Bob Criner

Electric propulsion system design, requirements definition, architecture and certification support.

+ Supported integration of magniX EPUs on the eBeaver and eCaravan flight test aircraft. + Electric Propulsion Unit (EPU) ground test planning, test directing, post test data analysis and report creation in support of successful world’s first(eBeaver)/largest(eCaravan) all-electric commercial aircraft flight test programs. + Propeller governor oil system and oil cooling system design, analysis, build, test and troubleshooting. + Defined EPU system level requirements and loads specification in compliance with Part 23 and 33 requirements. + Detailed static, fatigue and damage tolerance structural analysis of motor components to support safety of flight reviews with certification authorities and motor redesign efforts. + Supported definition of structural design and analysis methods/tools to be used by engineering team.

+ Responsible for leading a team of 7 engineers working on the development, integration, test and certification of magniX’s Electric Propulsion Units (EPUs) for Part 23 aircraft installations. + This included integration of electric motors, motor controllers, 600-800V/300+kWh Li-ion battery packs, cooling systems, propeller, airframe mounts and human machine interface (HMI). + Design, build and operation of magniX 560 kW system integration test lab (Iron Bird), an integral part of the EPU verification and certification test program. + Supported company-wide shift from R&D development approach to an aerospace system engineering development process according to SAE ARP4754A, RTCA DO-254 (Hardware) and DO-178 (Software). + Participated in the selection, implementation and rollout of a requirements management tool. + Led EPU certification program, attending CASA & FAA familiarisation meetings, developing draft certification plan, populating means of compliance checklist, negotiating certification basis for novel electric propulsion technology. + Active member of ASTM committees developing certification basis and means of compliance for electric propulsion units and energy storage systems with Civil Aviation Authorities.

+ Responsible for design, analysis, manufacturing, installation and structural testing of composite and metallic airframe structure. + Created FEMs (with NX CAE, NX Nastran and Femap) used for structural analysis, load path determination, strength, stability, fatigue and flutter. + 2D/3D CAD drawing/model generation of single parts and higher level assemblies in NX. + Designed and conducted structural tests used to validate airframe integrity and analysis methods. + Worked to understand, further develop and comply with certification requirements in the new field of energy kites. + Performed airframe structural inspections, investigated detected damage and designed repair solutions. + Close collaboration with teams from other disciplines, e.g. Aerodynamics, Avionics, Control, Power.

+ Led a team of 5 engineers responsible for static and fatigue analysis of airframe structure. + Daily tasks included structural analysis (static strength, buckling, crippling, fatigue, dynamic) using a combination of Saab Structure Manuals, FEM and standard hand calculation methods.

Program: Airbus A350-900 & -1000 Responsibility: Fuselage Structure Development and Static/Fatigue Full Scale Test Support + Stress lead for a team of up to 7 analysts. Responsible for static and fatigue analysis of composite and metallic fuselage structure including frames, clips, skin/stringer stiffened panels, longitudinal/orbital skin joints, frame splices, PAX floor, cargo floor and belly fairing interfaces. + Daily tasks included structural analysis (static strength, buckling, post-buckling, damage tolerance, fatigue) using a combination of Airbus analysis tools (ISAMI), FEM and standard hand calculation methods (Bruhn, Niu, Mil-Hdbk-17, HSB), checking/signing drawings, working with design to optimize structure, writing/checking stress reports and scheduling/coordinating/leading team tasks to meet deadlines. + Completed certification stress reports and supported Airbus in preparation for EASA A350 type certification meetings. + Defined, built and validated Nastran/Patran DFEMs of complex composite/metallic structures. + Managed and checked structural analysis work performed by an external supplier. + Definition and evaluation of coupon testing required for composite material allowables determination. + Designed and analyzed composite fuselage structural repairs for A350 Structural Repair Manual. + Another major team responsibility was static and fatigue analysis of structure for the A350 ES Full Scale Static and A350 EF1 Fwd & Nose Fuselage Full Scale Fatigue tests. + Defined strain gauge locations, strain predictions and test inspection requirements for above tests. Performed live monitoring of tests and used test results to validate FEMs and analytical methods. + Worked as a stress analyst for PAX Door Surrounding structure for 3 months, performing analysis of composite skin, intercostal and frame components with FEM and Airbus analysis tools (ISAMI). + Performed PAX Door Surrounding FEM updates including GFEM superelement condensation.

Program: Airbus A350-900 Responsibility: Nacelle Structure (Fan Cowl, Thrust Reverser) + Stress lead for a team of 6 analysts. Responsible for static and fatigue analysis of Fan Cowl structure from preliminary layouts through to drawing release. Structure consisted of a large composite panel with hollow hat frames/longerons/intercostals, numerous metallic fittings, a composite strake and two composite sandwich panel access doors. + Developed structural analysis methods for sizing a new adhesively bonded composite hollow hat stiffener technology including material allowable generation and validation of the method by test. + Created detailed Nastran/Patran FEM of Fan Cowl structure for integration into the nacelle IFEM, used to obtain loads for structural sizing of parts and to perform non-linear buckling and post-buckling analysis. + Other responsibilities as lead included presenting at technical review meetings, check/review of other analysts’s work, sign-off of drawings/structural analysis, providing technical advice/coaching to less experienced analysts and planning/coordination of team tasks using MS Project. + Liaised across multiple disciplines to ensure product met stringent technical requirements and aggressive component delivery targets. + Involved in the design, analysis and execution of a number of structural tests (both engineering and certification level) aimed at validating the design and analysis methods used to size structure. This included loaded fire testing of titanium fittings attached to composite structure. + Defined allowable damage limits and repair techniques for composite nacelle structure.

Program: Gulfstream G650 Responsibility: Wing Structure (Main Landing Gear Sponson, Spoilers, Rear Spar) + Responsible for leading a team of engineers working on static and fatigue analysis of main landing gear sponson box structure including primary metallic skins, ribs, intercostals, splice plates and secondary systems brackets. + Generated stress reports for a number of parts to support drawing release. + Involved in technical review meetings, review/sign-off of structural analysis and coaching of less experienced engineers. + Created Nastran/Patran loads FE model which was used for final sizing of all sponson parts and surrounding wing box structure. + Worked on the analysis and FE modeling of composite sandwich panel spoilers, spoiler attachment fittings and wing rear spar. Also assisted with updates to the global AV FEM.

Jul 2007 - Oct 2007 Program: Airbus A350-900 Responsibility: Wing Fixed Trailing Edge Structure + Preliminary sizing of composite sandwich panels using standard Airbus analysis methods. + Modeled composite wing fixed trailing edge structure for AV FEM using Nastran/Patran and applied pressure and temperature mapping to structure. Jun 2005 - Jul 2007 Program: F-35 Joint Strike Fighter (Lightning II) Responsibility: Northrop Grumman Centre Fuselage Structure + Static and fatigue analysis of composite skins/panels in fuel tank region, a large composite strap, an adhesively bonded composite patch, an aluminum casting and metallic frames/intercostals. + Detailed analysis performed on these parts included Bolted and Bonded Joint Strength (Metals and Composites), Fastener Pull-Through, Inter-Laminar Shear and Tension, Core Strength, Panel and Column Stability/Buckling (Classical, Linear SOL105, Nonlinear SOL106), Post-Buckling, Crippling, Cutouts, Composite Durability, Metallic Fatigue (Crack Initiation and Growth), Flutter and Sonic Fatigue. Analysis conducted using classical hand analysis techniques, Lockheed Martin structural analysis tools and FEA. + Created breakout Nastran FE model (derived from portion of global AV FEM) of the center fuselage using Patran. Refined mesh in critical areas, modeled surrounding breakout structure as a superelement and ran SOL106 nonlinear buckling analysis. + Modified and reran entire global AV FEM, working mainly with large Nastran decks. + Assisted in the development and validation of engineering automations used to reduce analysis time when dealing with repetitive tasks and large numbers of load cases. + Also worked test program, designing/sizing test fittings, defining gauges and correlating test results.

+ MSC.Software Australia Prize (awarded for highest grade/mark in Mechanics of Solids and Analysis of Aerospace Structures) + CRC-ACS Prize (awarded for the best undergraduate project on Advanced Composite Structures)