The topics are presented in viewgraph form and include the following: Mars Observer; Mars Environmental Survey (MESUR); and the Small Rovers and Sample Return missions

Dickinson, Tamara L.

English

NASA Technical Reports Server

N93-26899
MARS EXPLORATION PLANNING
Tamara L. Dickinson
National Aeronautics and Space Administration
Washington, DC 20546
Mars Exploration Planning
I Ill It !!,, ....
I .......
O_b II $ k'lr '
-,r _ p
• Mars Observer
• MESUR
* Small Rovers and Sample
Return Missions
E pl ti P1 i g o_-.,_Mars x ora on ann n _:_?,,o-
Mars Observer
MESUR
Small Rovers and Sample
Return Missions
107
PRECEDING P.,a_GEBLANK NOT FILMED
https://ntrs.nasa.gov/search.jsp?R=19930017210 2020-03-17T05:42:04+00:00Z
Mars Observer: Mission Rationale V.o);
While Knowledge of Mars is Extensive, It Contains
Significant Gaps. More Importantly, There Are a Number of
First Order Scientific Questions That Can be Best Addressed
From an Orbital Platform. The Geoscience/Climatology
Orbiter Will Provide New Observations and Complement
Existing Measurements, and Provide an Improved Basis for
Future Intensive Investigations.
]l r r
III IIIII IJ
Mars Observer
I I
SSEC Report
o _ TM
• Low Altitude Polar Orbit
• 1 Martian Year Mission Duration
L
• Simple Repetitive Geological/Climatological Mapping Mission
• Spacecraft Based on Derivative of Earth Orbital Spacecraft
• Experiments Selected Concurrent with Spacecraft
I08
SCIENCE OBJECTIVES
MARS OBSERVER WILL
DEFINE GLOBALLY THE TOPOGRAPHY
AND GRAVITATIONAL RELD
DETERMINE THE GLOBAL ELEMENTAL
AND MINERALOGICAL CHARACTER
OF THE SURFACE MATERIAL
DETERMINE THE TIME AND SPACE
DISTRIBUTION, ABUNDANCE, SOURCES,
AND SINKS OF VOLATILE MATERIAL AND
DUST OVER A SEASONAL CYCLE
EXPLORE THE STRUCTURE AND
ASPECTS OF THE CIRCULATION
OF THE ATMOSPHERE
ESTABLISH THE NATURE
OF THE MAGNETIC FIELD
Mars Observer
'i lii I i , • i l ........ !t
I •
Science Instrument Measurement Objectives
'0 I _q%
Gamma Ray Spectrometer
Magnetometer
Mars Observer Camera
Pressure Modulator
Infrared Radiometer
Radar Altimeter
Radio Science
Thermal Emission
Spectrometer
Elemental Composition of Surface
Intrinsic and Local Magnetic Field
Global Synoptic Views, Selected Moderate and Very
High Resolution Images of Surface and Atmosphere
Profiles of Temperature, Water, Dust, and Radiation
Budget Measurements
Topography, Microwave Radiometry
Gravitational Field; Atmospheric Refractivity Profiles
Surface Mineralogy; Atmospheric Dust and Clouds:
Radiation Budget
109
Mars Observer Status
I
_.l ! k#
I IIII1[ 1-11
• Spacecraft Assembly and Test Nearing Completion
• Five of 7 U.S.-Supplied Instruments Delivered and Integrated
- Remaining 2 to be Delivered in February
- Gamma-Ray Spectrometer Electrically Integrated with
Spacecraft and Functional Testing Completed
....
• Excellent Instrument Performance
- Thermal Emission _pectrometer Successfully Completed
Acceptance Tests and Was Delivered _
- Pressure Modulator Infrared Radiometer (PMIRR)
Integrated Systems Testing Successfully Completed
11o
Mars Observer Status _'_9,_;
ZO R _
I IIIIII ......... EL.._ t t tH
I
* Instrument and Spacecraft Integration and Test Schedules
Remain Challenging
- Mars Balloon Relay Delivered and Integrated
- Mars Observer Camera Electronics Completed and
System Performance Testing Underway
• All Titan III Major Design Reviews Completed
- TOS Completed and in Storage
- Launch Complex Behind Schedule, but on Recovery Plan
].
Mars Exploration Planning
I IIIH tJ ..... Hill III ..... I
Mars Observer
MESUR
Small Rovers and Sample
Return Missions
111
MESUR Philosophy
o_ _ _
• "Grow" a Survey Network Over a Period of Years
(a Series of Launch Opportunities)
• Develop a Level of Effort Which is Flexible
and Responsive to a Broad Set of Objectives
• Focus on Science Return While Providing
a Solid Basis for SEI (e.g., Site Selection Data)
• Minimize Cost and Complexity Wherever Possible
Baseline Mission Profile
TH'rWIn ......... i llillll lllll I! I[F
• 16 Landers
• Delta II Launches at Every Opportunity
- 2001, 2003, 2005
- 4 Probes per Launch
• Small Free-Flyer Spacecraft, Spin Stabilized
_2
O _ -,r 5 j.j.
- Probes Designed as Cruise Stage, Entry System, Lander
- Design Based on Pioneer & Viking Heritage
• "Hard" Landing of <40 g's
• RTGs
- Communications Orbiter
• Launch 2003 ..
112
Launch Configuration
II II I IIII dill IIIII
il i
Four MESUR Probes
on Delia Launch Vehicle
Payload Envelope
_SUR Probes
MESUR Mission Summary
I III I IIIIIII IIIII IIII I IIIIII IIIII I IIIII II I II1' II I
III II I II I
li I
[ndepcndcn( Frccflight to Mars
Probe Rclcase
P_achu_e Release
& Aeroshen Separation
Insmamen[ Dcployrnen_
& Surface Operallons
i13
MESUR Descent and Deployment
lo ft ¢,,L"
Pr0b¢ Cruise
Cruise Stage/
Cover = 10 km
Deploy Main Chute
Lander/Aerocra ft _
Separation = 10 km
Release Chute
Deploy Air Bag = :2 m
Detailed Mission Obiectives
and Assumptions from MarsSWG
.............. II ..... J II ....
I
• Descent and Surface Imagery (Multiband)
- Nested Images Desirable but Not Required
• Landing Accuracy on the Order of 100 km
- Knowledge of Relative Lander Position to I km
• Entry Science Performed
- Atmospheric Structure Experiment
114
RANGER DESCENT IMAGING
Descent Imaging Concerns ;.°:.,,o_O;:
ili II II IlUlUnl II I II I_111_
ii
,l
.I
(20_) I I ,I
r,_rtFO'¢
_ Dislance
gkm
r.,.,,.,=3
Figure V-2. Dcsccn( Imaging Conccpl
Unccaa[nty of Wind Magni|od¢
115
Detailed Mission Obiectives
and Assumptions from MarsSWG
........ I' ' .......... I_ ' _ ]11 II I
11I III I
• Meteorology Measurements
Long Station Life (Simultaneous
Measurements for 1-3 Mars Years)
Large Number of Widely Dispersed
Stations (15-20)
Pressure, Opacity, Temperature, Winds
and Humidity if Possible
I
Detailed Mission Obiectives
and Assumptions from MarsSWG
IImIIIIII . I[. [lllJ..
II
0 _ _
• Seismology Measurements
Short Period Seismometer, Single
3-Axis, as Broad Band as Possible
Surface Emplaced Seismometer
Long Station Life (>1 Mars Year)
I16
Detailed Mission Obiectives
and Assumptions from MarsSWG
IJllillli
J _ z
° GeochemistryMeasurements
Instruments Placed on Surface
Elemental Composition Instrument ((_-p-x)
Deployed at Each Station
Thermal Analyzer and Simple Evolved Gas
Analyzer
Strawman Lander Science Payload
IIII I
• Atmospheric Structure Experiment
- Determination of Winds
m b _
_'0 _ ar
"_4 _,Lv 0
lU
• Descent/Surface Imager (CCD/CID Array)
• Meterology Package
- Atmospheric Pressure
- Atmospheric Opacity
- Temperature, Humidity, and Winds (at lm Above Lander)
• Surface Composition (c_-p-x)
• Seismometer
• Impact Accelerometer
• Thermal Analysis Instrument (e.g., DSC)
117
_.g SPr
LanderMESUR ' **
Fiber Optics Camera &
MeteoroTogy Probe
Solar Panels-total collection area is 1.24 m z
Sensor Ports
Imaging
Antennas
mp-x Sensor
Batteries
Seismology Sensor
MESUR Strawman Science Payload
1[!! Inillrlll I .......... '1 ,.. __.= _" -
INSTRUMENT
MASS I'OWF;R DATA DIM_NSIONS LATIn. DE IIERITA(;E MAX, OPERATIONS
(kg) (W) (cm) DEPENDENCY 'g' DUTY
. koa_ cYcLe:
MEFEOROLOG Y PACKAGE 0,66 0.021
Note (I) *
3-AXIS $EISMOMEI'ER 1-5 2
SeTMnsorpa¢l_ge ) ' Note 2
OSPHE.RIC 5"I'R U[_FURF:S "1.$ "" ' 6.2
INS_RUM_¢]I', Nole (1)
E_ENTAL COMPOSITION
INSTRUMENT,
(p_._°Abalp r o_o n/x'r a_}
GERS:
$URF'AC_
COMMON
ELECTRONICS
THERMAL ANALYZER &
EVOLVED GAS ANALYZER
ANALYSER
I0
kblls per day Nol AvIIls_It
-<_F_r----_
wind, tamp
po[n( me_Lsur¢.
m tI_L_,humidity,
pressurr
conHnuous
<500 53 rain utes
I0 Mbtl_day NEW
65 bp_ 4 • (5-] 0) long Note (1)_ Galileo. PV.
($ _nsor s) Viking
lOxl3x 13
(tie( bo, lJ.
'0.6 0.5 100 kbtts need aloe[ primarily NEW, <,40 600 minutes
for 5 spcclra dimensions il(e Viking
t (4J x 3.2) dependent
_ :_::'_'_4":':::"<.........................: '::::':<:_ ......... ['IMbILI - 6X6x3 ,, :.:: :::::I_:_:NEW II I ::::::::::::::::::::::::::::::::::::<40c0nlinuous
to store (head) during
12 Imal_s l0 x 10 • } descent
* (internal elec)
1.36 21 25MbI_ I0 x IS X 6 NE_V <40 --l_]-n_-e_
per (cameraddrlve)
_60 deg _can tO00 x t dia
(M..a)
3x/x$
• (lie|d)
0.26 NOIC } :::::::::::::::::::::::::::: Included w/ NEW included w/
:::::::::::::::::::::::::::::::
_!_i_i_:_i___ii_!_:'ii :_:!:i: Iml_erl Ima_er|
2 12 .)M bil_ 12 • I • 12 primarily NEW <40 60 minutes
per sam pie site (4 sam pies
dependent _er martian year)
i mgs_ ale[mate _o_ not [n¢|_lo deploFaw, at hardwu¢
(I) may sh_wc conm_on se.nsor
(2) m_ e_Cm.t_ fo_ _ only
(3) mass _tlmalt, included in de..Ice_l at_d surface imsgerl m_s estima_
118
Mars Exploration Planning
_,'_,o
Mars Observer
MESUR
>- Small Rovers and Sample
Return Missions
Science Drivers: Sample Return Mission
I III I I IIII IIIIIII I IIHIgllllgl')ll
0_1.I k $ _',p..
• Return Martian Samples to Earth Laboratories for Analysis
- Highest Priority Science Objective for Mars
• Geology of Mars
- Based on Geologic Mapping from Viking Images
(Defined Units kms Scale)
• Defined 10 Different Units
- Need --10 Different Types of Samples Returned
119
Science Drivers: Sample Return Mission
I fl IN
p_ 5 b,s
Heavily Cratered Material _-_ Early History of Planets
Volcanic Rocks _ Age and Composition of Planet
Sedimentary Rocks _ Climatologic and Biologic (?) Conditions
Drift Material, Soil, Salts, __" Volatile Inventory
Ice, Atmosphere
MSRS "Old Think"
Fly in '96
Appropriate
Technology
Large, Heavy
Elements
2 Titans/
Sample Return GrowingCost
Result
• Many interacting elements, complex operation
• Extremely Capable Rover
• Two Titan 4 Launches for One Sample Return
• Risk management through very high reliability, single items
• Cost ~$10B
120
Micro Technology Based Approach
"New Think"
I
Result
Emerging
Micro
Technologies
Small, Light Many Landers
Elements per Flight
Affordable
"F '_ , y 0
• Much smaller pieces - few on a Delta or Atlas
• Risk Management through many tries
° Cost goal -$1.5 - 2 B
Key Concepts to "New Think" _:_:_
Take Advantage of Emerging Micro Technologies
- Most Develop Outside NASA, Particularly for SDI
- Includes Integrated Electronics, Power, Processors, Propulsions,
Software...
Focused Science
- Limited Access from Lander and Constrained Landing Regions
- Less Capable Rover
- Less Elaborate Sampling
- Less in-situ Science
- No Traverse Science
- Less Stringent Sample Preservation
121
Key Concepts to "New Think"
Simplify Missions to Absolutely Essential Elements
Commit to Many Small Landers
- Accept that Some Fraction (-20%?) Will Fail
- Manage Risk by Increased Number of Independent Landers
- Mission Success Achieved with a Fraction (<1) of Landers Successful
Comparison of Approaches ._o_._.,o._.o..,,
Returned Samples
- Both ~8-10 Different Sample Types
- Similar Total Mass
- MRSR Samples from 2 Areas
- Small SR Samples from Diverse Areas
122
Comparison of Approaches
E I • III II I II i
II I
Rovers/Landers
- MRSR
• Large Complex Rover
• Many in-situ Instruments on Rover
• Traverse Science
• Sample Packaging/Preservation on Rover
- Small SR
• Small Simple Rover
• No Traverse Science
• Most in-situ Instruments on Lander
• Sample Preparation on Lander
• Different Instruments on Different Landers
_,1_ I $ _'_j,
0 _r "
IIIIII ._
Small SR
_U__l i
o_ "" *-j,_
"_M '_y O
• Satisfies All Major Science Objectives
• Simple Approach
• Flexible
• Less Expensive
• Failure Tolerant
123
Key Technologies
IIIIII II ! III IIIIIIIIIIIlUll
ll_ I _1,_.
:O:*.
Io R P-_'\
I IIII
• Mini RTGs
• Advanced Propulsion Systems
• Small Rover 'Behavior' Control
• Micro Sensors and Instruments
• In-situ Instruments
• Micro Spacecraft Subsystems
• Long Life Electronics
gi _"'*_Small Rover Mission Strate es-_o......o
• Many Landing Options (Propulsive Lander to Ranger-Style
Impact Capsule)
• Use Beacons and INS to Guide Rovers
• Reliability Through Redundancy
• Many Small Rovers Mean Smaller Traverses and Shorter
Required Lifetimes
Many Landings Allow Rovers to be Targeted at Individual
Geologic Units
124
Mission Options
0 4r _ @,
• tw II
• Direct Return from Surface to Earth Entry
- No Sample Transfer After MARV Lift-off
- JPL Design Emphasis
• Mars Orbit Rendezvous
- Sample Transfer MAV to ERV/SRC in Mars Orbit
- Previous JSC Design Emphasis
• Earth Orbit Rendezvous
- Sample Transfer MARV to ERV/SRC in Earth Orbit
- Martin Marietta Corporation Design Emphasis
pl Op o....Micro MAV Sam e Return tions
III
Option
Design
MARV Mass
MARV Delta-V
Sample Mass
Other Element s
Flight System
Mass
Aeroshe11
Diameter
Oeta
Launch
Vehicle
C3
FIlght Systems
per Launch
Mass Mar_fn'
Other Launched
EIer_ents
Direct Return Mars Orbit Rendezvous Earth Orbit Rendezvo'us
Current JPL Old JPLIJSC Current MMC
380 kg
6339 mls
0.5 kg
SRC*Lander÷Aeroshell*
Mlnlrover
(6 elements)
79O kg
3.6 m
46 kg/m2
Atlas IIAS (4)
II.I km3/s2 (2009)
62
0.5
Lander+Aeroshell+
Mlnlrover
(S elements)
230
2.0
46
Delta 7925 (4)
17.7 (2005)
2
85_,
311
7235
0.5
L ande r',Aeroshe I l*
Hlnlro'_er
(S elements)
715
"3.7
41
Atlas IIAS (4)
II.I (2009)
2
33%2O%
CO*Delta (2) R/CO*Atlas (2) CO*Delta (2)
SRC,ERV*Delta (4) SRC*ERV*Delta (3)
125
'llJJll._. IInl
Interactions with SEI
nrl lilt lit ilmltlllll ................... 1 ..i
I
• New Associate Administrator Named
• Huntress/Griffin Agree on Science Objectives
and Priorities for Moon and Mars
• Who Will Implement Moon/Mars Missions?
• Discussions Continue
126


Mars exploration planning

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