimode propulsion control system concept has been developed for the remotely piloted research vehicle of the NASA Highly Maneuverable Aircraft Technology program. The concept is based on the retention of most of the bill-of-materials control hardware, and will allow the implementation of flight/propulsion control coupling, high and normal flow stability margin operating modes, and rapid and normal thrust response modes. Description of the control system, the airborne control components, and the ground generated and displayed signals is given in this paper.
