Michael Asp Email & Phone Number

Defiance, Mo, Us

Work in Lightning Direct Effects group for the 787 Dreamliner Program

* Consulted and coordinated with the Aircraft Structural Integrity Program, the Avionics and Electrical Systems engineers, the Electromagnetic Effects engineers and the Manufacturing engineers to resolve problems and interface issues around a composite wing tip created through a Resin Transfer Method that included a never-before-used Position and Anti-Collision light. * Acted as a liaison between Avionics and Electrical Systems engineers, wing supplier, wing tip supplier, and Position and Anti-Collision light supplier to minimize risk when assembling the overall wing once the parts were received from the respective suppliers.* Modeled wing tip assembly and installation, trimeron assembly and installation, and a test article structure to identify what ice shapes occur on the leading edge of the wing during icing conditions by utilizing CATIA V5 in ENOVIA/VPLM.* Designed two alternate methods to externally deploy slat for test article structure so that each method of deployment could be done externally by one person inside the NASA Glenn Icing Research Tunnel test section to minimize down time in-between test runs. * Created engineering bill of materials, work orders, and part numbers for wing tip assembly and installation, trimeron assembly and installation and test article structure through the Production and Inventory Optimization System.

* Studied various high lift devices to be used during landing, including flapperons, fowler flaps, slats with fowler flaps and slats with plain flaps.* Modeled current wing of Cirrus SR-22 in SolidWorks based on information provided by sponsor and completed computational fluid dynamics analysis using FloWorks.* Derived requirements from sponsor's goals and FAA Requirements. An example of this is the sponsor wanted 300 lbs more lift at landing, the landing speed cannot be greater then 61 knots as dictated by the FAA Requirements, so an analysis was conducted of the lift coefficient at landing. * Invalidated FloWorks through a comparison of the results FloWorks would give and results from a previous wind tunnel test.Presented results to peers, sponsor and professor through a PowerPoint Presentation.

* Designed, Fabricated and Tested various wing configurations on a Micro Air Vehicle based on a blue print using an exacto knife, glue, bass wood and cover tissue.* Modeled designs in Pro-E and completed computational fluid dynamics analysis using ANSYS CFX. * Validated theory against experimental results through calculations at various angles of attack to determine the aerodynamic forces on the Micro Air Vehicle at any moment in time. It was then implemented in SIMULINK for MATLAB to model the behavior of the Micro Air Vehicle based on initial conditions.

Bachelor Of Aerospace Engineering And Mechanics

Education record