Project M.E.T.E.O.R.

P07109: Flying Rocket TeamAndrew Scarlata, Geoff Cassell, Zack Mott, Garett

Pickett, Brian Whitbeck, Luke Cadin, David Hall

M.E.T.E.OM.E.T.E.OS.S.R. Overview R. Overview Immediate goal is to prove ability to launch a Immediate goal is to prove ability to launch a

hybrid rocket using Nitrous Oxide and HTPB hybrid rocket using Nitrous Oxide and HTPB carrying a small payload to the boundary of carrying a small payload to the boundary of space.space.

Long-term goal is to launch payloads both Long-term goal is to launch payloads both into space and to land them on NEO’s.into space and to land them on NEO’s.

Meteor rocket is carried to altitude by Meteor rocket is carried to altitude by weather balloons, released, and propels weather balloons, released, and propels itself into orbit.itself into orbit.

Our ObjectivesOur Objectives Responsible for integration of Steel Rocket and Responsible for integration of Steel Rocket and

Guidance teams’ systems.Guidance teams’ systems. Optimized Fuel Grain, Combustion chamber, Nozzle Optimized Fuel Grain, Combustion chamber, Nozzle

and Injector designs.and Injector designs. Thrust Vectoring and guidance systems. Thrust Vectoring and guidance systems.

Research materials that satisfy the design Research materials that satisfy the design requirements.requirements.

Design, Manufacture, Test and Launch Single Design, Manufacture, Test and Launch Single Stage RocketStage Rocket

Research shows that successful rockets adhere Research shows that successful rockets adhere to a 1:10 structure to propellant ratio. The to a 1:10 structure to propellant ratio. The minimum requirement is 2:10.minimum requirement is 2:10.

Rocket Design ConceptsRocket Design Concepts Five designsFive designs

ClassicClassic ChaliceChalice Embedded Fuel GrainEmbedded Fuel Grain Exterior Nitrous Oxide Exterior Nitrous Oxide

TanksTanks Annular Nitrous Oxide Annular Nitrous Oxide

TankTank

Hot means Owwie!

Classic ConceptClassic Concept Constant radius Constant radius

dimensions determined dimensions determined by Fuel Grainby Fuel Grain

AdvantagesAdvantages Easy to manufactureEasy to manufacture All subsystems can be All subsystems can be

contained within outer contained within outer shellshell

DisadvantagesDisadvantages Extreme length requires Extreme length requires

excess weightexcess weight Guarantees custom Guarantees custom

Nitrous TankNitrous Tank

HTPB Fuel Grain

Nitrous Oxide Tank

Pre-Combustion Chamber

Post-Combustion Chamber

Graphite Nozzle

Helium ReservoirElectronics

PayloadMicro IMU(Inertial Measurement Unit)

Composite Outer Shell(Possibly Aluminum Reinforced)

Micro IMUProvides serial digital outputs of tri-axial acceleration, rate of turn (gyro) and tri-axial magnetic field data.

PayloadPico-Satellite

ElectronicsAvionics and Data Acquisition

Helium Reservoir

HTPB Fuel Grain(Solid Fuel)

Pre-Combustion ChamberMoldable Ceramic, acts also asan insulator for the composite shell

Nitrous Oxide Tank (Liquid Fuel)

Post-Combustion ChamberMoldable Ceramic, acts also asan insulator for the composite shell

HTPB Fuel Grain(Solid Fuel)

Graphite Nozzle Currently replicates the steel rocket design

Chalice ConceptChalice Concept Dimensions determined Dimensions determined

by Nitrous Tankby Nitrous Tank AdvantagesAdvantages

Reduced weight due to Reduced weight due to aspect ratio and variable aspect ratio and variable radiusradius

All subsystems contained All subsystems contained within shellwithin shell

Accommodates varied Accommodates varied payload geometriespayload geometries

Potential for off the shelf Potential for off the shelf Nitrous tankNitrous tank

DisadvantagesDisadvantages Complex geometries Complex geometries

complicate productioncomplicate production

HTPB Fuel Grain

Nitrous Oxide Tank

Pre-Combustion Chamber

Post-Combustion Chamber

Graphite Nozzle

Helium ReservoirElectronics

PayloadMicro IMU(Inertial Measurement Unit)

Composite Outer Shell(Aluminum Inner Reinforced)

Micro IMU

PayloadPico-Satellite

ElectronicsAvionics and Data Acquisition

Helium Reservoir

HTPB Fuel Grain(Solid Fuel)

Combustor

Pre-Combustion Chamber

Nitrous Oxide Tank (Liquid Fuel)

Post-Combustion Chamber

HTPB Fuel Grain(Solid Fuel)

Graphite Nozzle – Replicates the steel rocket design

Embedded Fuel GrainEmbedded Fuel Grain Dimensions determined Dimensions determined

by nitrous tankby nitrous tank AdvantagesAdvantages

Reduced Pressure Reduced Pressure Differential surrounding fuel Differential surrounding fuel graingrain

Single tank forms main Single tank forms main body surrounding engine body surrounding engine assembly on all but nozzle assembly on all but nozzle sideside

DisadvantagesDisadvantages Complex structural designComplex structural design

HTPB Fuel Grain

Nitrous Oxide Tank

Pre-Combustion Chamber

Post-Combustion Chamber

Graphite Nozzle

Helium Reservoir Vessel

Electronics

Payload

Micro IMU(Inertial Measurement Unit)

Composite Outer Shell(Aluminum Inner Liner)

Siphon Tube

Micro IMU

PayloadPico-Satellite

ElectronicsAvionics and Data Acquisition

Helium Reservoir

HTPB Fuel Grain(Solid Fuel)

Pre-Combustion Chamber

Nitrous Oxide Tank (Liquid Fuel)

Post-Combustion Chamber

HTPB Fuel Grain(Solid Fuel)

Graphite Nozzle Steel rocket replica

Siphon Tube

Other ConceptsOther Concepts External Nitrous TanksExternal Nitrous Tanks

Four External tanks mount Four External tanks mount outside of main body, outside of main body, providing more compact providing more compact rocket, but added cost.rocket, but added cost.

Annular Nitrous TankAnnular Nitrous Tank Single tank mounts around Single tank mounts around

main body, providing more main body, providing more structural strength but structural strength but added weight and cost.added weight and cost.

ConceptsA B C D E

Selection Criteria Weight Rating Weighted Score

Rating Weighted Score

Rating Weighted Score

Rating Weighted Score

Rating Weighted Score

Durability 15% 4 0.6 3 0.45 2 0.3 1 0.15 1 0.15Safety 15% 3 0.45 3 0.45 2 0.3 2 0.3 2 0.3

Temperature Consideration 10% 3 0.3 3 0.3 2 0.2 3 0.3 4 0.4

Ease of Manufacture 20% 4 0.8 3 0.6 2 0.4 1 0.2 1 0.2

Weight 25% 2 0.5 4 1 2 0.5 2 0.5 3 0.75Cost 15% 4 0.6 4 0.6 3 0.45 1 0.15 2 0.3

0 0 0 0 0

0 0 0 0 0

0 0 0 0 0

100% 0 0 0 0 0

Total Score

Rank

Continue? No Yes No No No

Annular TankEmbedded Fuel

Grain

2.15

Ext. Tanks

1.60 2.10

(reference)

3.25 3.40

Classic Chalice

Material ConceptsMaterial ConceptsResearched metal, ceramic and fibrous Researched metal, ceramic and fibrous

and honeycomb composite possibilitiesand honeycomb composite possibilitiesMetals and ceramics are cheap, easy to Metals and ceramics are cheap, easy to

manufacture, however are too heavy for manufacture, however are too heavy for this application by themselves.this application by themselves.

Composites may not hold up to heat, Composites may not hold up to heat, pressure and acceleration stresses.pressure and acceleration stresses.

Solution may be hybrid: composite Solution may be hybrid: composite overwound aluminum.overwound aluminum.

Nitrous Oxide: Self PressurizationNitrous Oxide: Self Pressurization Rely on self pressurizing Rely on self pressurizing

characteristics of Nitrous Oxide(Ncharacteristics of Nitrous Oxide(N220) to 0) to drive liquid Ndrive liquid N220 flow0 flow

Vapor pressure a very strong function Vapor pressure a very strong function of temperatureof temperature

Atmospheric temperatures during Atmospheric temperatures during balloon ascent as low as -57 degrees balloon ascent as low as -57 degrees Celsius, will cool NCelsius, will cool N2200

Clear need to carefully regulate Clear need to carefully regulate temperature pressure, likely target temperature pressure, likely target range between 20 and 30 Celsius (734 range between 20 and 30 Celsius (734 to 916 psi).to 916 psi).

Temperature Temperature (Celcius)(Celcius) Pressure (psi)Pressure (psi)

-50-50 9494

-40-40 137137

-30-30 192192

-20-20 261261

-10-10 348348

00 454454

55 514514

1010 581581

1515 654654

2020 734734

2525 821821

3030 916916

3535 10201020

36.4236.42 10521052

Self PressurizationSelf Pressurization

Furthermore, critical temperature of NFurthermore, critical temperature of N220 is 36.42 0 is 36.42 Celsius; past the critical point, most thrust will be Celsius; past the critical point, most thrust will be lostlost

Would need to develop accurate heat transfer Would need to develop accurate heat transfer model to insure tank would be kept at proper model to insure tank would be kept at proper temperaturetemperature

Insulation and heater will be requiredInsulation and heater will be required

Helium Gas PressurizationHelium Gas Pressurization Would use separate tank of Helium at high Would use separate tank of Helium at high

pressure (regulated to desired pressure) to pressure (regulated to desired pressure) to pressurize Npressurize N220 tank0 tank

Helium pressure will be much less temperature Helium pressure will be much less temperature sensitive and will be able to supply pressure sensitive and will be able to supply pressure reliably that we needreliably that we need

Provide constant pressure (and hence thrust) Provide constant pressure (and hence thrust) throughout entire burn timethroughout entire burn time

Will add weight to system, which is at a premiumWill add weight to system, which is at a premium

Schedule for rest of SD1Schedule for rest of SD1Week 6: Intense revision of concept for final selection, further material research/selection, further modeling of concept.

Week 7: Start basic system design, begin risk and engineering analysis, continued modeling of design.

Week 8: Continue FEA analysis, complete proof of concept, begin material purchasing, complete design modeling.

Week 9: Completion of basic system design, prepare for Design Review, continue material purchasing.

Week 10: Plan for SD2, continuation of system design, material purchasing.

Hot means Owwie!

Questions?Questions?

Thank YouThank You