Project M.E.T.E.O.R. P07109: Flying Rocket Team Andrew Scarlata, Geoff Cassell, Zack Mott, Garett Pickett, Brian Whitbeck, Luke Cadin, David Hall

M.E.T.E.O S. R. Overview Immediate goal is to prove ability to launch a hybrid rocket using Nitrous Oxide and HTPB carrying a small payload to the boundary of space. Immediate goal is to prove ability to launch a hybrid rocket using Nitrous Oxide and HTPB carrying a small payload to the boundary of space. Long-term goal is to launch payloads both into space and to land them on NEO’s. Long-term goal is to launch payloads both into space and to land them on NEO’s. Meteor rocket is carried to altitude by weather balloons, released, and propels itself into orbit. Meteor rocket is carried to altitude by weather balloons, released, and propels itself into orbit.

Our Objectives Responsible for integration of Steel Rocket and Guidance teams’ systems. Responsible for integration of Steel Rocket and Guidance teams’ systems. Optimized Fuel Grain, Combustion chamber, Nozzle and Injector designs. Optimized Fuel Grain, Combustion chamber, Nozzle and Injector designs. Thrust Vectoring and guidance systems. Thrust Vectoring and guidance systems. Research materials that satisfy the design requirements. Research materials that satisfy the design requirements. Design, Manufacture, Test and Launch Single Stage Rocket Design, Manufacture, Test and Launch Single Stage Rocket Research shows that successful rockets adhere to a 1:10 structure to propellant ratio. The minimum requirement is 2:10. Research shows that successful rockets adhere to a 1:10 structure to propellant ratio. The minimum requirement is 2:10.

Rocket Design Concepts Five designs Five designs Classic Classic Chalice Chalice Embedded Fuel Grain Embedded Fuel Grain Exterior Nitrous Oxide Tanks Exterior Nitrous Oxide Tanks Annular Nitrous Oxide Tank Annular Nitrous Oxide Tank Hot means Owwie!Hot means Owwie!

Classic Concept Constant radius dimensions determined by Fuel Grain Constant radius dimensions determined by Fuel Grain Advantages Advantages Easy to manufacture Easy to manufacture All subsystems can be contained within outer shell All subsystems can be contained within outer shell Disadvantages Disadvantages Extreme length requires excess weight Extreme length requires excess weight Guarantees custom Nitrous Tank Guarantees custom Nitrous Tank

HTPB Fuel Grain Nitrous Oxide Tank Pre-Combustion Chamber Post-Combustion Chamber Graphite Nozzle Helium Reservoir Electronics Payload Micro IMU (Inertial Measurement Unit) Composite Outer Shell (Possibly Aluminum Reinforced)

Micro IMU Provides serial digital outputs of tri- axial acceleration, rate of turn (gyro) and tri-axial magnetic field data. Payload Pico-Satellite Electronics Avionics and Data Acquisition Helium Reservoir

HTPB Fuel Grain (Solid Fuel) Pre-Combustion Chamber Moldable Ceramic, acts also as an insulator for the composite shell Nitrous Oxide Tank (Liquid Fuel)

Post-Combustion Chamber Moldable Ceramic, acts also as an insulator for the composite shell HTPB Fuel Grain (Solid Fuel) Graphite Nozzle Currently replicates the steel rocket design

Chalice Concept Dimensions determined by Nitrous Tank Dimensions determined by Nitrous Tank Advantages Advantages Reduced weight due to aspect ratio and variable radius All subsystems contained within shell Accommodates varied payload geometries Potential for off the shelf Nitrous tank Disadvantages Disadvantages Complex geometries complicate production

HTPB Fuel Grain Nitrous Oxide Tank Pre-Combustion Chamber Post-Combustion Chamber Graphite Nozzle Helium Reservoir Electronics Payload Micro IMU (Inertial Measurement Unit) Composite Outer Shell (Aluminum Inner Reinforced)

Micro IMU Payload Pico-Satellite Electronics Avionics 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 Grain Dimensions determined by nitrous tank Dimensions determined by nitrous tank Advantages Advantages Reduced Pressure Differential surrounding fuel grain Reduced Pressure Differential surrounding fuel grain Single tank forms main body surrounding engine assembly on all but nozzle side Single tank forms main body surrounding engine assembly on all but nozzle side Disadvantages Disadvantages Complex structural design Complex 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 Payload Pico-Satellite Electronics Avionics 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 Concepts External Nitrous Tanks External Nitrous Tanks Four External tanks mount outside of main body, providing more compact rocket, but added cost. Four External tanks mount outside of main body, providing more compact rocket, but added cost. Annular Nitrous Tank Annular Nitrous Tank Single tank mounts around main body, providing more structural strength but added weight and cost. Single tank mounts around main body, providing more structural strength but added weight and cost.

Material Concepts Researched metal, ceramic and fibrous and honeycomb composite possibilities Researched metal, ceramic and fibrous and honeycomb composite possibilities Metals and ceramics are cheap, easy to manufacture, however are too heavy for this application by themselves. Metals and ceramics are cheap, easy to manufacture, however are too heavy for this application by themselves. Composites may not hold up to heat, pressure and acceleration stresses. Composites may not hold up to heat, pressure and acceleration stresses. Solution may be hybrid: composite overwound aluminum. Solution may be hybrid: composite overwound aluminum.

Nitrous Oxide: Self Pressurization Rely on self pressurizing characteristics of Nitrous Oxide(N 2 0) to drive liquid N 2 0 flow Rely on self pressurizing characteristics of Nitrous Oxide(N 2 0) to drive liquid N 2 0 flow Vapor pressure a very strong function of temperature Vapor pressure a very strong function of temperature Atmospheric temperatures during balloon ascent as low as -57 degrees Celsius, will cool N 2 0 Atmospheric temperatures during balloon ascent as low as -57 degrees Celsius, will cool N 2 0 Clear need to carefully regulate temperature pressure, likely target range between 20 and 30 Celsius (734 to 916 psi). Clear need to carefully regulate temperature pressure, likely target range between 20 and 30 Celsius (734 to 916 psi). Temperature (Celcius) Pressure (psi)

Self Pressurization Furthermore, critical temperature of N 2 0 is Celsius; past the critical point, most thrust will be lost Furthermore, critical temperature of N 2 0 is Celsius; past the critical point, most thrust will be lost Would need to develop accurate heat transfer model to insure tank would be kept at proper temperature Would need to develop accurate heat transfer model to insure tank would be kept at proper temperature Insulation and heater will be required Insulation and heater will be required

Helium Gas Pressurization Would use separate tank of Helium at high pressure (regulated to desired pressure) to pressurize N 2 0 tank Would use separate tank of Helium at high pressure (regulated to desired pressure) to pressurize N 2 0 tank Helium pressure will be much less temperature sensitive and will be able to supply pressure reliably that we need Helium pressure will be much less temperature sensitive and will be able to supply pressure reliably that we need Provide constant pressure (and hence thrust) throughout entire burn time Provide constant pressure (and hence thrust) throughout entire burn time Will add weight to system, which is at a premium Will add weight to system, which is at a premium

Schedule for rest of SD1 Week 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!Hot means Owwie!

Questions? Thank You