Controlling Stability and Load Limits of Aerodynamically Induced Forces on Very Large Asymmetric Fairing Designs
Agency / Branch:
DOD / USAF
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 innovative geometric design was developed in Phase I using an analysis-driven design approach. Extensive CFD analysis and shape optimization was used to achieve desired aerodynamic and launch vehicle interface loads. In Phase II this design will be further optimized and validated through wind tunnel testing of a scale model. A detailed structural design will then be developed which takes advantage of the latest large fairing manufacturing technologies. The end product of Phase II will be a fully detailed structural design of a half scale fairing prototype which can be taken to manufacturing as part of a Phase III program. This fairing design will demonstrate greatly increased payload capacity, low weight, and integrate existing commercial-off-the-shelf separation and isolation system components to minimize development costs.
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ATA ENGINEERING, INC.
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