PROJECT METEOR OXIDIZER SYSTEM AND STRUCTURE PROJECT REVIEW Friday November 9, 2007 MAGGIE ANDERSON NATHAN CONFER TONY NIMEH TIM SEIBERT CHRIS WERGIN 1/1/2019

CONTENTS METEOR Overview Hybrid Background Team Organization Constraints/Risks Deliverables Specifications List Hybrid Rocket Concept Strategy Detail Design Overall Hybrid Rocket Structure and O.D.S Structure Oxidizer Tank Oxidizer Delivery System SDII Project Plan Questions/Discussion *Please feel free to ask questions or make comments during the presentation* 1/1/2019

Introductions Tim Seibert Maggie Anderson Chris Wergin Tony Nimeh Nathan Confer Tim Seibert Maggie Anderson Chris Wergin Tony Nimeh 1/1/2019

Project METEOR strives to create a lower-cost Project Background Project METEOR strives to create a lower-cost alternative to current low-Earth orbit launch solutions for "Picosatellites", a class of satellites weighing approximately 1 kg. The purpose of the Rocket Integration Team is to accept the hybrid engine while incorporating the remainder of the major rocket subsystems. 1/1/2019

Project Overview 1/1/2019

Benchmarking and Brainstorming Chalice Design Embedded Design After investigating the previous team’s work and looking into other hybrid rocket designs it became obvious that the project has three major components. These components are the frame, the tank, and the oxidizer delivery system. 1/1/2019

Team Organization Project Manager Technical Lead Frame Oxidizer Tank Nathan Confer Technical Lead Tony Nimeh Tank Design -sizing dimensions -material considerations Manufacturing -composite capabilities Frame Tony Nimeh (focal) Tim Seibert Super Structure -assembly rods -support plates Oxidizer Tank Chris Wergin (focal) Tony Nimeh Delivery System Maggie Anderson (focal) Nathan Confer Components -piping -valves Safety -burst prevention -pressure regulators 1/1/2019

Hybrid Rocket Concept 1/1/2019

From Concept to Reality… Engineering the Future Tank Design 1/1/2019

Oxidizer Tank 1/1/2019

N20 Pressurization Oxidizer Tank Single-tank configuration with Helium gas used to pressurize the liquid nitrous oxide. Goal: Deliver 1500 psi to injector plate Helium (gas) Nitrous Oxide (liquid) 1/1/2019

MATLAB Program Results – End Pressure Tank Volume 1/1/2019

MATLAB Program Results – End Pressure Initial Temperature 1/1/2019

MATLAB Tank Evacuation Solution 1/1/2019

Final Oxidizer Sizing Prefab composite Tank produced by SCI composites Aluminum liner with carbon/glass reinforcement 1212 cubic inch volume 3259psi rated service pressure Pressure tested to 5000psi 18.7lbs empty weight Tank already purchased by P07109 1/1/2019

From Concept to Reality… Engineering the Future Oxidizer Delivery System 1/1/2019

Oxidizer Delivery System 1/1/2019

Head Loss Calculations Velocity: Mass Flow Rate: 1/1/2019

Head Loss Values Component Description Head Loss (in) A N2O Tank 0.00 1 N2O Tank Connection Port 16.48 2 N2O tank Fitting 0.19 3 Cross Fitting 73.36 4 Connection Nipple 0.06 5 Remote Ball Valve 1.39 6 7 Pressure Regulator / Flow Switch 0.28 8 9 Flexible Hose + Connectors 5.61 10 11 Check Valve 244.23 12 13 14 15 Injector Plate Connection Port 0.05 B Injector Plate TOTAL 415 1/1/2019

Feed System: Part Selection Aaaaaaaahhhhhhhhhhhh that’s a lot of money! With a regulator in there, I just spent about 4/5 of our budget! Well, at least the feed system will be pretty sweet. 1/1/2019

Feed System: Part Details Relief Valve Desired range: 3000-3600 psi Proof pressure: 4500 psi Stainless steel construction ½” Pipe Size 250°F max temperature ~$450 each 1/1/2019

Feed System: Part Details Ball Valve 316 Stainless Steel ball 17-4 PH SS stem Delrin seats PTFE body seals & packing ½” Pipe Size 4500 psi max at 120°F $126.45 each Check Valve 303 Stainless Steel 440 SS ball 5000 psi max at 400°F $86.40 1/1/2019

Feed System: Part Details Metal Hose and JIC Swivel Female Fittings T361L SS heavy-weight hose T321 SS double braid 1500°F max temperature ½” Pipe Size Minimum length for vibration = 6 in 1/1/2019

Feed System: Part Details Circle Seal Pressure Regulator 303 Stainless Steel body Orifice = 0.145” Cv = 0.37 Inlet/Outlet: 0-6000 psig 160°F max temp ~$2000 (approximation based on P07105 Emerson Quote) 1/1/2019

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From Concept to Reality… Engineering the Future Structure 1/1/2019

Structure 1/1/2019

Rods Rings Structural Skeleton Continuous-length distributes thrust and weight Lightweight & strong Excess length for future add-ons Rings Anchored to rods Spaced so as to avoid buckling Chamfered in order to support tank 1/1/2019

Structural Skeleton Rod analysis Worst-Case (Axial Stress): Vert. Test Stand Fixed at top, Axial load Worst-Case (Bending Stress): Balloon Ascent TBD depending on carriage 1/1/2019

Sourcing Rods Structural Skeleton Online Metal Store – round bar stock Grade 5 more difficult to machine than 2 1/1/2019

Sourcing Rings Structural Skeleton McMaster-Carr – Aluminum plate stock 6061 Al is reasonable to machine in-house 1/1/2019

Senior Design II Outlook Review finalized design, milestones, and lessons learned from SDI Establish part delivery dates Resolve any shipping delays or unexpected setbacks during transition from SDI to SDII Finalize manufacturing schedule Setup manufacturing and assembly completion date(s) Correlate with P08105 for date to assemble entire rocket (tank with engine) Test entire rocket assembly Write up design, manufacturing, and testing, reports and conclusions (and poster) 1/1/2019

questions comments concerns 1/1/2019

thank you 1/1/2019