NESS Network of Environmental and Seismic Stations NASA Solar System Roadmap Objective 6 Understand the current state and evolution of the ATMOSPHERE, surface, and INTERIOR of Mars Mars Exploration Program Goals Goal 1: Determine if Life ever arose Goal 2: Characterize the Climate Goal 3: Characterize the Geology Goal 4: Prepare for Human Exploration Mission Objective
Determine the state and structure of the Martian interior and atmosphere using a network of stationary landers. Assess geologic hazards and long-term variations in climate/radiation environment in preparation for human exploration NESS Science Goals Current seismic activity How active is Mars? Temporal and spatial distribution of Mars-quakes Planet interior Composition and properties of layers Size and state of core Global climate data
Global coverage from several meteorological stations Concurrent data from 4 locations Radiation & habitability for humans Geology of landing site Panoramic camera for context Change in environment with the weather over the year Science Objectives Measurement Objectives Instrumentation Requirements Data Products Ideally, seismic measurements from 0.1mHz-100Hz and 0.11x10-8 m/s2 peak ground acceleration
1 (3-axis) Very Broad Band Seismometer (0.1mHz10Hz), 1 (3-axis) short period, high frequency microseismometer (10Hz100Hz). 4 Landers, good ground-coupling, 1 Earth year primary mission to maximize probability of Marsquake detection Continuous daytime collection and limited nightime collection of 3component (X,Y,Z) seismograms from 2 seismometers on each lander Atmospheric pressure: 1 mbar-14mbars, temperature: 125-300K,
Wind speed and direction: 0.1-100 m/s, UV: 200-400nm wavelength (1) Phoenix or Mars Polar Lander-Type Meteorology Package including: thermocouple, barometer, anemometer and UV radiation sensor 1 Earth year to track seasonal climatic variation at multiple locations Continuous daytime collection and limited nightime collection of atmospheric measurements
3-color (RGB) stereo images at IFOV: 0.28 mrad at 1.5m to infinity. Subframed opacity measurements with 4th neutral density sun filter. (1) MER-Type Panoramic camera Gimballed mast: 360o azimuth range, +/- 90o elevation range Image data Geophysics & Seismicity 1. Size and frequency of Mars-Quakes 2. Thickness and state of core, mantle, and crust 3. Variations of interior with
latitude and longitude 4. Correlation of seismic activity with major geologic and tectonic features Climate & Meteorology 1. Air pressure, temperature 2. Wind speed and direction 3. UV Radiation Geologic & Geomorphic Context 1. Images of landing site 2. Changes in landscape and atmospheric opacity with seasons Mission Context Viking landed seismometers on Mars Data noisy due to poor ground coupling Determined upper limit on Mars seismicity Meteorological data available from Viking and
Pathfinder Limited concurrent measurements, no global coverage These missions have characterized surface 60 degree latitude, 360 degree longitude distribution Lander elevations are below -0.2km 30N, 135E 20N, 320E 5N, 205E 32S, 70E Instrumentation Each lander will have: Seismometers Two Very Broad Band Seismometers One Broad Band Seismometer One Microseismometer
Barometer Thermometer Anemometer Radiation sensor Panoramic Camera Microphone Mission Design Trades and alternative designs 6 landers versus 4 Level of redundancy Alternative landing sites Entry of carrier Mission Design Launch vehicle (type): Delta 2925H Flight schedule: liftoff
Mars arrival Ls 25 Oct - 14 Nov 2011 12 Sep 2012 170 Flight performance: trajectory C3max payloadmax payloadactual Type 2 10.7 1217.5 kg 983 kg Launch Vehicle Configuration Cruise Configuration Carrier Only
Bus total = 314.5 Spacecraft total = 982.9 Payload total = 612.3 Launch vehicle mass margin = 234.6 EDL Only Bus total = 69.4 Spacecraft total = 152.6 30%+ contingency Entry system diameter = 1.2 m Drag coefficient = 1.55 Ballistic coefficient = 87.9kg/m2 EDL Configuration Lander Configuration
Lander Only Instrument mass + contingency = 5.5 Total bus + contingency = 75.5 Spacecraft total = 81.1 30%+ contingency More time=better defined mass, ex drill/instruments Meteorological Package (from Mars Polar Lander/MPF ) ~855g 855g http://mars.jpl.nasa.gov/MPF/mpf/sci_desc.html#ATMO 360deg. Panorama Camera
sharing the mast with Met package ~300g http://mars.jpl.nasa.gov/MPF/mpf/sci_desc.html#IMP Microphone(50g, 5.2cm5.2cm1.3cm) http://www.lpi.usra.edu/meetings/sixthmars2003/pdf/3078.pdf Seismological Package (from NETLANDER mission by ESA/NASA) 1.75kg VBB Axis (+BRB) 22-5mm,22-5mm,10mm 3 10**-4-10Hz, 10**-2-10Hz JPL Axis Evacuated Sphere
Very Broad Band Seismometer (VBB) ~800g MicroSeismometer(SP/NB) 22-5mm,22-5mm,10mm 3 10-100Hz Resol:~10**-9 m/(s**2)/HZ**-1/2 ~100g http://ganymede.ipgp.jussieu.fr/GB/projects/netlander/sismo/ Data Return Strategy TELECOM Hardware A. Earth to Mars Transit Redundant X-band Trans/Rec 1 medium gain and 2 low gain antennae
B. Entry, Decent, and Landing Electralite Trans/Rec UHF, non-directional monopole Comms with MTO C. Landers Electralite Trans/Rec UHF, non-directional monopole Comms with MTO SDST NESS CARRIER
X-Band Downconverter command data to S/C CDS Processor TWTA telemetry data from S/C CDS X-band MGA Horn HYB Diplexer X-band 35W, RF X-Band
X-Band Exciter Processor command data to S/C CDS telemetry data from S/C CDS WGTS NESS EDL UHF Monopole Ka-Band Exciter UHF
Monopole X-Band Downconverter NESS LANDER Electra Lite D I P L cxs TELECOM Systems Optimal 128 kbps Decrease transmit window, maximize data volume transfer Average ~23 minute link per lander/SOL for 180 Mbits/SOL (avg. transfer capacity 315 Mbits/SOL) Potential increase to 256 kbps with loss of total data
volume received, but decrease in power consumption 11% 14% 58% 38% 17% 18% SOL 1 28% 16% SOL 2 24% 25% 26%
25% Avg 10 SOLS Ground Systems: DSN Deep Space Network: Launch, track TCMs, cruise Lander deployments (biggest cost) 24-hour coverage for 6 weeks Science operations (relay through MTO)
Daily (1-hour) coverage in first month Weekly (1-hour) coverage for duration Cruise-Phase Power A 2 m2 fixed array powers the carrier Supplies power to last lander for telecom, TCMs, etc. Charges lithium-ion lander batteries prior to separation During 32-day separation phase, landers sleep Timer circuit wakes controller just prior to EDL EDL is powered by short-term thermal battery Li-ion battery powers array deployment once landed Lander Array Supplies instruments and controller day and night with 23-minute daily telecom Daily energy usage ~330Wh Landers are identical, so must design for worst-case latitude Array is non-articulating because diffuse light limits benefit of orienting toward sun
Lander Array Power Estimation daily solar incidence per m2 during landed mission Orbital state (LS) Minimum solar flux day Latitude Driving power constraint is minimum solar energy for lander at 30N at Ls = 270 (approx. 6 months after landing) 1900 Wh/m2/sol, 30% power reduction from dust, 27% efficient cells A 1.2 m2 solar array (4 petals) gives a 30% contingency factor
16 Need to keep instruments, parachutes, and propulsion tanks heated Command and Data Handling Requirements for CDS: Data volume storage of 180 Mbits per sol for up to 8 days Data transfer rate to MTO (Mars Telecom Orbiter) at 128 kbps Data transfer rate between instruments and data storage average of 1 kbps (camera burst rate of10 Mbps)
Modified I/O card interface between computer and I/O card Interface to instruments, power, propulsion, ACS (Attitude and Control Subsystem) elements, telecom, carrier separation interface & state of health to carrier Design assumptions of CDS is rad-tolerant Total dose: 20-50 krad SEU (Single Event Upset) threshold LET: 20 MeV/mg/cm2 SEU error rate: 10-7 10-8 bits per day Data storage capability (per lander): 8 Gbits (includes data storage for missed pass) capable of storing up to 40 sols of data 2 landers will be capable of controlling cruise and EDL (Entry, Descent, and Landing) stages of mission Attitude Control -- Carrier
Cruise stage Three-axis attitude control, with control electronics on landers. One lander is used, others are for redundancy. Eight sun sensors (coarse), for safe mode. Two star trackers (6 arcsec accuracy) Two IMUs (inertial measuring unit), drift corrected by star trackers Lander deployment Attitude adjustments for lander deployment accurate to within 0.1. Each lander is spun up to 2 RPM with a spin table, and popped out using springs. Attitude Control -- Landers Three accelerometers to determine: When to deploy parachute When the lander impacts Martian surface Orientation after touchdown ACS Costs Carrier: $10,087,000
Lander: $477,000 Total: $10,564,000 Public Engagement Public Engagement Today, America has a serious shortage of young people entering the fields of mathematics and science. This critical part of NASAs Mission is to inspire the next generation of explorers so that our work can go on. This educational mandate is an imperative. -- NASA Administrator Sean OKeefe Making Mars Real - Constructing a virtual experience as psychologically real as someones backyard Sharing the Adventure - N.E.S.S. - An opportunity for us all to explore. Public Engagement Education Formal-Learning experience inside classroom
Nationwide workshops for educators (Teaching Teachers) Focus on Seismometry and Meteorology mission and science analogs. (K-12, college) Provide mission related materials to educators for the generation of curriculums that follow national guidelines. (Supporting Teachers) Informal-Learning experiences outside the classroom Imagine Workshops Science Seminars Museum Partnerships Youth Groups/Community Groups Guest Observer Programs Visualization/Imaging/Audio An opportunity for us all to explore
Public Engagement Outreach Public Outreach Name the landers/sites participation The Mars Insider Program: Daily Updates from N.E.S.S.(climate,weather, and sound) partnership with weather channels and programs Public presentations (mission scientist and engineers) Dynamic educational Website Make-a-seismometer project (Mars vs. My Backyard) An opportunity for us all to explore Overall Mission Risk Matrix 5 4 3 L i k e
l i h o o d Sys:1 Tel:1 Sys:1 Sys:1 Sys:2 Cos:1, Ins:1, Pow:1, Sci:1, Sys:1 Ins:2, Mis:1,
ACS:3, Sci:2, Sof:1, Str:2, Sys:1 1 2 3 4 5 Impact Major Risks to Mission Activities 26 risks have been identified. 6 of the risks have been determined by many of the systems/disciplines to be critical to the mission. If dont land on crushable material because of uncertain landing terrain, then severe damage to lander and loss of data (Impact 4, Likelihood 3)
Mitigation: Land in locations where terrain is most understood and fewest elevation changes (Impact - 4, Likelihood - 2) Single string redundancy on the lander (Impact - 5, Likelihood 2) Mitigation: Determine which systems have the lowest reliability and either increase this reliability or add a redundant component (Impact 4, Likelihood - 1) Seismometer can not take the large g-loads on landing (Impact 5, Likelihood 3) Mitigation: Perform adequate testing to insure that instrument will withstand landing (Impact - 5, Likelihood - 1) Major Risks to Mission Activities (continued) Failure to establish seismometer contact with the ground (Impact 5, Likelihood - 3) Mitigation: Increase reliability of ground contact mechanism (Impact - 5, Likelihood - 1) Failure to handover CDS control of cruiser (with landers still attached) if primary control system fails (Impact - 5, Likelihood - 3) Mitigation: Build into CDS an automatic handover of control to
another landers processor if the primary CDS fails (Impact - 4, Likelihood - 2) Loss of power because of dust build up on the landers systems, such as solar arrays (Impact - 4, Likelihood 3) Mitigation: More analysis needed to determine how much this will really effect the instruments Project Schedule Project Life Cycle Phase Start Date Pre Phase A Advanced Studies Duration Notes
12+ month instrument tech development Phase A Mission & System Definition 11/14/08 5 months Phase B Preliminary Design 4/16/09 5 months Phase C Design & Build 9/15/10
15 months Descope saved 1 month Phase D Assembly Test & Launch Operations 12/14/10 12 months Descope Saved 1 month Phase E Operations 1/5/12 21 months Organization Chart
NASA Program Office (NPO) Science Team Principal Investigator - Algorithm Development - Science Data Reduction SW - Science Data System - Science Data Processing - Education & Outreach Project Manager JPL Safety & Mission Assurance JPL Mission Design Reqmts. Doc. Flight Sys I/Fs L/V I/Fs - Mission Design Manager JPL -Trajectory and Maneuver Design
- Mission Activity Coordination - Mission and Navigation Plans Advisory Board PI, Chair Dean, PI's U. Dir For PFP, JPL VP, S/C IP Business Manager JPL Project Systems Engineer JPL Instrument Manager JPL - Instrument Design - Instrument Fabrication - Instrument I&T Flight System Manager JPL
- Spacecraft Subcontracting & Fabrication & Integration - Flight System I&T - Operations Support - Planning - Resource Analysis - Schedule Analysis - Earned Value Mgmt - Procurements Mission Operations Manager JPL - Ground System Development - Flight Operations - NASA Ground Station I/F Work Breakdown Structure MARS Lander S.S. 2004-2008 1 WBS Levels 2 Proj Mgmt
GEO Phone Commercial Launch Approval Eng 02.08 Mission Ops Assur 03.08 Inst 4 05.08 - 05.19 MET Pack JPL Launch Syst 08 Launch Services 08.01 MOS V & V 07.06
NOTES 01.RE: Includes all Project reserves as a non-WBS item. Launch System Eng 02.09 Inst 5 05.20 Pan Cam ASU? Project V&V 02.10 Common PS HW 05.31 PS I&T 05.32 05: Use reserved elements 05.08 - 05.19 as needed for additional instruments and 05.21 - 05.29 as needed for additional technology payloads.
05.03 and 06.03: Top level product assurance elements are used for system contracts providing more than one instrument or flight module 06.05: Use the WBS elements in 06.05 as the template for Flight System Modules that are implemented in-house at JPL. 06.06 Use the WBS elements in 06.06 as the minimum template for Flight System Modules that are implemented as System Contracts. Add selected WBS elements from 06.05 as needed for activities performed by JPL. 06.07 - 06.10 : Use reserved elements 06.07 - 06.10 as needed for addional Flight System Modules including Orbiters, Rovers, etc. Cost Estimation Process Cost Chair requests data from all subsystems The data are the parameters for equations in a cost model developed by Team X specialists using historical data These data are run through the cost model and tabulated The process is iterated until all subsystems are satisfied Cost Assumptions
Class B mission Cost Dollars are FY 2004 Inflation rate = 3.1% We assumed a 97% learning curve for the landers and the EDL (Iearning curve equations incorporated into Team X models). Expected Cost $572 M Expected Cost There is no single huge cost driver. The cost is spread roughly evenly among the different subsystems. The upper estimated bound of the cost is $686 and the lower estimated bound is $515. Cost Breakdown
Carrier Instruments Lander EDL ATLO Launch Vehicle Reserves Other Mission Summary First global network of landers on Mars Addresses NASAs exploration goals Lay foundation for forecasting hazards and weather change for human exploration Thank You Team X CoCo Karpinski and Anita Sohus
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