International Space Exploration Coordination Group Human Exploration of the Lunar Surface International Architecture Working Group Future In-Space Operations Telecon September 20, 2017
Icon indicates first use opportunity. Commercial/Institutional launchers not shown. Human Exploration in Cislunar Space The Mission Scenario chart from GER2 notionally connects the Gateway (labeled as the Evolvable Deep Space Habitat) and the lunar surface scenarios together. Thus the IAWG sought to address the question: How would the Gateway be used to support human lunar surface missions? Potential functions for the Gateway in a lunar surface scenario include: 1 Storage and refueling of a reusable ascent module 2 Safe haven for crew aborting from the surface 3 Communications relay to Earth from the lunar far side 4 Teleoperations of robotic systems (on the far side) 5 Access to medical and exercise equipment for reconditioning. 6 Act as a hub for refueling spacecraft consumables. ISECG&Mission&Scenario& Low-Earth Orbit International Space Station Beyond Low-Earth Orbit Test Missions Rosetta Hayabusa-2 OSIRIS-REx (Sample Return) (Sample Return) Near-Earth Objects Lunar Vicinity LADEE Luna 25 Luna 26 Luna 27 RESOLVE SELENE-2 Moon MAVEN ISRO Mars Orbiter Mission Mars Multi-Destination Transportation Capabilities (Planned and Conceptual) Chandrayaan-2 ExoMars 2016 InSight Orion & SLS ExoMars 2018 Russian Piloted System 2020 2030 Asteroid Redirection Advanced Electric Propulsion Luna 28/29 (Sample Return) Apophis Extended Duration Crew Missions Mars JAXA 2020 Mars Precursor Evolvable Deep Space Habitat Commercial or Government-Owned Platforms SELENE-3 Explore Near Earth Asteroid Human-Assisted Sample Return Human-Assisted Sample Return Orion & SLS (Upgrade) Initial Cargo Delivery Small Cargo Lander Human Surface Mobility Crewed Lunar Lander Staging Post for Crew to Lunar Surface Potential Commercial Opportunities Humans to Lunar Surface Potential Commercial Opportunities Mars Sample Return Mission Opportunities Human Scale EDL Test Mission Opportunities Orion & SLS (Upgrade) Robotic Mission Human Mission Cargo Mission Sustainable Human Missions to the Mars System 2/16
ISECG Principles The GER has identified 6 exploration principles that are helpful metrics for devising a comprehensive architecture: 3/16
Architecture Driven by ISECG Principles The combined principles could be summarized as an endeavor to maximize partnership opportunities by prioritizing modular systems while at the same time minimizing cost and complexity, ultimately favoring minimum mass solutions. 1 GER derived strategic principles! A ordability, Exploration Value, International Partnerships, Capability Evolution, Human-Robotic Partnership 2 GER derived goals and objectives! 5 missions, 4 crew and 28+ days on surface 3 Capability based constraints as framed by international participants.! Currently featuring ESA, CSA, JAXA and NASA contributions 4/16
Cislunar Orbit Options While,the preferred orbit from a lander standpoint would be LLO, NASA s Orion doesn t have enough fuel to get in and out. Reduced round-trip times on the order of 85% to 95% to the surface from the NRHO compared to DRO or larger L2 Halos directly correlates to decrease in the mass of supplies, air and associated systems that in turn result in a multiplied increase in lander propellant mass. 5/16
Final Trade Space Acompletelymobilebasedsystemwasselectedasthepreferredimplementation for the crewed stays. Two pressurized rovers provide full habitation for 2 crew members each for 42 days (2 lunar days + 1 lunar night). Amobilesystem maximizes landing site diversity while simultaenously minimizing surface infrastructure. 6/16
Design Reference Mission Initial 3Launchscenario. Subsequent missions require 1.5 launches. 7/16
Two Stage Lander Reusable Ascent Module Main function: deliver 4 crew safely to the lunar surface and back. 3-4 day lifetime capability required for abort modes Reduced pressurized volume to 10 m 3 to save mass Pump-fed storable fuel-based engines LO 2 /CH 4 Descent Module LO 2 /CH 4 was selected for the descent module for ISRU potential and increased performance Key features of descent module given below: Item Descent Module Main Propellants LO 2 /CH 4 # Engines 3 Engine Thrust >80 kn Engine I sp 370 s RCS 40 x 220 N Power Solar Panels 8/16
Reusable Surface Rovers Small Pressurized Rovers 2reusableroverscarry2crew members each Yearly missions will require small cargo resupply Volumetric challenge to fit 2 rovers atop a descent module in launch vehicle shroud The rover has 4 main systems: 1 The rover platform/chassis 2 The radioisotope power/thermal source 3 The airlock 4 The pressurized module Unique hybrid power system includes: 1 Partially deployable solar panels 2 Multiple radioisotope power systems 3 Rechargeable batteries or regenerative fuel cells. Notional Rover Design Notional Launch Configuration 9/16
Element Co-Development Envisioned co-development approach Aprogrammaticanalysiswas performed on how to realize a lunar surface architecture. The time scale on the top of the figure indicates years to Human Lunar Return. Relationship between demonstrator and human elements The study found that: 1 Asub-scalerobotic demonstrator version of the human lunar lander is the most a ordable solution 2 System components would be implemented based on the partnership roles in the human architecture 3 Demonstrator mission should be between 4 and 6 years before human lunar return 4 Ademonstratordoesnot significantly delay human lunar return. 10 / 16
Key Technology Challenges Radioisotope-Solar Hybrid Power (Lunar Night survival) Life support and EVA for extended lunar stay (LSS atmosphere choices, dust mitigation, radiation, exercise requirements) Zero-boil-o LO 2 /CH 4 propulsion 11 / 16
Landing Sites to Connect 5 Consecutive Missions Notional Sites in SPAB Coordinates of Notional Sites # Site Lon. Lat. 1 Malapert Massif 0-85 2 Shackleton Plateau 126-89 3 Schrödinger Basin 139-75 4 Antoniadi 172-70 5 SPAB Interior 160-60 Detailed Example SPAB Landing Site Theme Geological Features Water or Ice Observation Objective Geological Exploration as wide area of SPAB Lunar Water/Ice or Volatile component exploration for ISRU Moonquake observation. Astronomical Observatory on lunar surface. The five example SPAB sites are useful for addressing the feasibility of the architecture concept driving power, thermal, and communication subsystem designs, as well as the assumptions on the terrain environment for surface landing and mobility. 12 / 16
Crew Concept of Operations 13 / 16
Sub-Scale Demonstrator Mission Aconceptforthedemonstratormissionscenariohasbeenadvancedto phase-0 level by the participating agencies CSA, ESA, and JAXA Once landed, surface rover is envisioned to collect up to 15 kg of samples from previously unexplored regions of the Moon. The first operational concept will allow significant advances in preparing for human missions to Mars and sustained exploration of the Moon While reliance on ISRU has been excluded for the DRM, it is nevertheless an objective of the campaign to deploy a to-be-defined ISRU pilot plant 14 / 16
Gateway Enabled Human Surface Summary Lunar surface concept is logical combination of: Planned components (SLS and Orion) + Conceptual Components (Human Lander and Pressurized Rovers) Key is a ordability: minimizing heavy lift launches, maximize reusability and minimize new developments Approval of the demonstrator mission for development is vital to make human lander project a ordable. 15 / 16
http://www.globalspaceexploration.org 16 / 16