Moon Express Summary. Dr. Andrew Aldrin President, Moon Express, Inc. 12 June, Science Network. Sample Return ME-1: GLXP

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1 Science Network Moon Express Summary Sample Return Dr. Andrew Aldrin President, Moon Express, Inc. 12 June, Sub-Satellite Deployment ME-1: GLXP ISRU / Resource Prospecting Polar Astronomy Moon Express, Inc.

The Executive Team Proven track records of business & technical experience Board Naveen

Robert (Bob) Richards Cofounder, CEO Mars Phoenix, XSS-11 ISU, Singularity U, Optech Dr.

Singularity U Management Team Andy Aldrin President ULA, Boeing, TRW Rand Corporation

Technology & Programs Rocket Racing League (COO), Pratt & Whitney, MIT and POET Jim

2 The Executive Team Proven track records of business & technical experience Board Naveen Jain Cofounder, Chairman inome, Infospace, Microsoft X PRIZE, Singularity U Dr. Robert (Bob) Richards Cofounder, CEO Mars Phoenix, XSS-11 ISU, Singularity U, Optech Dr. Barney Pell Cofounder, Vice Chairman NASA Ames/DS-1, MER, Microsoft PowerSet, QuickPay, Singularity U Management Team Andy Aldrin President ULA, Boeing, TRW Rand Corporation Daven Maharaj VP Operations Mars Phoenix, XSS-11 Space Shuttle, Optech Mike D Angelo VP Technology & Programs Rocket Racing League (COO), Pratt & Whitney, MIT and POET Jim Cantrell VP Flight Systems JPL, CNES, SpaceX, Cosmos 1 Space Dynamics Lab Moon Express, Inc.

3 Vibrant MOONHACKERS Our under 30 s compliment our seniors ~3: Moon Express, Inc.

4 MX-1 Flight System Moon Express, Inc.

Moon Express is in Full Scale Development on MX-1 ILOX Telescope ETU Delivered & Flight Unit under contract Mono and BiProp Green Propulsion Development Three thrusters two mono, and one dual mode

5 Moon Express is in Full Scale Development on MX-1 ILOX Telescope ETU Delivered & Flight Unit under contract Mono and BiProp Green Propulsion Development Three thrusters two mono, and one dual mode Composite Overwrap Tank Development Proprietary toroidal winding machine Positive expulsion fuel delivery system Hover Test Beds & Vehicle Development NASA Ames Hover Test Vehicle (HTV) Mighty Eagle Lander Flights using MoonEx code executed in 2013 under MSFC RSAA MTV-1 and MTV-2 ground testing in 2014 Slosh Test Rig Developing detailed Slosh Dynamics Model Slosh tank model and test rig in development Rapid test turnaround Radar Altimeter Development Two airship flight tests Testing on Ames HTV ILDD CLIN 1, CLIN 1.5 successfully delivered Embedded SW and Avionics Development HI-FiHWIL in I&T for SW and HW testing support Flight System Avionics in Implementation and Test Executing GLXP Terrestrial Milestone Prize (TMP) Testing in Moon Express, Inc.

Primary Payload 60 Kg Payload Class MX-1 Vehicle A Single Stage Lander Capable of Reaching the Lunar Surface from GTO Mission Types: Small lander / high delta V space tug In space propulsion module

High thrust/weight bi-prop main engine (1g at start of burn) Precision 6 DOF vernier control 12 pulse mode maneuvering/descent and thrust vector control engines Our MX-1 lander fits in standard 62

6 Primary Payload 60 Kg Payload Class MX-1 Vehicle A Single Stage Lander Capable of Reaching the Lunar Surface from GTO Mission Types: Small lander / high delta V space tug In space propulsion module Orbit rendezvous and proximity ops Ascent vehicle for sample return Wet Mass: 575 kg (spacecraft) Secondary/ESPA capable (~28 h x 55 d) Single Stage Design TLI, cruise, braking, decent and landing High thrust/weight bi-prop main engine (1g at start of burn) Precision 6 DOF vernier control 12 pulse mode maneuvering/descent and thrust vector control engines Our MX-1 lander fits in standard 62 ESPA as secondary payload 50 kg Class GTO to WSB TLI to WSB TLI Direct Payload Mass 50 kg 70 kg 60 kg Payload Average Power 10W 10W 10W Payload Volume >3ft 3 >3ft 3 >3ft 3 Data Rate 100 kbps 100 kbps 100 kbps Flight Duration 3-6 months 3 Months 4 days Surface Mission Duration 2 weeks 2 weeks 2 weeks Example LV Falcon 9 / Secondary GTO Shared Falcon 9, *Dedicated Falcon 9 Shared Falcon 9, *Dedicated Falcon 9 Launch Mass 575 kg 575 kg 575 kg Moon Express, Inc.

7 Secondary Payload Rideshare Issues Major issues are business, not technical Most USG customers hold LV mass margins Pricing theories Marginal cost Cost per kg Market Contract terms Hitchikingis a fine way to get to the beach, but a lousy way to get to work Moon Express, Inc.

8 ME-1 Mission Concept of Operations GTO Insertion Orbit Weak Stability Boundary Transfer Apogee = 1.5 M km Lunar Orbit Insertion Moon s Orbit 185 km x 35,787 km Period = 10.5 Hours TLI Alignment Phasing Time = 2.5 days DV = 33 m/sec Moon at Intercept TLI DV = 755 m/sec Transfer Time = 90 days DV = 610 m/sec Orbit = 250 km x 250 km Inc = 90 deg Landing Timeline Post-Landing Re-location Moon Express, Inc Moon Express, Inc.

9 Moon Express Lunar Missions Moon Express, Inc.

10 Selected for Lunar Catalyst Moon Express, Inc.

11 A New Space Work Horse With Immediate Global Markets Lunar Access Space Debris Space Tug The MX-1 is not just a lunar lander it is a spacecraft workhorse with many markets The iphone of Space Security Operations Satellite Refueling Flexible Upper Stage for Commercial Launchers Cubesat Deployment Planetary Defense Earth Observation & Monitoring Moon Express, Inc.

12 MX-1 Spacecraft Mission Capability Mission Type DV Required (m/sec) MX DV Margin (m/sec)* LEO Satellite Servicing/Testbed N/A 3500 Delivered toleo. Mission dependent. LEO to GTO Delivery Upper Stage Vehicle used as Upper Stage to GTO GTO to GEO Servicing Capability after GEO Insertion Notes GTO to Cislunar Payload Delivery Capability after Cis-Lunar Insertion Cislunar Comm Relay (Farside) Capability after L2 Insertion Cislunar Asteroid Encounter, Data Collection, Imaging, Payload Delivery Capability after DRO Type Insertion Lunor Orbit Payload Delivery Capability after Lunar Orbit Insertion Lunar Orbit Data Collection/Comm Relay Assmues 200 m/sec for orbital Ops. Lunar Orbit Rendezvous and Earth Return Assmues 200 m/sec for orbital Ops. Direct Return. Lunar Surface Payload Delivery Baseline Design for Vehicle Sizing Lunar Surface Sample Return Assumes MX-1 Liftoff to Direct Return. 15 kg SRC. NEO Asteroid Encounter, Data Collection, Imaging, Payload Delivery Capability after NEO Orbit Insertion Mars Orbit Payload Delivery Capability after Capture Mars Orbit Insertion Mars Orbit Data Collection/Comm Relay Capability after Capture Low Mars Orbit Phobos/Deimos Encounter, Data Collection, Imaging, Payload Delivery Capability after Phobos Encounter/Opertaions *All margins assume baseline payload values: MX-1 = 50 kg, MX-2 = 400 kg Moon Express, Inc.

Moon Express is Pioneering the Lunar Frontier Moon express is on track for a

customer, and executing a lunar sample return by 2020 Moon Express owns the

through private equity Combining Silicon Valley entrepreneurship with aerospace

for MX-1 maiden flight Enabling low cost access to the lunar surface High

delivery of 400kg payloads and sample return Flexible launch options We re going

13 Moon Express is Pioneering the Lunar Frontier Moon express is on track for a 2015 MX-1 maiden voyage, conducting a South Pole mission for a commercial customer, and executing a lunar sample return by 2020 Moon Express owns the development cost and risk of our missions and spacecraft Independently financed through private equity Combining Silicon Valley entrepreneurship with aerospace best practices Expanding team of 30 experienced engineers Full payload manifest for MX-1 maiden flight Enabling low cost access to the lunar surface High performance, mass efficient design Scalable architecture with a clear pathway to delivery of 400kg payloads and sample return Flexible launch options We re going to the Moon and ready to partner with NASA for cost effective collaboration Moon Express, Inc.

Next Steps in Human Exploration: Cislunar Systems and Architectures

Next Steps in Human Exploration: Cislunar Systems and Architectures Matthew Duggan FISO Telecon August 9, 2017 2017 The Boeing Company Copyright 2010 Boeing. All rights reserved. Boeing Proprietary Distribution