OPPORTUNITYCONFERENCE

INNOVATION &

ADVANCING AEROSPACE AND DEFENSENovember 7-8, 2018 | Aurora, Colorado

Future Technology Needs:Entry, Descent and Landing Systems

Michelle M. MunkNASA-Space Technology Mission Directorate

EDL Systems Capability Lead

NASA’s Exploration Campaign

PresenterPresentation NotesLanding Precisely is one of the key capabilities that feeds forward from Lunar exploration to Mars exploration, and it applies at all scales of landersThe ability to land precisely enables:Accessing high-value science and in-situ resources quickly and potentially with more simple systems (e.g., landing on the rim of a crater, or right on top of an ice deposit)Aggregating equipment with minimal damage to other assets, shorter surface operational time and lower complexity (e.g., plugging in power sources, sharing unloading equipment, connecting pressurized modules, etc.)

Flight SystemGround Tests

Flight Tests – EarthFlight Tests – Mars

ManufacturingImplementation

HumanMars EDL

Mars EDL is a Long-Term ChallengeLeveraging Lunar Missions in the Exploration Campaign

Viking 1 & 2Pathfinder

MER(Opportunity

& Spirit)Phoenix

MSL(Curiosity)and MEDLI

EDL Architecture SelectionGround Tests

Flight Tests – EarthFlight Tests – MarsSystems Analyses

DDT&E Assessments

Performance & QualificationGround Tests

Flight Tests – EarthSub-scale Flight Tests – MarsImplementation Development

Mars Landed Mass: 1 t 3-10 t 15-30 tMars Precision: 10-25 km 5-10 km

Precision Landing Feeds Forward to Mars• Landing precision is improving with each

Mars mission• To get to the current state of the art,

system changes have been made, along the way:

• MSL had the first active hypersonic guidance• In addition, Mars 2020 employs a range trigger

on the parachute, and uses Terrain Relative Navigation (camera images compared to a stored map)

• Human missions will need integrated guidance, improved velocimetry, and hazard detection/avoidance

5

Human50 m radius

Mars

How Will We Land 20t on Mars?

Rigid aeroshells limited to low altitude

sites (blue)

Inflatables allow access to southern

highlands6

MSL3300 kg 4.5m

HEART3500 kg 8.3m

Name Shape Vehicle DimensionsLaunchMass

Capsule10 m (h) x 10 m (w) 68t

Mid L/D22m (l) x

7.3m (h) x 8.8m (w)

66t

ADEPT4.3m (h) x

18m diameter 60t

HIAD4.3m (h) x

16m diameter 57t

ADEPT = Adaptable Deployable Entry & Placement TechnologyHIAD = Hypersonic Inflatable Aerodynamic DeceleratorMid-L/D = Has a lift-to-drag ratio (L/D) of about 0.55

Human Mars EDL Concepts of OperationsNotional Only, 20t Payload

DeorbitAft RCS Thrusters

Entry AOA= 55 degVelocity = 4.7 km/sFPA = -10.8 deg

Powered Descent Initiation Mach = 1.98, Alt = 3.2 kmPitch up to 90 deg AOA

ApproachT/W = 1.25 Earth g8x125kN engines80% throttle10 deg outward cant

Touchdown

Ground Operations

7

Entry AOA= -10 degVelocity = 4.7 km/sFPA = 10.6 deg

Powered Descent InitiationMach = 3.0, Alt = 8.3 kmPitch to 0 deg AOA

Approach8x100kN engines80% throttle

Deorbit & Deploy

Touchdown HIAD Retract Surface Ops

Hypersonic Inflatable Aerodynamic DeceleratorSupersonic Retropropulsion

Precision Landing

Mid-L/D VehicleSupersonic Retropropulsion

Precision Landing

Human Mars Lander Challenges• 20x more payload to the surface than Mars Science Laboratory• 200x improvement in precision landing (first: Terrain Relative Navigation on Mars 2020)• Dynamic atmosphere; poorly characterized• New engines; performing Supersonic RetroPropulsion (LOx/Methane, 100 kN, 90% throttle)• Terrain hazard detection - improving, but not yet implemented in flight• Surface plume interaction - debris ejecta could damage vehicles

8Image Credits: NASA

1 km

700 m

PresenterPresentation NotesEDL is hard enough, we want to be careful about adding additional challenges. We need to consider the cost vs risk carefully.

Summary of EDL Technology Needs

• Large-scale deployable aerodynamic decelerators for slowing down large, massive Mars payloads (materials challenges, volumetric constraints, controllability)

• Supersonic retropropulsion (parachutes won’t work!) with deep throttling capability• Precision Landing capability (integrated GN&C) for Lunar and Mars applications• Plume-Surface Interaction prediction capability for Lunar and Mars applications• For low-cost science or commercial missions, methods of achieving precise

delivery or Earth return • EDL system instrumentation, to gather flight data with which to validate models

(EDL is only qualified end-to-end via computer models, before it’s flown)

Backup

What We Need to Land:Cargo Elements for Long Duration Human Mars Surface Stay

Lander 2 Lander 3 Lander 4Lander 1

10 m diameter SLS fairing | 300 day stay | Crew of 4 | Four 20 t payloads

• Surface Power Units• Unpressurized Rovers• Cargo Off-loading• Logistics Module• Science Payloads

• Mars Ascent Vehicle • Atmosphere ISRU• Crew Access Tunnel

• Pressurized Rover• Logistics module

– Crew consumables– Fixed system spares– Mobile system spares – EVA spares

• Surface Mobility

• Habitation• Crew

Slide Number 1Future Technology Needs:�Entry, Descent and Landing SystemsNASA’s Exploration CampaignMars EDL is a Long-Term Challenge�Leveraging Lunar Missions in the Exploration CampaignPrecision Landing Feeds Forward to MarsHow Will We Land 20t on Mars?Human Mars EDL Concepts of Operations�Notional Only, 20t PayloadHuman Mars Lander ChallengesSummary of EDL Technology NeedsBackupWhat We Need to Land:�Cargo Elements for Long Duration Human Mars Surface Stay