1. PROJECT METEOR OXIDIZER SYSTEM AND STRUCTURE
DETAIL DESIGN REVIEW
Friday November 9, 2007
MAGGIE ANDERSON
NATHAN CONFER
TONY NIMEH
TIM SEIBERT
CHRIS WERGIN
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2. CONTENTS METEOR Overview Team Organization Deliverables
Hybrid Rocket Concept Strategy
Detail Design
Overall Hybrid Rocket Structure and O.D.S
Oxidizer Tank
Oxidizer Delivery System
Structure
Finite Element Analysis
Deliverables Revisited
SDII Project Plan
Questions/Discussion
*Please feel free to ask questions or make comments during the presentation*
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3. Introductions Tim Seibert Maggie Anderson Chris Wergin Tony Nimeh
Nathan Confer
Tim Seibert
Maggie
Anderson
Chris Wergin
Tony Nimeh
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4. 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.
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5. Project Overview
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6. 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.
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7. 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
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8. Constraints and Objectives
Tank
Importance
N20 tank needs to sustain pressure of 2500 psi 9
Incorporate safeguards with respect to burst pressure
Oxidizer Delivery System
Maintain pressure of 1500 psi at the injector plate
Controllable (steady) flow rate
Safe fuel delivery system
Tank refilling mechanism 3
Fuselage
Accept and support delivery system, tank, motor
Withstand heat transfer from combustion
Accommodate payload integration
Power source for pressure regulator
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9. Hybrid Rocket Concept
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10. From Concept to Reality… Engineering the Future
Tank Design
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11. Oxidizer Tank
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12. 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)
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13. Equations Used to Size Oxidizer Tank
1st Law of Thermodynamics (N2O)
Ideal Gas Law
Isentropic Assumption (Helium)
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14. MATLAB Program Results – End Pressure Tank Volume
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15. MATLAB Program Results – End Pressure Initial Temperature
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16. MATLAB Tank Evacuation Solution
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17. 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
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18. From Concept to Reality… Engineering the Future
Oxidizer Delivery System
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19. Oxidizer Delivery System
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20. Head Loss Calculations
Pressure at a given point:
Reaction from Momentum Flux:
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21. Head Loss Calculations
Mass Flow Rate:
Velocity:
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22. Head Loss Calculations Continued
Head Loss Term:
Reynolds Number:
Friction Coefficient:
Relative Roughness:
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23. Head Loss Values Component Description Head Loss (in) A N2O Tank 0.001
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
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24. 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.
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25. Feed System: Part Details
Relief Valve
Desired range: psi
Proof pressure: 4500 psi
Stainless steel construction
½” Pipe Size
250°F max temperature
~$450 each
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26. 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
$ each
Check Valve
303 Stainless Steel
440 SS ball
5000 psi max at 400°F
$86.40
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27. 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
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28. Feed System: Part Details
Circle Seal
Pressure Regulator
303 Stainless Steel body
Orifice = 0.145”
Cv = 0.37
Inlet/Outlet: psig
160°F max temp
~$2000 (approximation based on P07105 Emerson Quote)
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29. From Concept to Reality… Engineering the Future
Structure
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30. Structure
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31. 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
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32. 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
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33. Sourcing Rods Structural Skeleton Online Metal Store – round bar stock
Grade 5 more difficult to machine than 2
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34. Sourcing Rings Structural Skeleton
McMaster-Carr – Aluminum plate stock
6061 Al is reasonable to machine in-house
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35. From Concept to Reality… Engineering the Future
Finite Element Analysis
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36. Boundary Conditions
At the nozzle end there are 75 pounds force per rod in the negative Z direction
At the payload end all displacement degrees of freedom are fixed at 0
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37. Displacement
Maximum deflection is inches in the direction of the force loading which is located at the nozzle end of the assembly
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38. Maximum Stress
Maximum stress is 6280 psi which is located at the payload end of the assembly
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39. Vibration – Modal Analysis
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40. Vibration – Modal Analysis
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41. From Concept to Reality… Engineering the Future
Concluding Remarks
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42. Constraints and Objectives Revisited
Tank
Importance
N20 tank needs to sustain pressure of 2500 psi 9
Incorporate safeguards with respect to burst pressure
Oxidizer Delivery System
Maintain pressure of 1500 psi at the injector plate
Controllable (steady) flow rate
Safe fuel delivery system
Tank refilling mechanism 3
Fuselage
Accept and support delivery system, tank, motor
Withstand heat transfer from combustion
Accommodate payload integration
Power source for pressure regulator
in progress
to be determined
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43. 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 (if time allows)
Write up design, manufacturing, and testing, reports and conclusions (and poster)
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44. Senior Design Two Schedule
Senior Design One
Update edge
Finalize pressure regulator selection
Finalize SDII Testing Plans
Order parts
Week 1
Review Senior Design One deliverables, calculations, and design criteria
Determine locations and delivery dates of all parts
Begin assembly of rocket body
Begin assembly of testing mechanisms
Week 2 – 4
Validate design
Completely assemble all subsystems
Place subsystems into entire assembly
Complete assembly on testing mechanisms
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45. Senior Design Two Schedule
Week 5 - 7
Analyze data from testing
Re-evaluate testing mechanisms and scheduling
Coordinate testing with P08105
Week 8 – 11
Retest proper conditions based on conclusions from weeks 5-7
Make project poster
Write up technical paper
Present Senior Design Two Deliverables
Ensure proper documentation of all paperwork and procedures
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46. questions comments concerns
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47. thank you
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