Jennifer Trosper

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Session 7 Human Precursor Missions Thoughts on
Mars Human Precursor Discussion

• Jennifer Trosper
• NASA Hq. ESMD
• Frank Jordan
• Manager Advanced StudiesMars Program Office

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Advent of Human Precursor Activities
In addition to the approval of the next decade
science-driven robotic Mars Program, the new
President/national initiative in 2004 resulted in
an augmented budget to allow the Mars program to
contribute to the preparation for human
exploration Human precursor activities can
bridge the gap between the capabilities
developed by the science missions and some
capabilities/measurements needed for the
beginning of the human era Here we
cover New requirements on robotic missions as
human precursors Illustrative examples of
possible robotic mission advances in -
Landing accuracy and - Heavier mass to the
surface.
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Objectives for Mars Human Precursors

• Perform measurements, technology demonstrations,
  and infrastructure emplacement in order to
• Reduce cost
• Reduce risk
• Enhance overall mission success
• of future human exploration missions

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Development of Mars Human Precursor Requirements

• Based on the previously discussed objectives,
  ESMD tasked the Mars Program Office to assist in
  the definition of the required mission set.
• The task was led by Frank Jordan with
  sub-group leadership by Dave Beaty (Measurement
  sub-group chair) and Noel Hinners (Technology
  Infrastructure sub-group chair).
• MEPAG members supported this task as well as
  additional experts from NASA centers, academia,
  and industry.
• 90 scientists and 25 engineers participated
• Two workshops, separated by two months of
  sub-group telecons over two months
• The task was kicked-off at the late June MEPAG
  meeting and will complete 1/15/2005.

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Guidelines for the Task
Aim for human mission to Mars in the centurys
4th decade, 2030 First dedicated precursor
opportunity -- 2011 Consider only activities
that should be performed at Mars (additional
requirements for earth, space-station or Lunar
based activities will be included in a later
task) Science robotic missions will continue
synergy between science mission and robotic
precursors will be sought Infrastructure
associated with science missions, e.g., 2009
Telecom Orbiter, is available Perform
qualitative analysis of cost, risk, and
performance effects based on expert opinion.
Inadequate data on human missions to Mars exists
for a quantitative analysis. Consider
requirements with major architectural impacts
(i.e. system of systems) higher priority than
those without.
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Summary of FindingsHigh-Priority, Early-Action
Recommendations

• Mars Environment Measurements
• Dust properties
• Effects on humans and mechanisms
• Traction and cohesion
• Biohazards in atmosphere, on surface, subsurface
• Atmosphere characterization
• Electrical effects
• Dust storms
• Find and characterize accessible water

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Summary of FindingsHigh-Priority Recommendations

• Technology and Infrastructure
• Early Phase (Launches 2011, 2013, 2016)
• Atmosphere/regolith ISRU demos
• Instrument (pressure, temp, etc.) all
  atmospheric flight missions
• Aerocapture (70 cone) demo

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Summary of Findings High-Priority
Recommendations (contd.)
Technology and Infrastructure

• Mid Phase
• (Launches 2018, 2020, 2022)
• Subscale demonstration of a human-scalable
  landing system
• Pinpoint Landing
• Subscale demonstration of a human-scalable ISRU
  surface system
• Radiation shielding properties of regolith

• Late Phase
• (Launches 2024, 2026, 2028)
• Detailed surface reconnaissance of a selected
  first human landing site
• Full-scale dress rehearsal of the human
  mission key systems
• Landing
• ISRU
• Ascent
• Infrastructure Emplacement e.g
• Telecom orbiters
• Landed infrastructure systems

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Some Observations

• Science Program, as it is, is a strong
  contributor to human exploration needs
• Current Decades Program
• Contribute to search and characterization of
  accessible water
• Odyssey Neutron Spectrometer
• MARSIS Radar (MEX)
• SHARAD Radar (MRO)
• Phoenix Ground Truth
• Neutron Spectrometer (MSL)
• Next Decades Program
• Can host some key measurements and demonstrations
• Biohazards MSR may be the only credible approach
• Dust MSR, AFL
• Pinpoint Landing MSL, MSR
• Aerocapture ST-9, MSR

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Some Observations (contd.)

• Some Human Precursor measurement needs contribute
  fundamentally to expanded science knowledge
• Dust
• Biohazards
• Water characterization
• Some Human Precursor engineering demonstration
  needs are likely distinct from the science
  program
• ISRU and accessible water characterization
• Human-scalable Landing System
• Program synergy is possible and preferable, but
  there needs to be some dedicated precursor
  missions

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An Integrated Mars Science Program with MHP
Activities
2007 2009 2011 2013 2016 2018
MSL
Scout
AFL
MSR
Scout
Phoenix
MTO
MTO 2
Mars Science Missions
ISRU
MET Stations
Environmental Measurements
Pinpoint Landing
Human Landing System
Instrumented EDL
Auto Rendezvous
Aerocapture
MHP Development Program
Testbed
Testbed
Testbed
MHP Flight Testbed Missions
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Results of Recent System Studies
1) How do we increase the accuracy of landing on
the surface of Mars? Goal Increase
accuracy by 2 orders of magnitude to 100
m (Work by A. Wolf, L. Miller, etc.
JPL) 2) How do we increase the landed mass on the
surface of Mars? Goal Double todays
capability to 4 metric tons (Work by J.
Cruz, R. Powell LaRC)
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Pinpoint Landing2011 Tech Demo Reference Concept

• 2011 mission envisioned as an initial test
  flight under benign conditions (daylight
  landing, moderate winds,..)
• Systems study assessed technological approach
  for this demo mission
• Optical Nav on approach
• Achieve 2 km knowledge at entry 130 km alt.
• Hypersonic entry guidance
• Bank-angle control with IMU
• Achieve 2 km control accuracy at 10 km alt.
• Parachute without guidance
• Vulnerable to wind drift up to 4 km 5 km
  alt.
• Optimal descent imaging
• Recovers knowledge to 100 m 5 km alt.
• Powered descent guidance
• Achieves landing to 100 m control accuracy

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Feed-Forward for Pinpoint Landing
Surface Images
MGS
ODY
MRO
New Tech Approach Camera
MRO Demo
2-way s/c-to- s/c Doppler
Phoenix Demo
Bank-Angle Aeroguidance
Phoenix
MSL
Descent Imaging
MSL Demo
Continuing use in program
End-to-End Pinpoint Landing
Testbed Demo
MSR
System Studies
Technology
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Increase Landed Mass
Future missions, both manned and robotic will
require delivery of increased payload mass to the
surface of Mars The objective of this task is
to identify high pay-off technologies that will
open the way to achieving this goal with an eye
towards human precursor missions Phase 1
(2004) robotic science mission (x 2 mass increase
factor) Phase 2 (2005, 2006) human precursor
(scalability to x 25)
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New EDL Concepts Technologies Costs (FY04 s)
2X Current Viking-Heritage Approach Improved
Thermal Protection System Development
Introduce Large Subsonic Parachute Qualific
ation Technology Investment 10 - 20M
Inflatable Aeroshell Inflatable Aeroshell
Development and Qualification for hypersonic
phase Introduce Large Subsonic Parachute
Qualification Technology Investment 80 -
90M
MID L/D Entry Vehicle Mid L/D Entry Vehicle
Develop- ment and Qualification Inflatable
Supersonic Decelerator (Hypercone) Development
and Qualification Introduce large Subsonic
Parachute Qualification Improved Thermal
Protection System Development Technology
Investment 160 - 180M
Aerocapture and Entry from Orbit Aerocapture
Demo Introduce large Subsonic Parachute
Qualification Mach 3 Supersonic
Decelerator (Parachute, etc.) Development and
Qualification Technology Investment 50 - 60M
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Suggestions for Consideration Mars Landing Systems

• Initiate a human-scale landing system
  configuration study before defining a subscale
  demonstration at Mars and its supporting
  technology development program

Inflatable Aeroshells
Supersonic Deceleration Methods
Hypersonic Deceleration Methods?
Higher Mach Parachutes
Deployables
Alternative Decelerators
Slender Body Aeroshells
Propulsion
Define the configuration for demonstration
and supporting technology program Include
guidance concepts and pin-point landing
Soft Landing
Impact Attenuation
Configuration
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Program Feed-Forward for Heavier Mass Landed on
Mars
2000
2010
Ballistic 1 Chute
MER
.4MT
L/D .2 1 Chute
.4MT
Phoenix
L/D .2 1 Chute Throttle Engines
MSL
1.1MT
MSR Orbiter
ST-9 Demo
Aerocapture
MidL/D? N chutes? 3-4 MT
L/D .2 2 Chutes
MSR Lander
1.4MT
MidL/D? TBD number of chutes
Scalable to human mission
3-4 MT
Testbed