Deep Space Transport (DST) and Mars Mission Architecture

Home , Deep Space Transport, Transit (astronomy)

John Connolly NASA Mars Study Capability Team

October 17 2017

1 Human Space Exploration Phases From ISS to the Surface of Mars

Ends with testing, research and Today demos complete* Asteroid Redirect Crewed Phase 0: Exploration Systems Mission Marks Move from Testing on ISS Phase 1 to Phase 2

Phase 1: Cislunar Flight Ends with one year Testing of Exploration crewed Mars-class Systems shakedown cruise

Phase 2: Cislunar Validation of Exploration Capability

Phase 3: Crewed Missions Beyond Earth-Moon System

Planning for the details and specific Phase 4a: Development objectives will be needed in ~2020 and robotic preparatory missions * There are several other considerations for ISS end-of-life Phase 4b: Mars Mid-2020s 2030 Human Landing Missions 2 Deep Space Gateway (DSG)

Phase 2: Deep Space Transport Orion

PHASE 2 Deep Space Gateway Phase 2 Mission Elements

Deep Space Transport Space Launch Deep Space System Gateway

Deliver payloads to cislunar space

Earth Moon

Orion Cislunar Space is used for Deep Space Gateway Deployment and Deep Space Transport Checkout

Transfer crew and cargo from Earth to cis Lunar space and back to Earth

Pre-decisional/Not for distribution/NASA Internal use only Deep Space Transport Functionality

• Emphasis on supporting shakedown cruise by 2029 • Shakedown cruise to be performed in lunar vicinity • Utilizes deep space interfaces and common design standards

• Example Assumptions • Deep Space Transport provides habitation and transportation needs for transporting crew into deep space including supporting human Mars-class missions • The Transport system life will be designed for: • Reused for 3 Mars-class missions with resupply and minimal maintenance • Crew of 4 for 1,000 day-class missions in deep space • Launched on one SLS 1B cargo vehicle - resupply and minimal outfitting to be performed in cislunar space

5 DST Driving Assumptions

Assumption Crew Number 4 Crew Vehicle Lifetime/Dormancy 15 year lifetime with up to 3 years dormant operation Dimensions Constraints 7.2 m diameter shell to meet 8.4 m payload shroud constraint. 0.95 eccentricity end domes to maximize useful volume Habitable Volume >25 m3/person Docking mechanisms 3 passive, 1 active ISS compliant docking mechanisms for cislunar aggregation Extravehicular Activity Contingency EVA only using modified Launch, Entry, and Abort (LEA) suits and an inflatable airlock

6 More complete set of assumptions in paper Deep Space Transport EVA Assumptions

7 Interior Layout Features

Large logistics storage with nested crew quarters for radiation protection

Central stowage Medical/Research Galley/Wardroom Research/Exercise Hygiene area 8 Image credit: NASA PHASE 3 First Human Mission to Mars Sphere of Influence

Deep Space Transport (DST) Mission to Mars Sphere of Influence (Phase 3)

• Emphasis on first human mission to Mars’ sphere of influence • First long duration flight with self sustained systems • Autonomous mission with extended communication delay • First crewed mission involving limited abort opportunities

• Example Assumptions • 8.4 m Cargo Fairing for SLS launches in Phase 3 • Crew of 4 for Mars class (1000+ day) mission independent of Earth • Orion used for crew delivery and return to/from cislunar space • Re-usable DST/Habitat and Propulsion Stage • Hybrid (SEP/Chemical) In-Space Propulsion System • Gateway used for aggregation and re-fueling of DST

10 Example Phase 3 Mission Elements

Space Launch System Deep Space Deliver payloads to Transport cislunar space

Deep Space Gateway

Earth Moon Mars

Orion

Transfer crew and cargo from Earth to cislunar space and back to Earth Crew Operations in Martian Vicinity Communications System

Earth-to-Mars communication Mars Orbital Mission Example Operational Concept

# Crew Phase Critical Event System Return to Earth Options

4 Lunar Gravity Assist #1 DST/Orion DST powered return to HEO / Orion return

5 Lunar Gravity Assist #2 DST DST powered return to HEO

5 Earth-Mars Transit (early phase) DST powered return to HEO (available for DST limited time post departure - TBD)

6 Earth-Mars Transit Thrusting SEP None – continue to Mars

7 Mars Orbit Insertion Chem Backflip (TBD) – continue mission

8 Mars orbit reorientation SEP None – continue mission 9 Trans-Earth Injection Chem None – continue mission 7 9 High-Mars Orbit 10 Mars-Earth Transit Thrusting SEP None – continue mission 8 11 Lunar Gravity Assist #3 DST None – continue mission

11 Lunar Gravity Assist #4 DST None – continue mission 438 days

12 Orion Launch SLS/Orion HEO Loiter

12 Earth Return via Orion Orion HEO Loiter 6 306 days 291 days 10

13 2 Deep Space Gateway 5 11 4 High-Earth Orbit Checkout before 1 3 each mission Orion return 12 12 (no crew)

Launch Loiter High Thrust Chemical Low Thrust Electric

12 Mars Orbital Mission Overview – 2033 Mission Example

Deep Space Transport ~ 300 kW Electric Propulsion (EP) power 3. Mars Arrival ~ 470 kW solar array power at start of the mission 1/2034 6. Earth Arrival Chemical ∆V = ~0.3 km/s ~ 20 kW power to the spacecraft and payload 1/2036 ∆V = 0 km/s ~ 24 t EP propellant and ~ 16 t chemical propellant 1. Earth Departure ~ 48 t Payload 3/2033 ∆V = 0 km/s ~ 21.9 t habitat with 26.5 t logistics and spares to support 4 crew D

2. Outbound 306 days SEP ∆V = ~3 km/s

Mission Concept of Operations 5. Inbound 1. After crew rendezvous with the Transport in high elliptical Earth 291 days SEP ∆V = ~3 km/s orbit it catches lunar gravity assists for Earth Departure 4. Mars Departure 3/2035 – Most opportunities don’t require a chemical departure burn Chemical ∆V = ~0.3 km/s but some harder outbound opportunities do 2. Transport uses EP in heliocentric space to complete transit to Mars 3. Transport captures into Mars orbit with chemical propulsion Mars SOI 4. Crew performs remote observations of Mars vicinity for 438 days (88 orbits) 5. Transport departs Mars via a chemical propulsion departure burn 6. Transport uses EP to return to Earth 7. Lunar gravity assists to recapture into Earth sphere of influence.

13 PHASE 4 Mars Surface Missions Mars Surface Mission Feasibility (Phase 4)

• Emphasis on establishing Mars surface field station • First human landing on Mars’ surface • First three missions revisit a common landing site

• Example Assumptions • Re-use of Deep Space Transport for crew transit to Mars • 4 additional, reusable Hybrid SEP In-Space Propulsion stages support Mars cargo delivery • 10 m cargo fairing for SLS Launches in Phase 4 • Missions to Mars’ surface include the following: • Common EDL hardware with precision landing • Modular habitation strategy • ISRU used for propellant (oxidizer) production • Fission Surface Power • 100 km-class Mobility (Exploration Zone)

15 Mars Surface Mission Example Operational Concept

# Crew Phase Critical Event System Return to Earth Options

4 Lunar Gravity Assist #1 DST/Orion DST powered return to HEO / Orion return

5 Lunar Gravity Assist #2 DST DST powered return to HEO 9 5 Earth-Mars Transit (early phase) DST powered return to HEO (available for DST limited time post departure - TBD)

6 Earth-Mars Transit Thrusting SEP None – continue to Mars

7 Mars Orbit Insertion Chem Backflip (TBD) – continue mission 8 Rendezvous & Mars Descent Lander Remain in Mars orbit for return 8 9 Mars Ascent Ascent None – must ascend to orbit 7 11 High-Mars Orbit 10 Mars orbit reorientation SEP None – continue mission 10 11 Trans-Earth Injection Chem None – continue mission

12 Mars-Earth Transit Thrusting SEP None – continue mission 300 days

13 Lunar Gravity Assist #3 DST None – continue mission

13 Lunar Gravity Assist #4 DST None – continue mission 6 390 days 370 days 12

14 Orion Launch SLS/Orion HEO Loiter

14 Earth Return via Orion Orion HEO Loiter 15 2 Deep Space Gateway 5 13 4 High-Earth Orbit Checkout before 1 3 each mission Orion return 14 14 (no crew)

Launch Loiter High Thrust Chemical Low Thrust Electric

16 Example Phase 4 Mission Elements

Space Launch Entry-Descent System Lander Deep Space Deliver payloads to cislunar space Transport, Hybrid SEP Cargo Transport Deep Space Gateway Transport 100-200t aggregated Land 20-30 t payloads payloads and crew between Earth on Mars and Mars

Mars Earth Moon

Mars Ascent Communications Vehicle Orion System Transfer crew and cargo from the Mars surface to Mars orbit Transfer crew and cargo from Earth to cislunar space and back to Earth Crew Operations in Earth-to-Mars, Mars surface-to-Mars orbit, and Martian Vicinity Mars surface-to-surface communication

Surface Habitat Logistics Carrier and Science Lab Surface Mobility Surface Utilities

Sustain 4 crew Power, In Situ Planetary Space for up to 500 Deliver equipment Resource days per Suits and robotic or and consumables Utilization Expedition pressurized rovers Human Mars Architecture Decisions Related To EVA

• End State – “Lewis and Clark” – Field Station (revisit) – Towards permanent habitation • Mission Duration – In-Space – Surface • Mars Descent and Ascent – Duration – Scale/capabilities of descent and ascent vehicles • Transfer Among Surface Elements – Pressurized vs unpressurized – Dust control • Spacesuit Commonalty – Launch/In-space EVA/Mars EDL/Mars Surface/Mars Ascent/Earth Entry – Volumetric constraints • ISRU – Availability of locally produced consumables • Maintenance and Spares

18 19 Human Mars Mission Design Decisions

Transportation Mission Architecture / End State Earth-to-Orbit The current big picture design Launch Propellant Element Earth-to-Orbit Launch Primary Program Level of Human Earth Based TransportationCrew Launch Vehicle Mission Class Cost Emphasis Reusability and/or Logistics Launch Flights per Vehicle Focus Activity Mission Support Vehicle Shroud Size / 37 Launch Vehicle Vehicle Expedition Rate Cis-Earth Infrastructure SLS 2B FairingDeep Space choices offers up 5.3 x 10

Supporting Opposition Class - 8.4 m In-Space No. of Flags & Footprints / Long-Term Robotic / Space Continual Low Cost / In-Space Earth Return Cis-Lunar Mars Orbit Chemical In-Space Initial OrbitShort Stay (1-60 Orion None SLS/Orion SLS SLS Diameter, Habitat 2 Crew to 1 per year Pathway Lewis & Clark StagingTeleroboticInfrastructure Control Gradual BuildRefueling-Up Mode Propulsion Propulsion Propellant Habitation possible combinations sols) Short LengthDuration Orbit Mass Transportation Research Base / Conjunction Class - 8.4 m Moderate High Cost / In-Space Antarctic Field Long Stay (300+ Expeditions Take Orion All Chemical / InternationalAll Chemical / International InternationalNTO / Monolithic Diameter, 4 2 per yearDSG > 2-year Flyby > DRO Cis-Lunar Hab < 50 mt Intervention Gradual BuildYes -UpDirect EntryHabitation Deep Space 600 days 2 Earth Return Analog sols) to Mars Cryogenic Cryogenic Hydrazine Transit HabLong Length Long-Stay Surface Near Mars Orbit Mars Orbit Mars Ascent Vehicle Ascent Vehicle 10 m MAV Earth Earth Descent to Primary Activity: All-Up vs. Split Mars Parking No Daily Low Cost / Fast In-Space Mars Orbit Mars Pre- Earth Entry Rectilinear No Cis-Lunar HumanDestination-Tended Leave Orion Insertion - Insertion Earth Orbit - All Chemical / CommercialDescent All Chemical / CommercialPropellant Commercial-LOX / Propellant Modular Diameter, - Payload Capture 6 3 per yearReturn DSG > 2-year Flyby > Earth's Science & Research Mission 50 - 100 mtInterventionOrbit BuildNo-Up TransportationOperations 1000 days 3 Deployment Vehicle Halo Orbit Infrastructure in Orbit Human HealthCargo CrewCapture StorablePropellantStorableFrom EarthMethaneFrom ISRUTransit HabShort LengthUp Orbit SurfaceScheme Short-Stay SurfaceSurface 10 m Primary Activity: (NRHO) Continuous High Cost / Fast Minimal EDL and Ascent Combination Combination Combination Diameter, Direct Entry8 6 per year Resource Utilization Presence Build-Up Lunar Orbit LOX / Landed Mass DSG > 3-year Orbital > LEO 100 - 200 mt NTR NTR CombinationLong LengthLander 1200 days(with 4Direct Mars Orbit 1-sol Propulsive PropulsiveCaptureDesign Minimal First Surface Storables CryogenicCrew Surface HydrogenNo. of Crew to LOX Only 0 kg per Lander Entry LongConsumables-Stay Surface DirectLanding Orion Landing Radiation Countermeasures Payload SizeTransit hab Entry Lander Altitude Primary Activity: Human Considerations Mission Date Stay Time Surface Crewmember Type Location Accuracy Surface Systems 12 m Diameter(Metric Tons)flyby)10 + DSG > 3-year Orbital > Human Expansion HEO Settlements> 200 mt SEP OCT (Metric Tons)Surface5 Rendezvous / Propulsive Short-Stay SurfaceSeparate Phobos 5-sol Aerobrake Aerobrake Cryogenic Hypergol LOX Methane 250 kg DRO None Commercial Infrastructure Transfer Capture System Human Hybrid SEP / Hybrid SEP / Short Stay 18 mt lander: Passive Zero-G w/Exercisefor Permanent Psychology 2035 Excursion 2 18 6 Blunt Body Near Equator - 6 km MOLA < 100 m Colonization Vehicle Chem Chem (1-60 sols) 6.0 - 36.0 mt Landing Habitation Habitat Life Planetary Radius/ Length of Planetary Laboratory Cargo Surface Mars' Surface 500 km Circular None ISRUNone RefurbishmenPower Other LOX/Hydrogen > 250 kg NHRO Landers ECLSS TrashCombinationRobotics Zone Hybrid SEP / TypeHybrid SEP / Support Outpost Exploration Surface Stay Sciences Sciences Handling Communication t Long Stay 20 mt lander: > 6 Surveys Active Artificial Short Arm MedicalHypergols 2037Hypergols Zone3 20 Mid L/D Polar 0 km MOLA 100 m - 1 km (300+ sols) 6.7 - 40.0 mt Earth Return Combination Areosynchronous Other HEO Split SEP / Split SEP / Different Teleoperation of Propellant 22 mt lander: Low Latency Crane/ Lunar First Artificial Long ArmNone DustSolarChem Monolithic2039 ChemOpen for Each < 10 km4 7 sols22 Instrument / NoneInflatable OpenMid-LatitudeContainers+ 2 km MOLA Orbital> 1 km Line of Sight 7.3 - 44.0 mt Telerobotics Hoist Q-Drive Q-Drive Expedition Networks Areosynchronous SEP / Chem / SEP / Chem / Demonstration Single Recon Geology / 25 mt lander: Basic Analysis 50 - 75%Northern NuclearAerobrakeModular2041 +AerobrakeClosed 10 - 100 km5 14 sols25 Deployable Recycle Autonomous Robotic Ramp Relay Satellite Mars Flyby Only Outpost Geophysiology8.3 - 50.0 mt / No Lab ClosedHemisphere NEP NEP Backflip Bimodal NTR Bimodal NTR Moderate Atmospheric Multiple 27 mt lander: 75 - 90%Southern Crew Grand Tour RTG Inflatable > 100 km6 30 sols27 Field Work Geochemical All Propulsive Combination ATHLETE Oxygen Outposts 9.0 - 54.0 mt ClosedHemisphere Partnered Fast + Life Science Water from 30 mt lander: Drilling / Full-Scale Life > 90%Different for Combination Rigid > 6 90 sols30 Other Regolith Geophysical Tests10.0 - 60.0 mt Science Closedeach mission

Local 40 mt lander: 40 Water from from Features 300 - 500 13.3 - 80.0 mt Subsurface Ice and sols Resources Fabrication / 500 - 1000 Manufacturing sols > 1000 sols, Combination overlapping crews Export