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  • CV: Systems Project Lead Engineer

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    Personal information
     Name:<withheld>
     Age:<withheld>
     Country:<withheld>
     Location:<withheld>
    Contact information
     Email:<withheld>
     Phone:<withheld>
     Mobile:<withheld>
    Candidate Profile
     Date Submitted:07-12-2012
     Last Modified:08-12-2012 (09:28)
    Job information
     Current job:Systems Project Lead Engineer
     Employment Term:Permanent
     Job location:US only
     Date available:immediately
     Industry:Civil Agencies/International Organizations, Satellite Operators, , , Launch Systems, Consulting/Engineering Services
     KeywordsGuidance Navigation and Control, GNC, Project Engineering, Project Management, simulation, powered flight, launch
    CV

     

    SUMMARY STATEMENT

    An engineer seeking to leverage a track record of innovative problem solving, thorough analytical skills, and ability to present complex topics to a variety of audiences, as well as management of people and software resources to enhance the company’s customer satisfaction and bottom line. A big-picture technical integrator and troubleshooter reaching out beyond the individual area of expertise across the technical spectrum to optimize the process or system.

     

    KEY SKILLS AND ATTRIBUTES

    Data-driven decision making – statistical analysis, LEA and Monte Carlo analysis

    Proven teamwork and Leadership skills – Space Shuttle flight controller, Group Lead

    Integrated Project Management and Earned Value Management training

    Strong oral and written communication skills – NASA Panel support

    Software

    ·        Project Management,  ISO / CMMI lifecycle support

    ·        Requirements analysis and generation

    ·        Costing, development, testing, and validation

    ·        MS Windows and Office (Excel, Word, PowerPoint), Star/Open Office

    ·        Programming: C, PYTHON, FORTRAN, UNIX: Shell programming, GUI development

     

    PROFESSIONAL EXPERIENCE

    United Space Alliance LLC, Houston, TX(1995 – 8/2011)                                                                                                                                                    

    • Ascent Abort Region Determinator Lead Engineer (2000 – 8/2011)

    Abort Region Determinator (defined) – High speed real-time spacecraft performance program utilizing a combination of mass properties, target information, guidance algorithms, propulsion models, and sequencing to produce cyclical performance solutions.

    Achieved on time error-free delivery of flight data products (databases, calibrations, and displays) as well as technical support to the customer (NASA) of this TIG (7 engineer technical integration group) was achieved via

    • Performing Subject Matter Expert tasks
      • Project Management
      • Systems engineering
      • Developing/presenting analysis for NASA technical panels
    • Managing workloads, task assignments, and schedules.
    • Process control (error analysis, procedures, certification, compliance, ISO 9001)
    • Quality assurance
    • Mentoring new engineers

                               

    • USA Powered Flight and Ascent Trajectory Principle Function Manager for the Cockpit Avionics Upgrade Project (1999 – 2005)
      • Brought an operational GN&C (Guidance Navigation & Control) perspective to a team of Boeing, United Space Alliance, and NASA EG representatives.
      • Evaluated, developed, and validated flight critical software requirements.
        • Presented results to the Ascent GN&C Panel for approval
        • Prepared Shuttle Abort Flight Management Powered Flight Operational Validation Test Report
    • Abort Support Flight Control Lead Engineer (1991 – 8/2011)
      • Supported 35 shuttle missions
      • Time-critical Space Shuttle powered flight abort decision making (team problem recognition, resolution, and execution)
      • Mission critical data generation and Quality Assurance day of launch
      • Process control (procedures, certification, compliance, ISO 9001)
      • Software costing, development, testing, and validation
    • Ascent Abort Region Determinator Production Engineer (1995 – 2000)
      • Produced Flight critical data
      • Streamlined production process with checklist development and automation

    Rockwell Space Operations Company (1986 -1995)

    • Ascent Abort Region Determinator Production Engineer (1986 – 1995)

     

    MAJOR PROFESSIONAL ACCOMPLISHMENTS

    ·        Flight Design STS-122 ECO sensor problem response– During tanking tests for STS 122 LH2 (liquid hydrogen) sensors had unexplained multiple intermittent failures. If the LH2 supply was exhausted during flight concurrent with multiple sensor failures, there would be a total vehicle loss (7 lives, $2 Billion). The impact of having no solution was ~ $200 million/month. An operational option was developed to minimize the statistical possibility of LH2 cut-off (maximize residual LH2 mass) while minimizing the shuttle payload capacity (mass) reduction ($10K/lb.). This option was six times more effective than other proposed non-hardware options. The presentation of my option resulted in increased community knowledge concerning the integrated impact of the propellant load, shuttle main engine system, and operations on shuttle performance. In the end, hardware engineers found the cause and solution to the sensor failures.

    ·        Rendezvous Launch Window definition– The open and close of the launch window of a space vehicle are dramatically impacted by having a space object as a target (Hubble telescope, MIR space station and International Space Station). As development of discipline software to correctly adapt to the rendezvous effects moved forward, it was discovered the launch window ground software was not prepared for the first rendezvous flight. An incorrect launch window calculation could result in a loss of mission capability (~$500 million) or dropping the external tank on a foreign land mass (safety and political impact). The concept and algorithms for combining planar (rendezvous) and propellant effects of a launch hold was developed (via Excel). The results were presented to the NASA community and implemented for all shuttle rendezvous flights

    ·        Shuttle Abort Flight Management Powered Flight Operational Validation Test Report- Developed automated validation process utilizing UNIX utilities, scripts, and PYTHON programming to automatically identify software version changes, execute relevant test cases, and generate quality assurance data. Two week process reduced to two days.

     

    AWARDS

    ·        Employee of the Quarter - Technical Achievement (4th quarter 2009) – Ares 1X team (Mass Track validation)

    ·        Space Flight Silver Snoopy Award (astronaut recognition award given to less than 1% of eligible recipients) (2008) – “Mr. Davidson is an asset to the nation’s human space flight program. His efforts to improve safety and mission success …….”

    ·        Ascent/Descent Peer Recognition Award (March 2007)

    ·        Employee of the Month – Teamwork(January 2002)

    ·        Space Flight Awareness Honoree Award (2000) – “John’s consistent hard work going well beyond job requirements to improve quality, reduce costs, greatly improve crew safety, and increase manifest flexibility …….”

    ·        National Rotary Stellar Award Nominee (1997) – Rendezvous launch window definition

    ·        Sustained Superior Performance Award (1994) – He was honored for hisresourcefulness, decisiveness, and excellent technical judgment.”

     

    EDUCATION             

                Rice University, Houston, TX

                Bachelor of Science in Mechanical Engineering            May 1985


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