Controlling Stability and Load Limits of Aerodynamically Induced Forces on Very Large Assymetric Fairing Designs

The proposed program addresses the development of a very large asymmetric fairing that will allow considerably larger payloads to be launched than is currently possible with cylindrical fairings. This fairing would be usable on existing launch vehicles without extensive modifications of those launch vehicles and would minimize in-flight instability conditions, reduce lateral force induced peak stresses in the fairing, and minimize the effects on the launch vehicle GNC system. An analysis-driven design approach will be used to evaluate a series of geometric concepts for the fairing before selecting one for further development in a Phase II program. Extensive CFD analysis and shape optimization of these concepts will be carried out to identify one or two geometries which result in the desired aerodynamic and launch vehicle interface loads. The dynamic load response of these geometries will then be evaluated and a preliminary structural design defined. Panel flutter and buffet concerns will also be addressed. The result of this Phase I program will be a very large asymmetric fairing design concept which shows a very high probability of meeting all requirements and which can serve as the basis for a more detailed Phase II design effort, including prototype development.