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Mars Sample Return Discussions
February 23, 2010
1
Agenda
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*Mars Sample Return is conceptual in nature and is subject to NASA approval. This approval would not be granted
until NASA completes the National Environmental Policy Act (NEPA) process.
"For Planning and Discussion Purposes Only"
2
Multi-element Mars Sample Return Architecture
"For Planning and Discussion Purposes Only"
3
Mars Sample Return Discussion - Overview
Multi-element Mars Sample Return Campaign provides robust architecture
•! Multi-element approach derived from numerous studies
•! Provides technical robustness and programmatic resilience
Technology challenges for mission elements are identified
•! Past investments laid ground work for many key required engineering
capabilities
•! Technology tall-poles have been identified: discuss status and development
plans that are mapped to mission needs
•! Other technical challenges also identified
Cost assessments
•! Mission element concepts developed to “Team X” level: recent updates
•! FY15 $/reserves per decadal survey guidelines
•! Recent updates to Independent Cost Estimate performed for NASA HQ in
May ‘08
"For Planning and Discussion Purposes Only"
4
Functional Steps Required to Return a
Scientifically Selected Sample to Earth
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**Note: Launch sequence of MSR-L/MSR-L can be switched:
launching MSR-O first can provide telecom relay support for EDL/
surface operation/MAV launch
"For Planning and Discussion Purposes Only"
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5
Multi-Element Architecture for Returning
Samples from Mars Is a Resilient Approach
*
*
MAX-C (Caching Rover)
*
*
Mars Sample Return Orbiter Mars Sample Return Lander
Mars Returned Sample
Handling
Science robustness
•!Allows robust duration for collection of high quality samples
Technical robustness
•!Keeps landed mass requirements in family with MSL Entry/Descent/Landing
(EDL) capability
•!Spreads technical challenges across multiple elements
Programmatic robustness
•!Involves mission concepts with sizes similar to our implementation experience
•!Incremental progress with samples in safe, scientifically intact states: improved
program resiliency
•!Spreads budget needs and reduces peak year program budget demand
•!Leverages and retains EDL technical know-how
"For Planning and Discussion Purposes Only"
*Artist’s Rendering
6
Mars Astrobiological Explorer-Cacher (MAX-C) rover
MAX-C rover will perform in situ exploration of
Mars and acquire/cache dual sets of
scientifically selected samples
•! Team X conducted Decadal Survey Mars Panel
study in Jan’10: added dual cache
Major Rover Attributes
Science Capability
Remote and contact science: Color stereo imaging,
macro/micro-scale mineralogy/composition, micro-scale
organic detection/characterization, micro-scale imaging
Key mission concept features
•!
Cruise/EDL system derived from MSL, launched
on Atlas V 531 class vehicle.
•!
Land in ~10 km radius landing ellipse, up to -1 km
altitude, within +25 to -15 degrees latitude.
•!
43% mass margin carried on MAX-C rover
(adopting many MSL parts), landing platform, and
hardware where specific modifications would be
made to the MSL EDL system.
Coring and caching rock samples for future return
Payload Mass
~15 kg instruments
~60 kg including corer/abrader, dual cache, mast, arm
Traverse Capability
20 km (design capability)
Surface Lifetime
500 Sols (design life)
Instrument/Sensing
Mast
Quad UHF
Helix
High Gain Antenna
Low Gain Antenna
*
SHEC
“Sample
Cache”
Hazard
Cameras
* Artist’s Renderings
2.2m
Ultraflex
Solar Array
Sampling/Science
Arm
"For Planning and Discussion Purposes Only"
7
Current 2018 Mission Concept Implementation Approach
Team X study concept included:
Land MAX-C and ExoMars rovers together
•!
attached to a landing platform
•!
MAX-C and ExoMars rovers perform in
situ science exploration: assessing
potential joint experiments
•!
MAX-C will cache scientifically selected
samples for future return
•!
*
*
•!
MSL Cruise/EDL and
Skycrane system lands
Rovers on platform
*
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Landing platform (pallet): ‘proof-of-concept’ by Team
X; with further refinements by dedicated design
team
Scaling of MSL aeroshell diameter (from 4.5 m to
4.7 m) to accommodate 2 rovers
•! Preserve MSL shape, L/D
•! Same thermal protection system
•! Same parachute
Descent stage architecture/design based on MSL
•! Same MSL engines, avionics, radar,
algorithms, etc
•! Mechanical structure updated to
accommodate rovers/platform geometry/loads
•! Incorporates terrain-relative descent
navigation capability
*
*
*
MAX-C Rover
* Artist’s Renderings
* Artist’s Renderings
"For Planning and Discussion Purposes Only"
Rovers post-landing
w/ example egress aids
8
Mars Sample Return Orbiter Concept
MSR Orbiter will
•!
•!
•!
•!
•!
•!
Rendezvous with Orbiting Sample (OS)
container in 500km orbit.
Capture, transfer and package OS into Earth
Entry Vehicle (EEV)
Perform “break-the-chain” of contact with
Mars
Return to Earth
Release EEV for entry
Divert into a non-return trajectory
If Before MSR Lander
•! Monitor critical events of EDL and MAV
launch
•! Provide telecomm relay for lander and rover
Key mission concept features
•! Over twice the propellant needed by typical
Mars orbiters. Uses bi-prop systems flown
on previous Mars missions
•!
UHF Electra relay system for surface relay
•!
Orbiter mass quite dependent on specific
launch and return years. Designed to
envelop opportunities in early-mid 2020s.
EEV
50 kg
Orbiter
Rendezvous systems
20
Systems
Capture/Sample Transfer
40
Avionics
40
Power
130
Structures/Mechanisms
330
Cabling
40
Telecom
30
Propulsion
170
*
*
Thermal
Team-X Design:
Alternate Design:
No “staging” required
Separate prop stage
that separates after
Trans Earth Injection
* Artist’s Renderings
Misc. Contingency
TOTAL Orbiter Systems Mass
40
100
940 kg
Propellant
2280 kg
TOTAL (43% margins)
3270 kg
"For Planning and Discussion Purposes Only"
9
MSR Orbiter: Sample Capture/Earth Entry Vehicle (EEV)
*
*
*
Capture Basket concept testing on Orbiting Sample (OS) container
NASA C-9 zero-g aircraft
*
Strawman EEV design
Detection and rendezvous systems
–! OS released into a 500km circular orbit by the
MAV
–! Optical detection from as far as 10,000km.
–! Autonomous operation for last tens of meters
Capture System
–! Capture basket concept designed
–! Prototype demonstrated on NASA zero-g aircraft
campaign.
–! 0.9m diameter, 60° sphere-cone blunt
body
–! Self-righting configuration
–! No parachute required
–! Hard landing on heatshield structure,
with crushable material surrounding OS
Capitalizes on design heritage
–! Extensive aero-thermal testing and
analysis
–! Wind tunnel tests verified self-righting
* Artist’s Renderings
"For Planning and Discussion Purposes Only"
10
Mars Sample Return Lander Concept
MSR Lander will
Key mission concept features
•!
Land a pallet with Mars Ascent Vehicle (MAV)
and fetch rover
•! MSR lander pallet delivered to the surface via the
Skycrane EDL approach
•!
Upon safe landing, the fetch rover will egress
and retrieve MAX-C sample cache
•! Traverse distance up to ~14 km
•! Supports and protects MAV in thermal igloo and
minimizes thermal cycle depths
•!
Sample cache transferred by robotic arm on
pallet from fetch rover to MAV
•!
MAV will launch sample container into stable
Martian orbit
Ultraflex Solar
Array
UHF
•! 1 Earth year life
Lander WEB
MAV
*
Fetch
Rover
Lander arm
Bio-Thermal
Barrier
*Artist’s concept
*
Egress Ramps
Fetch
Rover
"For Planning and Discussion Purposes Only"
11
MSL EDL Feed Forward To MSR
•!
MSL EDL system will deliver ~1000 kg rover to the surface for ‘11
launch
L
*
–! Can be used for MAX-C in 2018 and the MSR Lander in 2020s
•!
Mass of three major sub-elements of MSR lander ~ 1000 kg
•!
EDL performance is relatively constant between 2011 and ‘22-’26
–! Can accommodate the MSR Lander
–! 2018 is a more favorable opportunity than 2011 for EDL
•!
MSL EDL system capability may be improved to accommodate
minor increase (~5–10%) to landed mass
D
V
!
g
*
–! Options include increased entry body L/D and parachute deployment Mach
number
•!
Three flight-element approach improves resilience for landed mass
* Artist’s Renderings
"For Planning and Discussion Purposes Only"
12
Mars Returned Sample Handling Element
Mars Returned Sample Handling
element includes: ground recovery
operations; Sample Receiving Facility
(SRF) and sample curation facility
The SRF will
•! Contain samples as if potentially
hazardous, equivalent to biosafety
level-4 (BSL-4).
Industry studies performed to scope
facility and processes (2003)
•! 3 architectural firms, with experience in
biosafety, semi-conductor and food
industries.
•! Current costs estimates and scope
based on studies and comparison to
existing BSL-4 facilities.
•! Keep samples isolated from Earthsourced contaminants
•! Provide capability to conduct
biohazard test protocol as a
prerequisite to release of samples
from containment.
•! Could serve as a sample curation
facility after hazard assessment.
Artist’s concept of an SRF
"For Planning and Discussion Purposes Only"
13
Technical/Technological Challenges
for
Multi-element Mars Sample Return
Campaign
"For Planning and Discussion Purposes Only"
14
Existing* Technical Capabilities
•!
Navigation:
–!
•!
EDL:
–!
–!
•!
Reliable and precise navigation to entry corridor (~1.5km, knowledge)
Skycrane providing landing capability of ~1000 kg payloads
Guided entry providing ~10km (radius) landing accuracy
Mobility:
–!
Rovers with long traverse capabilities using
•! Autonomous hazard avoidance utilizing stereo cameras
•!
•!
Instrument placement:
–!
•!
Ability to satisfy forward planetary protection for landers and orbiters
Phoenix's Bio-Barrier to keep manipulator arm in sterilized condition until after landing on Mars
Sample Return:
–!
•!
Direct to Earth and relay communication capability
Planetary Protection:
–!
–!
•!
Lessons learned from Phoenix’s sample acquisition and sample transfer
Development of a drill for MSL and its sample transfer subsystem
Telecom:
–!
•!
Ability to approach and place tools and science instruments on targets with a single command with less than
~1 cm error
Sample Acquisition:
–!
–!
•!
Visual odometry providing accurate measurement of wheel slippage
Genesis and Startdust missions
Rendezvous and Capture:
–!
* Including flight and MSL design heritage
DARPA Orbital Express
"For Planning and Discussion Purposes Only"
15
Multi-element MSR Campaign
Technologies
•! Tall pole technologies
•! Defined as key technologies that require significant
development
•! Sample acquisition and encapsulation (MAX-C)
•! Mars ascent vehicle (MSR lander)
•! Back planetary protection (MSR orbiter)
•! Other key challenges
•!
•!
•!
•!
Round trip planetary protection (MAX-C)
Mobility capability (MAX-C and MSR fetch rover)
Terrain-relative descent navigation (MAX-C and MSR lander)
Rendezvous and sample capture (MSR orbiter)
"For Planning and Discussion Purposes Only"
16
Sample Acquisition and
Encapsulation
17
Target Requirements
Consistent with MEPAG Next Decade Science Analysis Group (ND-SAG)
Science
–! Acquire~ 20 rock cores with dimension
approximately 1 cm wide by 5 cm long
–! Store and seal samples in individual
tubes
–! Provide capability to reject a sample
after acquisition
–! Measure the sample volume or mass
with 50% accuracy
Engineering
–! System mass to be ~30kg
•! Includes robotic arm
–! Sample on slopes up to 25 degrees
–! Sample from a ~300kg rover
Examples of acceptable samples
"For Planning and Discussion Purposes Only"
18
Current Capabilities/State of the Art
•! Ten years of technology development
•! MTP, MIDP, SBIR, etc.
•! Two flight-like corers developed by
Honeybee Robotics:
•! Mini Corer (for ’03/‘05 MSR)
•! CAT (for MSL) in 2006.
•! MSL flight drill developed and tested
•! Drilling and coring testbed developed
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"For Planning and Discussion Purposes Only"
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19
Strawman Development Plan
•!
•!
•!
•!
Four end-to-end system concepts are being develop by industry and JPL in FY ‘10
MEP will select an approach that best fits MAX-C rover architecture and its constraints
Develop sample acquisition and encapsulation capability to TRL 6 prior to MAX-C PDR
Verify system performance via laboratory and rover field tests
ATK Concept
Honeybee Concept
Alliance Space Systems
Concept
"For Planning and Discussion Purposes Only"
JPL Concept
20
Mars Ascent Vehicle (MAV)
21
MAV Target Requirements
•! Launches 5kg Orbiting Sample (OS) into 500
+/-100 km orbit, +/-0.2deg
•! Ability to launch from +/- 30o latitudes
•! Continuous telemetry for critical event coverage
during ascent.
•! Survive relevant environment for Earth-Mars
Transit, EDL, and Mars surface environment
for up to one Earth year on Mars
•! 300kg (including OS)
"For Planning and Discussion Purposes Only"
22
Current Capabilities/State of the Art
NASA has not launched a rocket from a planetary surface
autonomously before.
Three industry MAV studies performed in 2001-2002
•! Considered solid, liquid, and gel propulsion systems.
•! Identified technology gaps, assessed risk, and provided estimates for
mass, volume, and cost.
•! Several follow-up reviews and RFIs have been conducted
Summary study results
•! Solid propulsion was judged to be more reliable, simpler, and most
mature
•! MAV components are available, but are not developed for long-term
storage in relevant environments (including thermal cycling) or for EDL
g-loads.
–! Long term martian surface storage more demanding than typical
storage in space
•! Mass estimate assessment ~300 kg
•! Preliminary cost assessment for TRL 6 development
–! Design/development including environmental qualification, ground
and high-altitude flight tests ~$250M (adjusted to $FY15 with 50%
reserves)
"For Planning and Discussion Purposes Only"
23
Solid Two-Stage Mars Ascent Vehicle Concept*
All figures are artist’s concepts
Payload Fairing
Orbiting Sample
(OS)
Avionics
Compartment
Stretched Star
17A SRM
TVC Actuators
2.5 m
Star 13A SRM
•! Kept thermally stable in an RHU-augmented thermal
igloo.
•! Continuous telemetry for critical event coverage
during ascent.
•! Fully redundant C&DH
•! Uses standard and stretched solid rocket motors
(SRMs). Same fuel as MER and Pathfinder descent
motors.
•! Flight time to orbit ~700 sec
•! 3-axis stabilized
•! Stage-one uses a Thrust Vector Controlled nozzle
•! Stage-two uses a fixed nozzle. Steering is
accomplished by the use of four pairs of 20Ibf
hydrazine engines (primary and backup)
* LMA 2002 study
"For Planning and Discussion Purposes Only"
24
Strawman Development Plan
•!
Phase 1: Early investment (~$3M funded by In-Space Propulsion ROSES
NRA, start date ~10/1/2010)
–! System definition and development studies (~6 months)
–! Propulsion subsystem development and tests for select MAV concepts (~3 years)
•!
Phase 2: Component technology development to TRL 6 and system
architecture downselect (~2 years, ~$40M, may include ISP follow-on
options)
–! Develop component technologies to reach TRL6
–! Test components’ performance in realistic temperatures, storage, EDL g-loads as appropriate
–! Culminates in the final downselect to a single concept, whose high-risk components have known
performance and survivability characteristics
•!
Phase 3: Integrate and develop a MAV. Perform integrated testing and
qualification. (~3 years, ~$210M, includes ISP Phase 3 options)
–! Perform three high-altitude flight tests to assure at least two successful tests and measure
performance prior to MSR lander PDR.
–! At least one flight test must be performed on unit that has successfully completed environmental
qualification/life testing
•!
Flight Project responsibilities, after completion of technology program:
–! Update design based on test results, fabricate flight unit hardware, spare, and interface test
articles (mechanical, electrical/testbed), complete flight acceptance test, and deliver to ATLO
"For Planning and Discussion Purposes Only"
25
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ROSES ISP MAV NRA
(~3.5 yrs
ISPduration)
MAV Studies
ISP follow-on
"For Planning and Discussion Purposes Only"
26
Back Planetary Protection
27
Planetary Protection
Requirements & Mission Scenarios
Forward PP
Round Trip PP
Outbound to Earth
Outbound to Mars
Avoid contamination of Mars
with Earth life
Introduction of viable Earth life into
a favorable martian environment is
considered harmful contamination
by definition
Back PP
Avoid false positive life detection event
Life detection event in this context is considered
to mean detection of contamination that could
be confused with extraterrestrial (ET) life
"For Planning and Discussion Purposes Only"
Protect Earth from potentially
harmful effects
(biohazards)
28
Target Requirements
OS
•!
•!
MSR is a Restricted Earth Return mission
–! Goal of <10-6 chance of inadvertent release of an
unsterilized >0.2 micron Mars particle.
CV Top
CV Bottom
Sealed CV
Subsystem requirements:
–! Break-the-chain of contact with Mars
•! Deliver a “Mars contained” OS to Containment
Vessel (CV)
•! Assure OS does not “leak”
•! Mitigate ascent and orbiter dust
–! Sample container protection
Impact
Sphere
Orbiting
Sample
(OS)
Containment
Vessel (CV)
Earth Entry
Vehicle (EEV)
•! Reliable delivery to Earth entry corridor utilizing a
robust Earth Entry Vehicle (EEV)
•! Assure containment at impact
•! Maximize OS , CV, and EEV meteoroid protection
–! Quarantine in specialized sample handling facility
and application of a test protocol to assess safety
prior to release
"For Planning and Discussion Purposes Only"
29
Current Capabilities/State of the Art
•!
Probabilistic Risk Analysis (PRA) approach was
developed to assess the overall probability of meeting
the goal
•!
Preliminary design of the EEV was completed and a test
article developed. Performed component and system
tests:
–! EEV drop test achieved terminal velocity and demonstrated
shock tolerance.
–! Wind tunnel tests verified aerodynamics, including self-righting.
–! Arc jet tests verified TPS performance.
•!
A brazing technique was developed to TRL 3 for
containment assurance and breaking the chain of
contact with Mars
•!
Leak detection
–! OS leak-detection technique using wireless transducer was
demonstrated at TRL3 via an SBIR
•!
Sample container protection
–! Preliminary materials for OS, CV, and EEV to assure meteoroid
protection were selected (TRL 2-3 development).
"For Planning and Discussion Purposes Only"
30
Strawman Development Plan
•!
Update/improve models for Probabilistic Risk Analysis (PRA) to measure capability to
meet goal
•!
Breaking-the-chain
–! Investigate various options of sealing the OS in a container. Will implement and evaluate prototypes
•! Down select and develop technology to TRL 6. Test and verify sealing
–! Develop OS leak detection technique by considering pressure drop or other techniques
•! Down select and develop technology to TRL 6
•!
Sample container protection
–! Update EEV design considering the availability of TPS material
•! Perform impact, heat, and aerodynamics tests
–! Select materials for OS, CV, and EEV and satisfy meteoroid protection requirement
•!
Assure containment and sample integrity during ground processing
–! Sample transfer from landing site to Sample Receiving Facility
–! Ultra-clean sample manipulation, double-walled glove boxes
"For Planning and Discussion Purposes Only"
31
Example Back Planetary Protection Development Schedule
"For Planning and Discussion Purposes Only"
32
Other Key Challenges
33
Other Key Challenges$
•! Round trip planetary protection (MAX-C)
–! Objective: Avoid false positive life detection
–! Approach: Clean assembly, bio-barrier, analytical tool to
compute overall probability of contamination
Round Trip PP
•! Mobility capability (MAX-C and MSR fetch rover)
–! Objectives: Increase average rover speed and develop
lighter/smaller motor controller
–! Approach: Use FPGAs as co-processors and develop
distributed motor control
•! Terrain-relative descent navigation (MAX-C and
MSR lander)
–! Objective: Improved landing robustness
–! Approach: Use terrain-relative navigation approach for
avoiding landing hazards. Leverage NASA ALHAT project
50 cm
rover
move
timeline
Safe Landing
•! Rendezvous and sample capture (MSR orbiter)
–! Objective: Locate, track, rendezvous, and capture OS in
Mars orbit
–! Approach: Update system design, develop testbeds, and
perform tests. Leverage Orbital Express capability
Sample Capture
"For Planning and Discussion Purposes Only"
34
Estimated Technology Cost Including 50% Reserve ($M)
MAX-C ($85M)
MSR Orbiter ($160M)
MSR Lander ($250M)
"For Planning and Discussion Purposes Only"
35
Cost Assessment for Multi-element
Mars Sample Return Campaign
"For Planning and Discussion Purposes Only"
36
Cost assessment approaches
•! Three sets of costs are provided, all in constant $FY’15 and include
S! Mission and flight system development and ATLO (including technology)
S! Launch vehicles
S! Mission and ground operations
•! First set of mission cost estimates are derived from JPL Team X studies
S! Team X cost estimating process employs representatives of the potential doing
organizations
S! The flight system WBS for each mission composed of many separate cost elements
(e.g., propulsion, thermal, mechanical, etc.)
S! Several additional WBS elements estimated by wrap algorithms (e.g. mission design)
and look-up catalogues, including the NASA instrument cost model
S! Recent MSL experience is taken into account
S! Team-X results have included
S! Development (phase A-D) reserves of 50%, phase E reserve of 25%
S! Technology/advanced engineering development, also with reserves of 50%
•! Second set of mission cost estimates are derived from analogy (enabled by multi-element
approach) with recently implemented missions in the program (completed by program office)
S! MSL and MRO are used for analogy
•! Third set of mission cost estimates are taken from a 2008 independent cost estimate by
Aerospace Corp., conducted for NASA Headquarters, recently updated in Oct’09.
"For Planning and Discussion Purposes Only"
37
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"For Planning and Discussion Purposes Only"
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"For Planning and Discussion Purposes Only"
39
*
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"For Planning and Discussion Purposes Only"
40
*
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41
Multi-element Sample Return Cost Estimates
(All In $FY ’15)
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"For Planning and Discussion Purposes Only"
on Oct/Nov’09 Team X
concept
42
Example Scenario for Multi-element Mars Sample Return Campaign
•! ‘16 Joint NASA/ESA orbiter
•! ‘18 MAX-C Joint NASA/ESA mission
•! ’22 MSR-O (Assuming it is a NASA-only mission)
•! ‘24 MSR-L (Assuming it is a NASA-only mission)
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43
Examples of Scenarios for Mars Sample Return Campaign
•! ‘16 Joint NASA/ESA orbiter
•! ‘18 MAX-C Joint NASA/ESA mission
•! ’22 MSR-O (Assuming it is a NASA-only mission)
•! ‘24 MSR-L (Assuming it is a NASA-only mission)
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•! ‘16 Joint NASA/ESA orbiter
•! ‘18 MAX-C Joint NASA/ESA mission
•! ’22 MSR-O (Assuming a joint mission; NASA contributes 25%
of mission cost)
•! ‘24 MSR-L (Assuming a joint mission; NASA contributes 80%
of mission cost)
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•! ‘16 Joint NASA/ESA orbiter
•! ‘18 MAX-C Joint NASA/ESA mission
•! ’22 MSR-O (Assuming a joint mission; NASA contributes 25%
of mission cost)
•! ‘26 MSR-L (Assuming a joint mission; NASA contributes 80%
of mission cost)
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44
Summary
•! Strong scientific impetus for sample return
–! Next major step in understanding Mars and the Solar System
•! Engineering readiness for sample return
–! Past investments have developed key capabilities critical to sample return
–! Key remaining technical challenges/development are identified
•! Resilient multi-flight-element approach
–! Science robustness
•! Allows proper sample selection/acquisition
–! Technical robustness
•!
•!
Spreads technical challenges across multiple elements
Keeps landed mass requirements in family with MSL EDL capability
–! Programmatic robustness
•!
•!
•!
•!
Involves concepts similar to our existing implementation experience
Scientifically intact samples on/around Mars that provides program resiliency
Spreads budget needs over ~1.5 decade
Approach amenable to international partnership
•! Multi-element MSR should not be viewed as an “isolated (flagship) mission”
but as a cohesive campaign that builds on the past decade of Mars
exploration
"For Planning and Discussion Purposes Only"
45