Launch Vehicle Selection

Slides:



Advertisements
Similar presentations
Space Science and Technology in Ukraine Yaroslav YATSKIV National Academy of Sciences of Ukraine
Advertisements

Concept Overview for 2 mt Case “2 mt case”: integrated payloads of no more than 2 mt can be landed on the surface of Mars; extension of current Mars EDL.
Less is More S. R.Kulkarni Director, Caltech Optical Observatories Chairman, SIM-Lite Science Team.
 Falcon 9 Heavy › To carry crew capsule and propellant required to rendezvous with transit vehicle Image Credit:
AAE450 Spring 2009 Ground Stations All Phases and Payloads Trenten Muller March 5, 2009 [Trenten Muller] [COM]
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 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 Descent Trajectory Hover Trajectory LD Code Integration John Aitchison March 5 th, 2009 [John Aitchison] [Mission Ops]
Project X pedition Spacecraft Senior Design – Spring 2009
AAE450 Spring 2009 Lunar Lander Preliminary propulsion system selection and design analysis Thursday, January 22, 2009 Thaddaeus Halsmer, Propulsion.
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 Launch Vehicle Performance Payload Cannon Zarinah Blockton Mission Ops~Group Earth to LEO~Phase Rover ~Phase February 19, 2009.
AAE450 Senior Spacecraft Design Poliskie - 1 T.J. Poliskie Week 7: March 1, 2007 Propulsion Earth Taxi, Mars Taxi Group Updated Propulsion System Analysis.
Rocket Power – Part 2 Introduction to Rockets and Missiles Scott Schoneman 4 Nov 03.
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
Spacecraft Launch Vehicles
Launch Opportunities for Standardized Payloads kg The 17th Annual Small Payload Rideshare Symposium June 9-11, 2015 Johns Hopkins University Applied.
AAE450 Spring 2009 Launch Vehicles Zarinah Blockton Mission Operations 1/29/2009 Blockton Ops.
AAE450 Spring 2009 Communications Ground Stations Communication Equipment Alternative Landing Method March 26, 2009 [Trent Muller] [COM]
2006 Commercial Space Transportation Forecast for Non-Geosynchronous Orbits John Sloan Federal Aviation Administration Office of Commercial Space Transportation.
Advanced Space Exploration LEO Propellant Depot: Space Transportation Impedance Matching Space Access 2010 April 8-10, 2010 Dallas Bienhoff Manager, In-Space.
Standard Form Recap – Planetary Data Sun mass kg.
TREADS Semester Review Dec. 14, Objectives Assess and Communicate Current Design Identify interfaces Approve the System Requirement Specification.
Minimalist Mars Mission Establishing a Human Toehold on the Red Planet Executive Summary DevelopSpace MinMars Team.
Mars Today 1 An immediate and inexpensive program for manned Mars visitation.
Final Slides By: Kara Akgulian Mission Ops Locomotion Phase 1.
© 2014 Orbital Sciences Corporation. All Rights Reserved. SPRSA Excess Capacity Panel Carol P. Welsch Orbital Sciences Corporation June 10, Welsch.
LEO Propellant Depot: A Commercial Opportunity? LEAG Private Sector Involvement October 1 - 5, 2007 Houston, Texas LEAG Private Sector Involvement October.
© T Madas. 1 m = cm cm = mm 10 1 km = m m = cm cm = mm 40 3 km = m m = cm cm = mm km = m cm = m 4 80.
AAE450 Spring 2009 Launch Vehicle Selection Zarinah Blockton Mission Ops~Group Earth to LEO~Phase March 5, 2009.
2005 Commercial Space Transportation Forecast for Non-Geosynchronous Orbits John Sloan Federal Aviation Administration Office of Commercial Space Transportation.
2015 in Spaceflight: A year in review Tal Inbar Head, Space Research Center The Fisher Institute for Air & Space Strategic Studies, Israel.
Mission data MissionTotal mission duration [d]Crew size [-] Total mission Δv [m/s] from LEO (including mid-course corrections) Lunar flyby Low lunar.
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.
Newton’s thought experiment: orbital velocity. Surface escape velocities Planet V escape, ft/sec Mercury13,600 Venus33,600 Earth36,700 Moon7,800 Mars16,700.
Callisto Mission LaRC Option
Cost Comparison of Higher Parking Orbit Scale up for Arbitrary Payload
CUBESATS Karla Vega Mechanical Engineering Department, Space Sciences Laboratory University of California, Berkeley.
Mass vs. Weight.
continued on next slide
TEMPO’s Commercially Hosted Payload Concept
Mars Sustainability Workshop Kennedy Space Center February 8, 2018
                                                                                                                                                                                                                                                
Week 6 Presentation Thursday, Feb 19, 2009
Attitude, Lunar Transfer Phase
continued on next slide
continued on next slide
Three-Body Trajectory Model and Spiral Transfer Matching
Lunar Descent Slide Suggestions & Questions
Solomon Westerman, PM “Polished” Final Slide Layout Week 13.
By: Josh Lukasak Attitude Group Lead Lunar Descent Phase Manager
AAE 450- Propulsion LV Stephen Hanna Design Review 02/19/01.
60% more payload to LEO from the Moon than from Earth.
Foreign Rideshare Panel
Standard Form Recap –.
Percent is really a ratio that can be used as a conversion factor.
Solomon Westerman Week3 1/29/09
[Kara Akgulian] [Mission Ops]
Standard Form Recap –.
Launch Vehicle Selection Spring Cannon Launch Vehicle Alternatives
SUPERPOWERS POLICIES EVALUATION BY REGION
continued on next slide
Sarah Shoemaker 3/20/2008 Structures, Gondola Design, Tanks, CAD Final Slides AAE 450 Spring 2008 Structures.
Complete Vehicle Systems.
continued on next slide
MARKET BRIEF NEW AND EXISTING LAUNCH VEHICLES
Presentation transcript:

Launch Vehicle Selection Zarinah Blockton Mission Ops-Earth to LEO 2/5/2009 [Blockton] [OPS]

Small Launch Vehicles Payload to LEO (kg) 2009 Launch Cost 550 kg ($M) Payload used (%) 2009 Launch Cost 2.2Mg ($M) Falcon 1e (USA) 1010 5.90 54 20.8 Taurus (USA) 1380 10.2 40 33.0 Strela (Russia) 1700 4.94 32 15.1 Long March 2D (China) 3500 4.57 16 11.6 Dnepr (Russia) 4400 4.00 13 9.63 [Blockton] [OPS]

Evaluated for 5,000 kg to LEO Evaluated for 10,000 kg to LEO [Blockton] [OPS]

Back-up Slide Clv = P((mp/mt) + E/100)*(1-i/100)^(n-2009) Clv = cost of launch vehicle for our payload mp = total payload mass deliverable to LEO mt = payload mass that we want to LEO E = Premium for piggy-backing (10%) i = inflation rate, 3.8% (from US govt. inflation stats) n = year of quote [Blockton] [OPS]

Back-up Slide

Back-up Slide [Blockton] [OPS]

Back-up Slide [Blockton] [OPS]