1. Mars Reconnaissance Orbiter 1 Overview of the Mars Reconnaissance Orbiter Mission Oct ‘01 MRO This technical data is export controlled under US law and is being transferred by JPL to ASI or its contractors pursuant to the NASA/ASI Agreement which entered into force on September 25, 2001. This technical data is transferred to ASI or its contractors for use exclusively on the NASA/ASI MRO cooperative project, may not be used for any other purpose, and shall not be re-transferred without the prior written approval of NASA

2. Mars Reconnaissance Orbiter 2 Lockheed Martin Private Data Competition Sensitive Material

3. Mars Reconnaissance Orbiter 3 PROJECT OVERVIEW Mars Reconnaissance Orbiter Salient Features 4 Earth years in Mars orbit –2 years science mapping –2 years relay mode International science payload with 30 cm resolution imaging Navigational Aid / Relay Telecom Payload Launch date August 2005 Science Characterize Mars’ seasonal cycles and diurnal variations of water, dust, and carbon dioxide. Characterize Mars’ global atmospheric structure, transport and surface changes. Search sites for evidence of aqueous and/or hydrothermal activity. Map and characterize in detail the stratigraphy, geologic structure and composition of Mars surface features Detect on Mars the presence of liquid water and determine the distribution of ground ice in the upper surface. Characterize the Martian gravity and atmosphere in greater detail. Characterize site for future landed missions.

4. Mars Reconnaissance Orbiter 4 Mission Overview Deliver a single orbiter to conduct targeted reconnaissance to further our scientific understanding of Mars and to and characterize future landing sites Launches in August of 2005 Arrival in March of 2006 Aerobrake down into the primary science orbit of 200 x 400 km by Sept of 2006 Primary science begins in late Nov 2006 and lasts for 687 Earth days ( 1 Martian Year)

5. Mars Reconnaissance Orbiter 5 MRO Organization Jim Graf Manager Richard Zurek Project Scientist Ross Jones, Project Engineer Tom Fouser (act.), Project Software Mgr Arden Acord, Launch Vehicle Liaison Bredt Martin, Business Mgr Walt Boyd, Finance& Resource Mgr Janis Norman, Secretary Erica Beam, Scheduler Marty Scarbrough, Acquisition Rep. H. Eisen Flight System Mgr R. Nybakken (act.) CTM B. Jai Mission Operations Systems Mgr D. Johnston Mission Design Mgr J. Duxbury Sci/Payload Mgr W. Mateer Dep. P/L Mgr James Graf P. Barela. Mission Assurance Mgr LMA- Orbiter Kevin McNeill Orbiter Mgr

6. J.Graf,PM R.Zurek, PS Project Science Group (PSG) SHARAD Experiment Mgr TBD, Roma Lead Payload System Engineer* B.Mateer, Acting Mars Climate Sounder JPL G.Fraschetti Radar Team (SHARAD) Gravity Team (Tracking Data) Context Imager Team Radio Science Team (Occultation/ USO Data) SHARAD Support JPL W. Johnson High Resolution Imager TBD Mars Color Imager-WAC MSSS M.Ravine Op Nav Camera JPL G.Fraschetti Context Imager MSSS M.Ravine Instruments Imaging Spectrometer TBD Atmospheric Structure Team (Aerobraking) Facility Investigations Science & Payload Office J.Duxbury, Mgr W.Mateer, Deputy TBD, Deputy PS MRO Science and Payload Office Organization *Interfaces with LMA Payload Accomodations (Tim Girard); member of JPL MRO S/C Team ** Member of MRO Mission System Design Team ***I/F with JPL Mission Design Team Approved:__sign. on file 10/8/01__ J.Graf, Proj Manager __sign. on file 10/8/01___ R.Zurek, Proj Scientist Payload System Engineers A.Dalton*** D.Norris Investigation Scientists & Ops Support A.Jerahian** LMA Payload Accommodations Manager Tim Girard Contract Negotiator N.Walizer SHARAD Instrument Alenia TBD

7. Mars Reconnaissance Orbiter 7 S/C Overview 3-m HGA 20 m^2 Solar Array (Cell Area) 4-Pi Tx/Rv LGA MGA 2x100 W(RF) TWTA 2.1 m Drag Flaps DC Brushless Motor w/16-Bit Resolvers MARCI PMIRR VNIR HRI 20 Mhz Radar (7-m Dipole Antenna) EM PM 6xMR-107N 4xMR-106B 8xMR-111C Optical Bench

8. Mars Reconnaissance Orbiter 8 Orbiter Features 1800 kg launch mass with JPL design principles compliant margins. 20 m 2 of solar array, providing ~2 kW of power. 3.0 m HGA attached directly to the bus with a 2 axis gimbal (no boom). –Design increases data rate over req’ts at maximum distance; increases data volume. Regulated multi-engine monoprop hydrazine system with engine out capability for MOI. Single set of deployments early in the mission. 3-axis stable for aerobraking. Pointing cross track and along track. Prominent risk management approach. Uses RAD750 with fast reboot capability.

9. Mars Reconnaissance Orbiter 9 Mass Status 32.4 m^2

10. Mars Reconnaissance Orbiter 10 Payload Description

11. Mars Reconnaissance Orbiter 11 Top Level Schedule

12. Mars Reconnaissance Orbiter 12 Issues for Discussion Command and data processing –Location of SOPC –Levels of processing and location of archiving –Need for quick look images Agenda for the Radar Workshop on Dec. 3 & 4 Organizational interface definition Instrument design and trade space for design options Accommodations-related issues (boom, etc.) Roles and responsibilities (off line)

13. Mars Reconnaissance Orbiter 13 Organizational Counterparts