Lead Lockheed Martin Loads and Dynamics engineer for the Pad Abort 1 test flight of the Launch Abort System (LAS) which includes the LAS and a NASA boilerplate Crew Module (CM). Performed and checked shock and vibration analyses and led the team in the specification development for CM and LAS components. Provided support for component shock and vibration acceptance and qualification testing. Mentored engineers at Lockheed and NASA and worked to develop a team approach to the analysis process. Worked close with NASA and Orbital engineers to help resolve problems resulting from the extreme vibroacoustic environments induced by the LAS motor.

Cognizant Engineer for Pegasus launch vehicle environments and the avionics structure. Analyzed flight and test data to determine payload and component environments. Evaluated component qualification status and determined shock isolation approaches to eliminate qualification exceedences. Worked closely and developed a trusting relationship with Eastern, Western and Wallops Range Safety groups on flight termination system component qualification and vehicle break-up issues. Involved in 32 Pegasus missions; providing and supporting mission specific analyses, testing and pre/post launch reviews. Participated in launch operations tracking telemetry of mechanical systems. Determined approach to increase flutter margins on Pegasus Stage 1 fins. Evaluated flight data for anomalies to determine cause and possible corrective actions. Mentored younger engineers in analysis techniques and team approaches to engineering.

Processed and analyzed data from Pegasus drop tests from the L-1011 carrier aircraft. Coordinated and directed the modal test and model correlation of the first Pegasus XL launch vehicle. Created coupled load analysis and payload modeling standards for Orbital's payload community. Evaluated the component qualification status for the Pegasus/STEP-2 mission.

Managed FAA design allowables databases for tape, fabric and adhesive material systems for use on the MD11/80E2 engine core cowl. Performed buckling optimization study of titanium metal matrix composite (TMC) ducts using finite element analysis for potential use in high temperature applications such as military aircraft and the high-speed civil transport. This study led to analytical techniques that will reduce predesign costs and schedule on future programs. Designed and analyzed test article for buckling program. Directed test program to evaluate properties on alternate TMC materials.

Performed failure investigation for a missile fin deployment system required to operate at high angle of attack and speeds exceeding Mach 1. This involved development of possible deployment scenarios, identification of corrective measures, and a successful retest in a wind tunnel. Analyzed missile airframes using finite element analysis and classical stress methodology. Evaluated conceptual designs for wings and fins based on stress and aeroelastic analyses for proposal efforts with very tight schedule.

Lead engineer for spacecraft/launch vehicle loads analysis using finite element. This included planning, scheduling, and customer interface with the different spacecraft integrators along with technical direction within the group. Developed tools and methodology for model updates based on full scale modal tests and static component tests. Specialized in finite element modeling of complex structures using NASTRAN. Standardized modeling techniques and quality checks between groups.