Stephan Shurn 20 March 2008 Propulsion Final Slides Rail Guns and LITVC AAE 450 Spring 2008.

Slides:



Advertisements
Similar presentations
Rocket Engines Liquid Propellant –Mono propellant Catalysts –Bi-propellant Solid Propellant –Grain Patterns Hybrid Nuclear Electric Performance Energy.
Advertisements

AAE 450 Spring Brandon White 3/20/2008 Structures Group Contact Inert Mass Standard Deviation Justification Other Work.
Design Goals Saturn V Ariane 4 Pegasus Vanguard Bellerophon ? ? ?
AAE450 Spring 2009 Propellant Choice and Mass Estimates for the Translunar OTV Week 2 Presentation Thursday, Jan 22, 2009 Brad Appel Propulsion Group.
AAE450 Spring 2009 Slide 1 of 7 Orbital Transfer Vehicle (OTV) Thermal Control Ian Meginnis February 26, 2009 Group Leader - Power Systems Phase Leader.
AAE450 Spring 2009 Slide 1 of 8 Orbital Transfer Vehicle (OTV) Masses and Costs Ian Meginnis March 12, 2009 Group Leader - Power Systems Phase Leader -
AAE 450 Spring 2008 Dana Lattibeaudiere February 7, 2008 New Code Developments.
AAE450 Spring 2009 Lander Phase: Hybrid Propulsion System Propulsion System Sizing and Inert Mass Analysis Hopper and Rover Designs for 10kg Payload Hopper.
AAE450 Spring 2009 Analysis of Trans-Lunar Spiral Trajectory [Levi Brown] [Mission Ops] February 12,
AAE450 Spring 2009 Final Sizing and Trajectory Design for 100 g/10kg Payloads [Levi Brown] [Mission Ops] March 12,
AAE450 Spring 2009 Project X pedition Final slides outline for Orbital Transfer Vehicle Propulsion Week 11 Presentation Thursday, March 26, 2009 Brad Appel.
AAE450 Spring 2009 Tony Cofer Power Group TLI Phase 03/05/09 Power Limitations for Arbitrary Payload Tony Cofer] [Power] page 1.
AAE450 Spring 2009 Translunar Orbit Transfer Vehicle (OTV): Propulsion System Setup for 100g & 10 kg Case Launch Vehicle Selection for Arbitrary Case Thermal.
AAE450 Spring 2009 Descent Trajectory Hover Trajectory LD Code Integration John Aitchison March 5 th, 2009 [John Aitchison] [Mission Ops]
AAE450 Spring 2009 Translunar OTV (Orbital Transfer Vehicle) : Chemical Propulsion System Refined estimates: OTV WET Mass, Propellant Volume & Propellant.
AAE450 Senior Spacecraft Design Catherine Frey Week 8: March 8 th, 2007 Propulsion Group, Transfer Vehicle Group, Mars Launch Vehicle Group, aM/aE/dM/dE.
Bellerophon 1kg Exploded View Sarah Shoemaker. Spin Table 3 rd Stage Engine 2 nd Stage Avionics 2 nd Stage Engine 2 nd Stage Propellant Tank 2 nd Stage.
AAE 450 Spring 2008 Chris Strauss Aerothermodynamics-Rocket Geometry Scaling Vanguard.
Parachutes Supersonic portion – Hemisflo Ribbon Most practical for velocities up to Mach 3 Subsonic portion – Ringsail Parachutes Historically proven success.
A spring with a mass of 6 kg has damping constant 33 and spring constant 234. Find the damping constant that would produce critical damping
AAE 450 Spring 2008 Ricky Hinton March 27 th, 2008 Propulsion Group Nozzle, Test Facility (back-up slides)
AAE 450 Spring 2008 Michael Walker January 17 th 2007 Dynamics and Controls Group Contact Control Methods Research, 1-d Corrections.
AAE 450 Spring 2008 Stephan Shurn 31 January 2008 Propulsion Rail Gun Feasability.
1 AAE 450 Spring 2008 Stephen Bluestone March 20, 2008 Propulsion Final Presentation Slides 1.
Rockets Tuesday: Rocketry Wednesday: Meet in my room 601: hydrogen demo and Quiz over rocketry. Thursday: Satellites and Orbital Mechanics Friday: Satellites,
AAE 450 Spring 2008 Nicole Wilcox March 20 th, 2008 Propulsion Engine Performance Characteristics Breakdown Propellant and Pressurant Final Slides Propulsion.
Dana Lattibeaudiere February 21, 2008 Propulsion Nozzle Design Injectors Assistance from Nicole Wilcox & Stephen Bluestone AAE 450 Spring 2008.
AAE 450 Spring 2008 Stephen Bluestone February 28, 2008 Propulsion Group Historic Solid Rocket Failure Probability.
AAE 450 Spring Brandon White 2/14/2008 Structures Group Contact Inertia Matrix Math Model Tank Buckling Math Model.
AAE 450 Spring 2008 Danielle Yaple 6 March 2008 Avionics Group, GC, CAD, MAT Final Slides 1.
AAE450 Spring 2009 Lunar Lander Main Engine Thaddaeus Halsmer Thursday, February 12, 2009 Thaddaeus Halsmer, Propulsion.
AAE 450 Spring 2008 Dynamics and Control 3 Periapsis Histogram(7131 cases)
AAE 450 Spring 2008 Propulsion Back-Up Slides Propulsion.
AAE450 Spring 2009 Lander Phase: Hybrid Propulsion System Propellant Tank Sizing and Pressure Analysis Thermodynamic analysis on Hydrogen peroxide Tanks.
AAE 450 Spring 2008 Steven (“CJ”) Hiu 03/27/2008 “Thank You For The Memories” MAT & FAM Coder – Structures Composite Tanks Analysis CAD – Tanks, Intertank.
AAE 450 Spring 2008 Danielle Yaple 6 March 2008 Avionics Group, GC, CAD, MAT Costs 1.
AAE 450 Spring 2008 Stephanie Morris 3/6/08 Propulsion Final Propellant and Pressurant Cost Thanks to Nicole Wilcox!
AAE 450 Spring 2008 Vince Teixeira 7 February 2008 Structures Nose Cone Design/Heating Analysis.
ChemE 260 Foundation of Thermodynamics March 29, 2005 Dr. William Baratuci Senior Lecturer Chemical Engineering Department University of Washington TCD.
Example Steam enters a turbine at 1200 kPa and 350°C and it exits at 100 kPa, 150°C. The water mass flow rate through the turbine is 2 kg/s. Determine.
AAE 450 – Spacecraft Design Sam Rodkey 1 Active Thermal Control Design Sam Rodkey March 1 st, 2005 Project Management Project Manager.
ChemE 260 Transient Mass and Energy Balances April 20, 2005 Dr. William Baratuci Senior Lecturer Chemical Engineering Department University of Washington.
AAE450 Spring 2009 Final Lander Volume and Mass 10kg, 100g, Arbitrary March 12, 2009 Lunar Descent Phase Group [Ryan Nelson] [STRC] 1.
AAE450 Spring 2009 Power Systems for Lander Adham Fakhry [Adham Fakhry] [Power]
AAE 450 Spring 2008 Stephanie Morris 2/21/08 Propulsion Standard Deviations.
AAE 450 Spring 2008 Stephan Shurn 31 January 2008 Propulsion Thrust Vector Control.
The Wright brothers are the two famous men who invented a type of aircraft that could fly. The Wright brothers started to made more and more different.
AAE 450 Spring Brandon White 2/28/2008 Structures Group Contact Inertia Matrix Math Model (Final)
Gas Bottle Blow-Down Analysis. Introduction This lesson provides the means to estimate the gas state in a pressure vessel during or after depressurization.
Design of the thermosiphon Test Facilities 2nd Thermosiphon Workshop
Steven (“CJ”) Hiu 02/20/2008 Congratulations MAT Coders
Dana Lattibeaudiere March 27, 2008 Propulsion Code Outputs (Thanks Stephen Bluestone, John Beasley, Nicole Wilcox) Mass Deviations – Solids Project Logo.
Stephan Shurn 28 February 2008 Propulsion Thrust Vector Control
Steven Hiu (“CJ”) 02/07/2008 Structural Analysis Model Analysis Team Function Code Structural Sizing & Optimization AAE 450 Spring 2008.
In-situ Propellant Production and ERV Propulsion System
Maximum work or available energy from a system
Jayme Zott Aerothermodynamics Aerodynamic Loads Special thanks to Alex Woods, CJ Hiu and the entire trajectory group AAE 450 Spring 2008.
Ricky Hinton January 24th, 2008 Propulsion Group Preliminary Analysis of Purdue Test Facilities at Zucrow Laboratories AAE 450 Spring 2008.
Brandon White 3/20/2008 Structures Group Contact Inert Mass Standard Deviation Justification Other Work AAE 450 Spring 2008.
Ricky Hinton February 21st, 2008 Propulsion Group CAD group Updated Altitude vs. Pressure Code and Nozzle CAD AAE 450 Spring 2008.
John Beasley 3/20/2008 Propulsion Group Contact: Black Boxes and Code Flowchart AAE 450 Spring 2008.
Brandon White 1/31/2008 Structures Group Contact Interface Loads Inertia Matrices / Structures Code AAE 450 Spring 2008.
Thermal Energy.
Vince Teixeira 6 March 2008 Structures Nose Cone “Sarah” Shear Analysis CAD AAE 450 Spring 2008.
Week 4 Presentation Thursday, Feb 5, 2009
Nicole Wilcox March 20th, 2008 Propulsion Engine Performance Characteristics Breakdown Propellant and Pressurant Final Slides AAE 450 Spring 2008 Propulsion.
Jayme Zott Aerothermodynamics Aerodynamic Loads Special thanks to Alex Woods, CJ Hiu and the entire trajectory group AAE 450 Spring 2008.
Energy Part 3 – Hooke’s Law.
Parachutes Changed Supersonic portion of descent
Sarah Shoemaker 3/20/2008 Structures, Gondola Design, Tanks, CAD Final Slides AAE 450 Spring 2008 Structures.
Presentation transcript:

Stephan Shurn 20 March 2008 Propulsion Final Slides Rail Guns and LITVC AAE 450 Spring 2008

Rail Guns Removed due to several factors: High G’s; ~2,000 g’s at 100m to ~101 g’s at 2km length High energy input starting at ~ 20,000 kW and high current ~13,000 A High heat loading on nose and body ~3000K High amount of technology development AAE 450 Spring 2008 Propulsion

LITVC 1st and 2nd stage control 4 valves per stage for perpendicular to centerline injection of H2O2 1st stage tap-off of main H2O2 tank 2nd stage bring own H2O2 pressurized tank Considered main part of engine for weight/cost due to low complexity Costs include: 4 valves per stage @ $100/valve Extra propellant Extra tank on 2nd stage AAE 450 Spring 2008 Propulsion

LITVC Weight Vehicle Stage Propellant Mass (kg) 200 g 1 17.88 2 4.4 3 Total 22.27 1 kg 28.44 10.11 38.55 5 kg 24.87 30.28 55.15 AAE 450 Spring 2008 Propulsion