Solomon Westerman Week3 1/29/09

Slides:

Advertisements

Similar presentations

AAE450 Spring 2009 Reliability Analysis Solomon Westerman, PM Week 5, 2/12/09 [Solomon Westerman] [PM] 1.

Advertisements

Ares V RFI Point of Departure Information Package

Lessons from Apollo * Data from NASA Apollo 11 Press Kit Shows spacecraft weight delivered to LEO (Low Earth Orbit) Shows weights for each portion of Apollo.

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 Final Presentation Draft Slides Description: Some draft slides and ideas 3/26/09 Kris Ezra Attitude 1.

AAE450 Spring 2009 Time to Complete 50m/s ΔV & 100g Payload System Overview Brittany Waletzko 100g Payload Integration Manager Translunar/OTV Phase Week.

AAE450 Spring 2009 Hopper Trajectory February 26, 2009 [Alex Whiteman] [Mission Ops] [Lunar Descent] Page 1.

AAE450 Spring 2009 Arbitrary Payload Cost Optimization to LLO Tasks: Payload Cost / Mass Optimization (Launch to LLO) Disprove Momentum Transfer Alternative.

The Lander is at a 25 km Lunar altitude and an orbital period of approximately 110 minutes. After separation occurs the Lander is completely self sufficient.

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 -

AAE450 Spring 2009 Brian Erson Attitude Control Systems Trans Lunar Phase Alternative Design Analysis Cold Xe Gas Thrusters [Brian Erson] [Attitude] 1.

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 Attitude Control – Arbitrary Payload Christine Troy Assistant Project Manager Webmaster Lunar Descent Attitude Control Analysis Design.

AAE450 Spring 2009 Final Sizing and Trajectory Design for 100 g/10kg Payloads [Levi Brown] [Mission Ops] March 12,

AAE450 Spring 2009 Week 4 Presentations [Solomon Westerman][PM]

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 LEO Atmospheric Drag Analysis and Lunar Orbit Circularization [Andrew Damon] [Mission Ops] February 19,

AAE450 Spring 2009 Lunar Descent Final Numbers Josh Lukasak Attitude Group Lead Lunar Decent Phase Lead 03/12/09 [Josh Lukasak] [Attitude] (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 Week 6 [Solomon Westerman] [PM] PDR Complete! Check the website if you have any mission requirement questions!

AAE450 Spring Gram Mission Integration and Model Korey LeMond STRC/THM/INTEG GL [Korey LeMond] [STRC/THM/INTEG/CAD GL, OTV Phase] 1.

AAE450 Spring 2009 Cost Analysis, Redux Solomon Westerman Week9: 3/12/09 [Solomon Westerman][PM]Page 1/3.

Project X pedition Spacecraft Senior Design – Spring 2009

AAE450 Spring 2009 Mass Savings and Finite Element Analysis (FEA) Preparation for Orbital Transfer Vehicle (OTV) 100 gram Case Tim Rebold STRC [Tim Rebold]

AAE450 Spring 2009 Lunar Lander Preliminary propulsion system selection and design analysis Thursday, January 22, 2009 Thaddaeus Halsmer, Propulsion.

AAE450 Spring 2009 Translunar OTV (Orbital Transfer Vehicle) : Chemical Propulsion System Refined estimates: OTV WET Mass, Propellant Volume & Propellant.

AAE450 Spring 2009 Lunar Capture Altitude Mass to LLO for Arbitrary Time to Rotate Lander During Descent Camera/Dust Removal [Kara Akgulian] [Mission Ops]

AAE450 Spring 2009 Hopper Design Alternative Josh Lukasak Attitude Group Lead Lunar Decent Phase Lead 02/26/09 [Josh Lukasak] [Attitude] (1)

AAE450 Spring 2009 Presentation Notes 1.Good Q&A Becoming ‘experts’ on your system! 2.Give background information / assumptions [Solomon Westerman] [PM]

AAE450 Spring 2009 X 0 Power System Solar - Battery Solar arrays Tony Cofer- Power System.

AAE450 Spring 2009 Week 4 Project Timeline [Solomon Westerman] [PM]

AAE450 Spring 2009 Launch Vehicle Performance Payload Cannon Zarinah Blockton Mission Ops~Group Earth to LEO~Phase Rover ~Phase February 19, 2009.

AAE450 Senior Spacecraft Design Project Aquarius Kowalkowski - 1 Mike Kowalkowski Week 4: February 8 th 2007 Project Aquarius Power Engineering Habitat.

Targeted Outcome: Phase , Safeguarding our Outbound Journey Determine Extremes of the Variable Radiation & Space Environments at Earth, Moon,

Propulsion Engineering Research Center NASA Technology Roadmap: Launch Propulsion Systems Robert J. Santoro The Propulsion Engineering Research Center.

AAE450 Spring 2009 Launch Vehicles Zarinah Blockton Mission Operations 1/29/2009 Blockton Ops.

AAE450 Spring 2009 Support structure for Orbital Transfer Vehicle (OTV) Tim Rebold STRC [Tim Rebold] [STRC] [1]

AAE450 Spring 2009 Brian Erson Attitude Control Systems Trans Lunar Phase Alternative Design Comparison [Brian Erson] [Attitude] 1.

AAE450 Spring 2009 Primary structure for Orbital Transfer Vehicle (OTV) Tim Rebold STRC [Tim Rebold] [STRC]

AAE450 Spring 2009 Launch Vehicle Selection Zarinah Blockton Mission Ops~Group Earth to LEO~Phase March 5, 2009.

Preliminary Cost Analysis Principles of Space Systems Design U N I V E R S I T Y O F MARYLAND Preliminary Cost Analysis Cost Sources Vehicle-level Costing.

AAE 450 Spring 2010 AAE 450 2/11/2010 Kathy Brumbaugh Chris Spreen

AAE450 Spring 2009 Lander Sizing and Launch Vibrations Feb. 12, 2009 Earth Launch/Lunar Descent Phase Group 1 [Ryan Nelson] [STRC]

Callisto Mission LaRC Option

Cost Comparison of Higher Parking Orbit Scale up for Arbitrary Payload

PROJECT PROPOSAL.

Cost Concepts and Design Economics

Week 6 Presentation Thursday, Feb 19, 2009

Attitude, Lunar Transfer Phase

Three-Body Trajectory Model and Spiral Transfer Matching

Architecture Selection Logic

Ian Meginnis January 29, 2009 Group Leader - Power Systems

Lunar Descent Slide Suggestions & Questions

Lunar Descent Trajectory

Orbital Transfer Vehicle (OTV) Power Systems

Solomon Westerman, PM “Polished” Final Slide Layout Week 13.

By: Josh Lukasak Attitude Group Lead Lunar Descent Phase Manager

Final Presentation Slides

Launch Vehicle Selection

[Solomon Westerman] [PM]

Lunar Descent Trajectory

Propulsion – Attitude Control Casey Kirchner

Lunar Descent Trajectory Optimization

Week 4 Presentation Thursday, Feb 5, 2009

Launch Vehicle Selection Spring Cannon Launch Vehicle Alternatives

Solving One-Step Equations

Ian Meginnis January 29, 2009 Group Leader - Power Systems

Presentation transcript:

Solomon Westerman Week3 1/29/09 Cost Analysis Solomon Westerman Week3 1/29/09 Page 1/3 [Solomon Westerman][PM]

Cost Breakdown Structure (CBS) XPrize Level 1: Mission Earth->LEO Translunar Lunar Descent Locomotion Overhead Level 2: Phase Launch Vehicle Avionics Integration Propellant Engine Power Avionics Integration Propellant Engine Power Avionics Integration Power Avionics Integration Development Salary License Fee Level 3: System $47.1 M (Delta II) $12.8 M (Dnepr) $3.4 M $1.4 M $0.2 M $5.7 M Total Xo Mission Cost: $25.4M for Dnepr, $57.8M for Delta II Page 2/3 [Solomon Westerman][PM]

[Solomon Westerman][PM] Cost Algorithms Launch Vehicle (LV) Hardware Integration Variable Description Clv Our LV cost P Book LV cost mp* Our mass to LEO mt* Deliverable mass to LEO E Piggy-back premium % i Inflation % n Year of book cost Variable Description Chw Our hardware cost P Quote/Estimate of existing system Cm* Needed capability Ct* Existing capability X Military/NASA quote? (1 or 0) F Algebraic quote reduction factor i Inflation % n Year of quote Variable Description Cint Our integration cost R Labor cost / hour N Number of workers Hw Hours required per worker *Note: require mp/mt < .7 *Note: require Cm/Ct > .6 Page 3/3 [Solomon Westerman][PM]

[Solomon Westerman][PM] Backup Slides [Solomon Westerman][PM]

Preliminary Cost Estimation Technique Use cost algorithms with the following inputs for Xo LV (Use Delta II and Dnepr) Source: www.futron.com (Trends in Price per Pound to Orbit) Use 5% of Clv for integration/avionics costs OTV $1800 prop cost from Brad’s second week presentation $40,000 solar array from Tony $2,000,000 engine cost (estimated) $100,000 electronics package from Trent (adjusted) $500,000 avionics package (estimated) 30% integration cost from prop/engine/avionics Lander $1,100 propellant cost from Ryan $500,000 engine cost (estimated) [Solomon Westerman][PM]

Preliminary Cost Estimation Technique Rover $40,000 solar array from Tony $100,000 electronics package from Trent (adjusted) 30% integration cost from total power and avionics Overhead 10 engineers @ $100,000/year for 3 years = $3M 3 STK license @ $400,000 each = $1.2M 10 MATLAB licenses @ $150,000 = $1.5M [Solomon Westerman][PM]