mars environmental observer a scout mission concept final report 25 february 2002 m. janssen m....
TRANSCRIPT
Concept HistoryA tale of two instruments
May 2001
MAMBOAtmospheric Sounding/ Chemistry On CNES Premier Orbiter
January 2002 Follow-on
MATMOSMars Solar OccultationFTS
MCSIR sounder
MARCISupporting camera
MEO Proposed
US participation to be proposed as
Mission of Opportunity
MEO Scout Concept Study
MOMESMillimeter Spectrometer(US/DLR)
MATMOS
MARCI
MEO Final
MIROSubmillimeter
spectrometer on Rosetta
(US/DLR/French)
ATMOSSolar occultation
FTS onSpace Shuttle
Heritage
MAMBOMillimeter Spectrometer(French/US/DLR)
MOSESSubmm Spectrometer(US/DLR)
MATMOSPrimary Instrumentfor MARVEL Scout
To be proposed as a Scout Mission
MEO Science Goals and Objectives
1. Seek evidence of extant life by a uniquely broad and sensitive mapping of the global distribution of atmospheric water (I.A.1).
2. Seek evidence of extant life by an ultra-high sensitivity search for trace atmospheric disequilibrium biosignatures (addresses objectives in I.A.2 by remote means).
3. Determine the oxidation state of the lower atmosphere and surface through highly sensitive global measurements of key trace photochemical oxidized species (II.A.6).
4. Characterize the present Mars climate by acquiring a complete global measurement of the physical state of the atmosphere—temperature and winds—over a wide altitude range and under all atmospheric conditions (II.A.1, IV.A.4).
5. Characterize present Mars climate processes through simultaneous measurements of temperature and water (II.A.1, II.A.3, II.A.4, II.A.5).
6. Determine the composition of surface dust by characterizing the mineralogy of atmospheric dust (addresses aspects of I.A.4, I.C.3, II.B.1, III.A.2, III.A.5).
7. Infer the presence of active volcanism through the detection of trace tectonic-formed gas emissions. (III.A.4)
8. Support the preparation for human exploration through a better understanding of upper atmospheric phenomena relevant to aerobraking and aerocapture (IV.A.4).
LIFE
CLIMATE
GEOLOGY
HUMANEXPLORATION
The Mars Environmental Observer (MEO) concept addresses the key Mars Exploration Program Goals of Life, Climate, Geology, and Human Exploration (MEPAG goals I-IV). MEO Objectives are:
Mission and Flight System Architecture
• Payload mass, power, and viewing requirements are accommodated by Lockheed-Martin Odyssey spacecraft.
• Launched by the Delta 2925 for the 2007 opportunity.
• The limb-sounding and solar occultation observing requirements are satisfied by the sun-synchronous polar orbit.
Parameter Value
Launch Date Sep. 2007 Launch Vehicle Delta 2925 Mission duration 40 mo. Trajectory Type Type II Final Orbit 375 km circ. Inclination 92.9 deg. Local Time Node 3:30 pm
Flight System Element Mass, kg Power, W
Spacecraft (Odyssey) 408 (dry) 366 Launch Vehicle (Delta 2925) 779 (wet) Power Source (GaAs arrays, 475 W) 48.7 41.9
System Estimates System Margins
Payload Mass 68 kg Mass 40 %Payload Power 84 W Power 50 %
MEO Budget
Phase
A/BPhase
C/DA/B/C/D
TotalPhase E
ProjectTotal
(FY2002$)
Total Project Costs ($M) $34.3M $261.2M $295.5M $43.8M $339.3M
1.0 Project Management $1.1M $7.5M $8.6M $5.4M $14.0M
1.1 Project Manager & Staff $0.5M $3.2M $3.6M $2.6M $6.2M
1.2 Launch Approval $0.1M $0.1M $0.1M
1.3 Planetary Protection Approval $0.1M $0.1M $0.1M
1.4 Education & Public Outreach $0.1M $0.8M $0.9M $2.5M $3.4M
1.5 Mission Assurance $0.6M $3.3M $3.9M $0.3M $4.2M
2.0 Science Team $0.6M $4.2M $4.8M $5.4M $10.2M
3.0 Mission Design & Project Engineering $0.3M $2.7M $3.0M $3.0M
4.0 Instruments $19.4M $32.9M $52.2M $52.2M
5.0 Spacecraft $5.5M $110.1M $115.6M $115.6M
6.0 Mission Operations & Development $0.6M $5.2M $5.8M $27.3M $33.0M
7.0 Reserves $6.9M $31.9M $38.8M $5.7M $44.5M
8.0 Launch Vehicle $66.8M $66.8M $66.8M
Mission costs with full (MATMOS, MOMES, MARCI) instrument complement
200 MHz
330.6 GHz 345.8 GHz325.2 GHz
12CO
200 MHz 200 MHz
13COH216O
•Advantages over IR: Insensitive to dust presenceDoppler windsHigh H2O sensitivity
•Temperature and Water Vapor will be profiled using limb (shown) and nadir sounding in CO and H2O lines
•Winds will be profiled by limb sounding CO
•Atmospheric chemistry involving H2O2, O3,
HDO, CO, will also be addressed
Atmospheric Sounding with MAMBO
Tangent altitude = 10 km
Spectrometer width
Mars Zonal Wind Simulation for Northern Sosltice
Figure from Conway Leovy (Nature Insight 412, 6843,245-249(2001))-derived from GCM of Haberle et al., J. Geophys. Res. 102, 13301-13311 (1993)
Westward wind, m/sec Eastward wind, m/sec
80S 60 40 20 0 20 40 60 80NLatitude
Retrieval Error, m/s
Alti
tude
, km
Wind Retrieval
Winds along the line of sight will be measured from the Doppler shift of CO lines in the limb-sounding mode. 12CO and 13CO lines allow a wide altitude range to be covered in the atmosphere.
The weighting function for the measurement is narrow in the limb sounding mode and the vertical resolution is set by the beamwidth on the limb (~10 km).
Nominal receiver performance with 10-sec integration time/point allows the determination of wind velocity profiles to better than 10 m/s over a large altitude range.
12CO
13CO
Lines with widths from 1 to 200 MHz are measured at 100 KHz resolution.
cut for weighting function
MAMBO CollaborationWork Agreement
Calibration Load 1st LO
Scan Mechanism
23-cm Off-AxisAntenna
335 GHz Receiver
PowerProcessor
HKP USO
Receiver
Backend
IF ProcessorFrequencySynthesizer
Chirp TransformSpectrometer
PowerProcessor
CP
UE
lect
roni
csIn
terf
ace
S/C
Dat
a B
us
S/C
Pow
er B
usS
igna
l
US
French
German
•MAMBO will be built as an international collaboration.
•A working agreement has been negotiated that minimizes interface complexity and plays to the respective strengths of the partners.
MAMBO US ComponentScience Team
Mike Janssen (lead)
Mark Allen
Gordon Chin
Todd Clancy
Margaret Frerking
Sam Gulkis
Mark Gurwell
Bob Haberle
Mark Richardson
Yuk Yung
JPL
JPL
GSFC
U. Colo
JPL
JPL
Harvard
ARC
Caltech
Caltech
The US MAMBO science team comes from a variety of universities and NASA centers, and brings world-class expertise in all aspects of the investigation: instrumentation, remote sensing, atmospheric dynamics and chemistry
MAMBO US Component Rationale
• Continues international collaboration on heterodyne spectroscopy - this time with French lead
• US responsibility for subsystem complements limited French workforce & experience
• Choice of radiometer backend provides well-defined interface and minimizes risk, travel, ITAR issues, etc.
• Backend experience will be valuable for future instruments• We have found no significant descope options that appear
viable. Possibilities are being explored:– Swedish collaborators assume backend delivery
responsibility, or– French contract to industry for this
US role would be questionable in these cases
MAMBO US Component Budget
02 0403 05 06 07 08 09 10 11
7
6
5
4
3
2
1
0
Schedule of Deliverables
STM
EM
FM
Co
st/F
Y,
M$
FYSchedule Key
Subsystem design and fab at JPL
Delivery to LERMA (French)
Support integration at LERMA
Delivery to CNES (from draft AO)
Budget Key and Summary
Hardware $15.8 MReserves $4.8 M
Science $4.8 M
Total $25.4M
Note: 3%/yr inflation assumed (NASA model)
launch
Phase B