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Engineer Design

Location:
Corona, California, United States
Posted:
December 24, 2015

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Resume:

SHAWKY LOUIS LANSING e-mail: acswk9@r.postjobfree.com

**** **** *****, ******, ** 92880

Cell (951) 533 - 5049

OBJECTIVE Home (951) 278 - 4684

Performing Analysis, Design, and Testing of Mechanical, Thermal, Hydraulic, Structural, and System Engineering in Aerospace and Energy Recovery Systems projects

QUALIFICATIONS

Registered Professional Mechanical Engineer in the State of California

MS in Aerospace Engineering - Cal. State Polytechnic Univ., Pomona, CA - GPA 3.86/4.0

MS in Mechanical Engineering – California State University, L.A., CA - GPA 3.71/4.0

Advanced courses in: Propulsion, Structure Dynamics and Stability, CFD (Finite Difference), Gas Dynamics, Airplane Design and Performance, Aerodynamics, Heat Transfer: Conduction, Convection, and Radiation, Thermodynamics, Vibrations, Internal Combustion Engines, System Optimization, Astro-dynamics, Mass Transfer, Cryogenics, and Air Conditioning.

Design 3-D models and 2-D engineering drawings utilizing: UNIGRAPHICS II Version NX2, CATIA 5 V16, Pro-E wildfire 3.0, and SolidWorks 2010 X64 SP5.0

Prepare engineering design documents using MS Office: Excel, Word, and Power Point.

U.S. citizen - Clearance: Secret

EXPERIENCE

June ’10 General Atomics Aeronautical System Inc., San Diego, CA

Present Programs: UAV MQ-9

Analysis & Environmental Engineer

Laser Electro Optic, Mission Systems Group

Apply Thermal, structural, mathematical, and optical analysis to laser gain medium.

Perform moisture analysis to series of laser windows tested in altitude chamber.

Apply thermal, fluid flow and structural optimization analysis to fin plate’s heat exchanger by conventional hand calculations and verified by ANSYS icepak software. Calculate flow induced vibrations between fins. Analyze duct system performance on selected fan/blower.

Perform vacuum analysis to diffusion pumps and piping network. Perform gas mixture analysis to vacuum chambers to correct for pumping imbalance effect on web coating.

Perform structural analysis to non-uniform cross-section pressurized pressure vessel. Create weld map and check for welding strength to vessel attachments. Model the 3-D vessel in SolidWorks and verify components structural stresses by using ANSYS static structural.

Create system schematic P&ID per API 614 for cooling optical systems.

Investigate and resolve non-conformance reports generated by the Electromagnetic group.

Aircraft Propulsion Engineer / Analyst

Aircraft Design Assurance / Validation / Materials / Airworthiness Group

Provide solution to technical problems by applying scientific principles in thermal and fluid flow analysis to ensure reliability, durability, and compliance to product standards. Identify the source of the problem and solve for the aircraft low oil pressure warning at low altitude.

Perform hand calculations for fuel and oil loop system pressure, temperature, and flow requirements for Block 5 and the Predator B airworthiness validation process.

Analyze system components: control, relief, check, and solenoid valves, hydraulic and jet pumps, oil reservoirs and fuel tanks, hoses, tubing, and fittings, screens and filters, fuel to oil and oil to air heat exchangers, and electric heaters. Perform pressure drop analysis to gas and liquid mixture in ducts and shell/tube heat exchangers.

Perform glycol-water pressure drop analysis for engine cooling system including radiator, Oil Cooler Module, engine block, and tubing/hoses/fittings network for the Gray Eagle Aircraft.

Shawky Louis Lansing (continued) Page 2

Oct. ’07 United Technologies Corporation

June ‘10 Pratt & Whitney / Hamilton Sundstrand Rocketdyne, Inc, Canoga Park, CA

Programs: Space Based Energy and Stage Engine for ARES I & V Vehicles

Engine Development Engineer

J-2X Engine Integration Group

Write technical design and test requirements for J-2X engine’s flexible lines start system, bleed, purge, fuel and oxidizer tanks pressurization, and pneumatic system components. Coordinate efforts with design and configuration management groups.

Utilize UTC’s ACE (Achieve Competitive Excellence) tools available to perform Standard Work for Rocket’s Heat Exchanger. Establish basic thermal, pressure drop, and effectiveness analysis to the heat exchanger with its inlet and outlet ducts.

Draft tooling drawings for Advanced Thermo-Electric Converter Group, by Pro-E Wildfire 3.0

July ’05 the Boeing Company - Commercial Airplanes Group, Everett, WA

Oct. ’07 Program: 747- 8 Passenger and Freighter

Mechanical System Design & Analysis Engineer

Environmental Control Systems - Cabin Airflow and Thermal Systems Group

Perform heat transfer analysis to fuselage structure and windows for 777 and 787 aircrafts. Assign air distribution to cargo, electronic equipment, and cabin zones using Boeing JENA software program.

Analyze and verify supplier’s electronic boxes design documents for adequate performance.

Conduct testing aircraft‘s Return Air Grilles (RAG), analyze results, and write test report.

Perform airflow and thermodynamic analysis to Air Cycle Machine at different flight cases and compare the hand calculation with the supplier’s expected unit performance.

Perform compressible flow and heat transfer cooling analysis to fan under cowl.

Estimate pressure drop in pneumatic line from APU compressor unit to main engine for startup

Nov. ’03 the Boeing Company – Space Programs, Huntington Beach, CA

July ’05 Proprietary Program

Environmental Control System Design Engineer

Thermal Control Systems Group

Perform purge analysis and hardware selection for cooling components at vehicle post landing.

Apply fluid flow analysis for sizing flow restrictions (orifices) in the cooling liquid loop system.

Select heaters, designing MLI and fibrous insulation blankets and installation hardware.

Perform gas flow analysis to non-metallic mechanical component at different environmental conditions and durations.

May ’02 Northrop Grumman – Integrated Air Combat System, San Diego, CA

Nov. ’03 Program: Global Hawk - Unmanned Aerial Vehicle

Design/Analysis Engineer

Mechanical Sub-Systems Group

Perform design analysis to the aircraft Fuel Flow Systems.

Specify and write technical requirements for the system components: heat exchangers, relief valves, and procurement templates (SOW, DID, SCD) based on the vehicle specification.

Initiate a weight saving of 9.5 pounds in the tubing network for the refueling system.

Perform engineering evaluation and analysis to supplier bids, and review the supplier’s component drawing, Acceptance and Qualification Test Procedures (ATP and QTP).

Perform compressible fluid flow analysis for optimizing and sizing the fuel tank’s double acting, pressure, and vacuum valve during the aircraft’s ascent and descent based on the vehicle mission profile.

Shawky Louis Lansing (continued) Page 3

Nov. ’87 the Boeing Company - Transport Aircraft, Long Beach, CA

Mar. ’02 Program: C17 Globe Master III

Senior Engineer Scientist

Wing Movable Surfaces Structural Design Group

Perform tasks in support of “Cruise Performance Improvement Program” from preliminary structural design analysis to production installation. Design the seals between spoilers, between the inboard spoiler and fuselage, and at the outboard aileron - wingtip interface. Design spoiler and aileron fiberglass fairings.

In support of the manufacturing, assembly, and design in the area of the flap box, spoiler, aileron, winglet, wingtip, and the wing trailing edge for the C-17 Transport Airplane.

Redesign the inboard and outboard flap box lower stringers for weight saving (56 pounds).

Initialize the Test / Work Request to test the polycarbonate wing tip lens, in a hot day, and coordinate with the test conductor. Apply heat transfer analysis for the test data.

Apply fluid flow and dynamic design analysis, steady and unsteady, for the hydraulic actuators, valves, and transmission lines for the aircraft’s Full Scale Durability Structural Test.

Apply compressible fluid flow analysis to aircraft vent system during descent.

Design special test support for testing the engine fuel pump and perform hydraulic analysis for testing the aircraft’s nose gear.

June ’82 Rotoflow Inc. - General Electric Gas & Oil, Gardena, CA

Nov. ‘87 Projects: Turbo-machinery Units for Energy Recovery Systems

Mechanical Design Engineer

Design and Thermodynamic Group

Assign and supervise the design engineering work, which includes pressure vessels, reservoirs, filters, and accumulators per ASME code, Section VIII, Div. 1, shaft seal and control oil to bearings per API Codes.

Perform overall weight, thermal, vibration, stress analysis to piping and rotating equipment supports. Select system components: heat exchangers, pumps, motors, gearboxes, electric generators, oil heaters, control valves, accumulators, filters, rotating machinery couplings, pipes, and fittings. Design un-pressurized oil reservoir as a part of the machinery base skid.

Design lifting structure and wood container for unit shipping. Select wire ropes and wire clips. Apply weld analysis to structural steel pipes, lifting lugs, and re-enforcement gussets.

Coordinate design activities with the shop, fabrication, suppliers, and the sales engineers.

Apply thermodynamic analysis to calculate the maximum energy usage from one or two phase fluid flow and from single or multi-component gas systems.

Perform thermodynamic, fluid flow, and gas dynamic design analysis to the rotor/ impeller, turbine/compressor blades at design and off-design point. Calculate total energy and efficiency across the turbo-machinery. Evaluate the turbine, compressor, and the blower test results.

Analyze the customer’s input proposals, provide the system schematic P&ID and the machinery arrangement drawings, and the turbomachinery’s performance curves.

Conduct technical seminars and design review meetings for company’s clients.

SCHOOL TECHNICAL REPORTS

Aerospace Engineering Master’s thesis by Using C++ in equation formulations to :

”Numerical Lifting Line Theory”. California State Polytechnic University, Pomona,

CA, June 2005.

Scramjet Inlet Spike of 3.0 Mach Number. Cal State Univ. Long Beach, June 2004.

Energy Storage in a Material via its Phase Change. Cal State Univ. L.A., June 1981.



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