Integrated Flight Control Systems for Kinetic Kill Vehicles with Novel Internal Actuators

Development of integrated flight control systems for kinetic kill vehicles incorporating novel internal actuators is proposed. The benefits of the new internal actuators are that they are contained entirely within the airframe and do not require mass expulsion. The actuator technology can be used in both the atmosphere and in vacuum, and in any speed range. However, due to the complexity of the dynamics they introduce, integrated design of flight control systems are essential for satisfactory vehicle performance. Unlike the previously reported internal actuation technology, the methodologies advanced in this proposal are effective even in the absence of any external thrust or aerodynamic forces. Phase I research will demonstrate the feasibility of the proposed internally actuated integrated flight control concepts using high-fidelity nonlinear simulations. Limited-scale Monte-Carlo simulations will be carried out to demonstrate the flight control system robustness to parameter variations and disturbances. Phase II work will use the Phase I research results to develop a working model of the internally actuated kinetic kill vehicle. Operation of the working model will then be demonstrated in a multi-axis motion table. Phase III research will develop and flight test an internally actuated kinetic kill vehicle of interest to the MDA.