Aero-Structural Coupling and Sensitivity of a Joined-Wing SensorCraft
Abstract
This presentation presents information on the Joined-Wing SensorCraft, including a history of the Joined Wing, SensorCraft background, configuration issues, parametric modeling and design method, aerodynamic panel model (i.e., PanAir and FlightLoads), structural finite element model, related studies, and conclusion. The Lockheed Martin new aircraft concept of the Joined Wing is intended to reduce drag, improve stability, strengthen the wing, and prevent flutter. The Air Force's requirement is for an unmanned aerial vehicle (UAV) for continuous, long-term intelligence, surveillance, and reconnaissance missions. The Joined Wing magnifies the sensor footprint by providing a 360 degree coverage of the area of interest. The SensorCraft aircraft is designed around the desired sensor package, rather than the sensor package being designed around an already existing platform. The design environment for the Joined Wing is object-oriented with native geometric modeling. The process uses the PanAir Aerodynamic Solver and the MSC FlightLoads Solver. Related research that is reviewed involves stochastic finite element analysis, reliability-based structural design, and structurally integrated conformal antennas. Nonlinear analysis was critical in designing the Joined Wing. The authors conclude that the Joined-Wing SensorCraft presents designers with unique technical issues. The next steps to tackle are the unsweep outboard or aft wing, design for buckling and nonlinear FSC, tailoring the aft wing buckling to alleviate flexible loads, and verifying aerodynamic results with CFD.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 05, 2002
- Accession Number
- ADA429511
Entities
People
- Jennifer Schwartz
- Maxwell Blair
- Robert A Canfield
Organizations
- Air Force Institute of Technology