Concept Review Oxidizer Tank and Delivery Team

Concept Review Oxidizer Tank and Delivery Team

Introductions Nathan Confer Tim Seibert Maggie Anderson Tony Nimeh Chris Wergin

Benchmarking 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 fuselage, the tank, and the oxidizer delivery system.

Needs Ranking Tank Importance N 20 tank needs to sustain TBD pressure 9 incorporate safeguards with respect to burst pressure 3 Oxidizer Delivery System Importance Controllable (steady) flow rate 9 Safe fuel delivery system 9 Tank refilling mechanism 3 Fuselage Importance Accept and support delivery system, tank, motor 9 Withstand heat transfer from combustion and tank 9 Accommodate payload integration 3 Power source 3 Recovery system 1

Team Organization Project Manager Nathan Confer Technical Lead Tony Nimeh Frame Oxidizer Tank Delivery System Fuselage Tony Nimeh (focal) Chris Wergin (focal) Maggie Anderson (focal) Tim Seibert (focal) Maggie Anderson Nathan Confer Chris Wergin Nathan Confer Tim Seibert Tony Nimeh Super Structure Tank Design Components -assembly rods -sizing dimensions -piping -support plates -material considerations -valves Sub Structure Manufacturing -pressure regulators -injector plate connection -composite capabilities Safety -payload platform -burst prevention Shell -necessity exploration (pending) -material considerations Attachment Mechanisms -test stand setup -future payload provisions

Concept Sketches

Concept Breakdown • Frame – Tony Nimeh • Oxidizer Delivery System – Maggie Anderson • Tank – Chris Wergin • Fuselage – Tim Seibert

Skeleton Structure • Three hollow rings to support the oxidizer tank Clamp Ring • Two clamp rings to hug the tank and fasten it to hollow rings • Four threaded rods run axially to unify structure • Two support plates align and constrain the feed system to reduce bending stress • Aft of the support plates will be the Injector Plate and Motor with attachment TBD Support Ring

Structure Needs • Lightweight – Remove material wherever possible (hollow, thin, etc. ) • Transfer and withstand thrust – Axially strong • Accommodate payload and electronics – Versatile foundation for future expansion

Feed System Background • What is the feed system’s function? – To deliver the oxidizer from the tank to the combustion chamber safely and with a controllable pressure loss • What causes pressure losses? – – Leaking Viscous effects Geometry/Direction changes Monitoring/Flow Control Devices

Ground Testing Feed System • P 06006 • P 07105 – Brass + teflon tape to stainless steel – Heating blanket for tank – Tube in tank to siphon liquid – Mass flow meter not implemented

Oxidizer Feed System

Same Feed System • Losses due to geometry/monitoring/leaking • Improvements to ground testing feed system – More hose (reduce geometry and leaking losses) – Redundant ball valve – Move needle and check valve

Tank Concept

NOX Tank Concepts • Aluminum Tank – Pros: low cost, easily fabricated, high psi rating – Cons: weight • Composite Tank – Pros: low weight, high psi rating – Cons: costly, difficult to fabricate in-house • Prefab Paintball Composite Tank – Pros: high psi rating, low cost, low weight (per tank) – Cons: low CI per tank, weight (given # of tanks needed)

Tank Fabrication Issues • (composite) In-house fabrication – Limited method of production – hand lay-up – composite sock – lathe winding – Cost of materials / shelf life of materials – Time • Outsourcing fabrication – Finding companies to fabricate custom tank – Cost – Time

Fuselage • Titanium construction – Two halves connected to inner support structure – Hatch to provide access to fuel delivery system

Vertical Test Stand Mount • Attach to payload receptacle at top of rocket • Bracing to run along side of fuselage and attach to bottom of vertical test stand Design Difficulties • Method of connection to internal support structure • Ease of access to internal components • Thermal expansion and thermal shock

Pugh Matrices • Tank • Oxidizer Delivery System • Fuselage • Assembly

PUGH Matrix for Tank Concept A: Aluminum Concept B: Hand Lay Up Composite Concept C: Outsourced Composite Concept D: Paintball Tank Selection Criteria Weight Rating Weighted Score Ease of Machining 0. 15 4 0. 60 3 0. 45 5 0. 75 Ease of Use 0. 10 4 0. 40 Reusability 0. 15 4 0. 60 5 0. 75 Durability 0. 20 2 0. 40 3 0. 60 Safety 0. 20 3 0. 60 2 0. 40 4 0. 80 Weight 0. 20 1 0. 20 3 0. 60 Total Score 2. 80 2. 85 3. 75 3. 90

PUGH Matrix for Oxidizer Delivery System Concept A: Maggie's system Concept B: (Nate, Chris, Tim, Tony)'s system Selection Criteria Weight Rating Weighted Score Ease of Machining 0. 05 3 0. 15 4 0. 20 Ease of Use 0. 15 3 0. 45 4 0. 60 Durability 0. 20 5 1. 00 Safety 0. 20 5 1. 00 3 0. 60 Reusability 0. 10 5 0. 50 Functionality 0. 15 5 0. 75 3 0. 45 Weight 0. 15 2 0. 30 4 0. 60 Total Score 4. 15 3. 95

PUGH Matrix for Fuselage Concept A: Two Halves Concept B: Two Halves with access door Concept C: Slip Cover Concept D: No Shell Selection Criteria Weight Rating Weighted Score Ease of Machining 0. 15 3 0. 45 2 0. 30 4 0. 60 5 0. 75 Ease of Use 0. 20 4 0. 80 5 1. 00 2 0. 40 5 1. 00 Durability 0. 20 4 0. 80 3 0. 60 4 0. 80 1 0. 20 Safety 0. 15 4 0. 60 3 0. 45 4 0. 60 1 0. 15 Weight 0. 30 3 0. 90 2 0. 60 3 0. 90 5 1. 50 Total Score 3. 55 2. 95 3. 30 3. 60

PUGH Matrix for Rocket Assembly Concept A: BAMF (Housing for tank/Brackets) Concept B: Rods and plates “in rods we trust” Concept C: Annular Concept D: Multiple oxidizer tanks Selection Criteria Weight Rating Weighted Score Ease of Machining 0. 05 3 0. 15 4 0. 20 1 0. 05 2 0. 10 Ease of Use 0. 15 2 0. 30 4 0. 60 1 0. 15 2 0. 30 Reusability 0. 20 4 0. 80 Durability 0. 20 4 0. 80 2 0. 40 3 0. 60 Safety 0. 10 2 0. 20 4 0. 40 2 0. 20 Functionality 0. 15 3 0. 45 4 0. 60 2 0. 30 Weight 0. 15 2 0. 30 4 0. 60 2 0. 30 1 0. 15 Total Score 3. 00 4. 00 2. 50 2. 45

Concept Selection

Senior Design I Outlook • Week 8 – – – Finalized concept Detailed concept sketches (CAD) Rough sizing of all components Material selections of components Part supply information for multiple subfunctions for Bill of Materials – Provide detailed information to manufacturing limits and difficulties for all subfunctions – Establish rough Senior Design II schedule with regard to project milestones (manufacturing, testing, etc)

Senior Design I Outlook • Week 10 – Finalized sizing of all components – Detailed sketches (CAD) with finalized subfunction sizes – Finalized material selections – Completed Bill of Materials for all subfunctions and assemblies – Order necessary parts and raw material – Manufacturing process finalized – Senior Design II schedule established with respect to parts delivery, manufacturing lead times, and testing milestones

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 P 08105 for date to assemble entire rocket (tank with engine) • Test entire rocket assembly • Write up design, manufacturing, and testing, reports and conclusions (and poster)

questions comments concerns

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