Glenn Case Email & Phone Number

Atlanta, Georgia, Us

Atlanta, Georgia, Us

Atlanta, Georgia, Us

Designed and developed major propulsion system components of the the GO1 system including the propellant tanks (LO2 / JetA), propellant feed systems and the pressurization/vent system. Developed 1D nodal network computation fluid dynamic models for the GO1 propellant feedlines and pressurization systems. Completed flexibility analyses of the propellant feed lines. Performed non-linear buckling analyses of the GO1 propellant tank structure. Planned and qualified weld schedules for the propellant tank primary welds. Designed in-tank LO2 vacuum jacketed transfer tube. Developed GO1 operating procedures. Conducted test readiness reviews and served as GO1 test director / conductor. Performed test data reduction and test data review. Successfully hot-fired the GO1 engineering development unit.Handled multiple high dollar subcontracts to supplier base (engine, COPV, etc.) and test site. Managed customer interfaces to AFRL High Speed Division and Edwards Air Force Base. Accountable for rocket vehicle and captive carry platform FMECA. Produced and managed schedules for propulsion and structural system development / testing. Recommended hiring and purchasing strategy. Wrote program reports. Part of the team to acquire the Air Force X-60A designation.

Kent, Wa, Us

Position is focused on design, analysis, test and integration of a 110 klbf LH2/LO2 reusable liquid rocket booster engine (BE-3) for a suborbital launch vehicle. Performed system-level risk analyses (FMECA) for multiple engine programs and for on-board avionics/controller systems. Led advanced concept studies for a non-rigid deployable nozzle extension as well as for advanced manufacturing process development for engine components. Led multiple cryogenic valve design projects, including a highly-surged oxygen compatible check valve and a hydraulic-actuated LH2 control valve. Ledthe design upgrade of valve position feedback sensors for a multi-channel LVDT, which included defining applicable mechanical, electrical and vibration requirements. Also supported other fluid/structural design efforts including pneumatics supply systems, controller structure, engine electrical interface hardware, vibration analyses, injector hardware, ground support equipment and production tooling. Performed data analysis of BE-3 engine testing and cognizant engineer duties for on-site test operations. This includes hardware inspections, approving test requests, directing on-site personnel and having the ultimate accountability for safe and expedient testing. Also performed engine ordinance operations. Wrote work orders, disposition reports, instrumentation squawks and reviewed/initiated workflows on a weekly basis.

Washington, Dc, Us

Position was focused on supporting the Pratt & Whitney / Rocketdyne J-2X engine integration and testing at Stennis Space Center. Job responsibilities included: [1] thermo-fluid analysis of SSC propellant supply systems, [2] steady-state and temporally transient multi-mode thermal analysis of cryogenic propellant systems, [3] finite element analysis of test facility structures and engine integration hardware, [4] design and analysis of cryogenic propellant piping systems, and [5] project planning, reporting at design reviews, and directly interfacing with engine suppliers/designers as well as with the NASA customer. Extensive experience utilizing the ANSYS suite of computational products has been garnered at this position.

Led the systems architecture design effort for both a hybrid rocket nanosatellite launch vehicle and an 11,500 lbf hybrid sounding rocket. Responsible for concept generation of an advanced biannular combustion chamber design which bridged the gap between the current state-of-the-art and the capability needed for commercializing low regression rate hybrid rockets. Developed the company’s hybrid rocket analysis capability, which included an internal ballistics combustion code. Developed software for use in conjunction with industrially available aerodynamic and structural analysis codes. Other responsibilities included providing engineering support to Purdue University’s rocket test facilities. This involved both hybrid, liquid, and hypergolic rocket engine test support. Authored multiple SBIR proposals under this position.

West Lafayette, In, Us

Worked within the Rolls-Royce / Gulfstream quiet supersonic jet (QSJ) research program.Developed generic (1/2/3-D) implicit routines and solvers to implement mathematically coupled periodic boundary conditions commonly found in turbomachinery. Performed viscous, turbulent, and unsteady (and steady) CFD analyses on the Rolls-Royce turbojet fan blade for the QSJ project at various flight conditions. Calculated and reported fan blade aerodynamic characteristics (lift, drag, moment, etc.) as well as compressor stage characteristics. Also led the thermal and propulsion design and testing efforts of the Purdue University hybrid rocket program. Managed the development of a flight weight 900 lbf 4-port 90% hydrogen peroxide (HP) / low-density polyethylene (LDPE) hybrid rocket motor. Led a team of 5 engineers in the design and development of a liquid injection thrust vector control (LITVC) system test bed. Designed the thermal protection system (TPS) for the LITVC system. Served as the performance analyst as well as project manager within the LITVC project.

Education record

B.S., Mechanical Engineering