Solutions for Rapid Yaw Mechanisms for High Lift-over-drag (L/D) Hypersonic Vehicles

GoHypersonic Inc. (GHI) and the University of Dayton (UD/UDRI) propose to expand the Phase I effort to investigate methods to aerodynamically provide high lift-over-drag (L/D) interceptors with higher skid-to-turn terminal engagement performance than traditional finned cones. The Phase II effort would involve investigating hybrid control schemes that utilize lateral divert jets, maturing all aspects of our vehicle concept, performing thermomechanical testing on our aerodynamic controls in realistic flight regimes, and working with defense prime contractors to identify technology that can be transferred. Three large prime defense contractors have expressed interest in coordinating strategic risk reduction efforts in Phase II and serving as a transition partner beyond the Phase II. In Phase I, the team surveyed design considerations, established a set of baseline vehicle configurations, investigated controls configurations, down-selected to the most promising candidate of canard and strake, developed an aerodynamic database, evaluated notional intercept conditions for a long range intercept attempt, developed control laws, investigated fully controlled flight, estimated size, weight, and power of notional internal systems and internal vehicle layout, designed control actuation deployment mechanisms and control cradles, performed risk assessments, and compared maneuverability energy penalties and yaw time constants versus the baseline finned cone. The Phase I design outperformed traditional finned cone concepts and maintained higher L/D ratios. The designed vehicle was assessed to be realizable and that two interceptors likely package within the fairing of a Standard Missile-3. The trajectory simulations indicated that longer initial standoff ranges result in intercept engagements at altitudes between 27.5 to 42.5km. GHI’s interceptor was well controlled with aerodynamic control surfaces. GHI assessed the thermal environment, prepared plans for a notional thermomechanical test, and investigated tools developments that would be required for Phase II. In Phase II, GHI will refine the concept and evaluate the thermomechanical implications derived from utilizing deployable control surfaces, especially on the windward side. GHI is extending the design to a hybrid configuration with lateral divert thrusters to account for the decreased lateral displacements achievable by aerodynamic controls at altitudes above 40kilometers. The canard and strake approach provides force amplification utilizing the bow shock of the divert jet impinging on the vehicle and strake to provide additional lateral force. Finally, a focus on high-fidelity computational verification and validation and thermomechanical testing with UDRI will provide significant risk reduction. Approved for Public Release | 25-MDA-12052 (27 Mar 25)