Mars 2020 Entry, Descent, And Landing Update
Mars 2020 Entry, Descent, andLanding Update15th International Planetary ProbeWorkshopBoulder, COJune 2018Erisa Stilley, Paul Brugarolas,Allen Chen, Richard Otero,Aaron Stehura, Gregorio Villar 2018. California Institute of California. Government sponsorship acknowledged.Mars 2020 Project 1
Mars 2020 Mission Overview2018 IPPW 15LAUNCHCRUISE/APPROACHENTRY, DESCENT & LANDINGSURFACE MISSION Atlas V 541 Rocket 7 month cruise Prime mission of 1.5 Mars years Period: Jul-Aug 2020 Arrive Feb 2021 MSL EDL System: guided entry,powered descent, and sky crane Augmented by range trigger: 16 x 14km landing ellipse Seeking signs of past life Augmented by TRN: enables safelanding at a greater number ofscientifically valuable sites Prepare for human exploration of Mars 20 km traverse distance capability Returnable cache of samples Access to landing sites 30 latitude, - 0.5 km elevation Deliver a 1050 kg roverMars 2020 Project 2
Mars 2020 Objectives
EDL Timeline2018 IPPW 15Cruise Stage SeparationTime: E – 10 minCBMDSeparationSky Crane DetailsRoverSeparationAlt: 21.3 mVel: 0.75 m/sEntry InterfaceTime: E 0 minFlyawayMobilityDeployAlt: 20.7 - 14.5 mVel: 0.75 m/sPeak HeatingTime: E 70 sTouchdownTime: E 430 sVel: 0.75 m/s verticalPeak DecelerationTime: E 80 sHypersonicAero-maneuveringMEDLI2Parachute DeployTime: E 260 sAlt: 8 – 13 km MOLAVel: 440 m/sRange TriggerHeatshieldSeparationTime: E 280 sAlt: 6–10 km MOLAVel: 160 m/sBackshellSeparationand Safe Target SelectionTime: E 380 sAltitude: 2 kmVel: 80 – 110 m/sRadarGroundSolutionandLVS SolutionPowered DescentTRNEDL CamerasSky CraneFlyawayMars 2020 Project 4
Landing Site Selection2018 IPPW 15n A fourth candidate site, Midway, has been added for evaluation by the engineeringand science teamsn Terrain and Atmosphere reviews completed in the past year; several improvements torock identification have been incorporatedn EDL is currently evaluating landing site safety in support of the 4th landing siteworkshop this Fall, with final site selection expected in early 2019 by NASA HQn All sites are expected to have acceptable riskMidwayMars 2020 Project 5
TRN Development Status2018 IPPW 15n Terrain Relative Navigation (TRN), Vision ComputeElement (VCE), and VCE SW design reviews arecompleteVCE EDU4 LCAM EM1n Design has matured and hardware and softwaredeliveries are in progresso VCE engineering dev units (EDU) delivered; EM and FMbuilds are in progress; LVS Camera (LCAM) EM1 deliveredo Box-level software design is ongoing and expected to bepart of 2019 field testo System-level software design is finalized and being testedn Monte Carlo simulations have exercised the TRNcapability using a Safe Targets Map (STM) andgenerated successful landing metrics based on thehazard mapn Full SW testing and delivery to ATLO happening Fall2018VCE EDU4 FPGA CardLCAM EM1calibration imageo ATLO testing in Jan 2019o Field testing in Feb 2019Jezero site: hazard map vs. STMJezero Mosaic,example of onboardappearance map forTRNMars 2020 Project 6
EDL Camera Overview2018 IPPW 15ParachuteSupportStructureUp-LookCameras(x3, 1.3 MPColor CMOS)DescentStageDown LookCamera(3.2 MP .3 MP ColorCMOS)OmnidirectionalMicrophoneCapsule(1.3 MP ColorCMOS)Mars 2020 Project 7
EDL Camera Overview2018 IPPW s(x3, 1.3 MPColor CMOS)DescentStageDown LookCamera(3.2 MP ColorCMOS)DescentStageUSB3 Hub &DataStorage UnitRoverUp-LookCameraRoverDown-LookCamera(1.3 MP ColorCMOS)OmnidirectionalMicrophoneCapsuleEDL Camera DataStorage Unit(Rover Internal)(1.3 MP ColorCMOS)Mars 2020 Project 8
Mars Helicopter2018 IPPW 15n Mars Helicopter is now officially part of the Mars 2020 Missionn Overview:o Mass: 1.8kgo Approx. 1.1m x 0.25m x 0.02mo Dual counter-rotating blades (L 1.21m)o Solar powered with lithium-ion batteryo B&W camera for nav; color camera for terrainn Concept of Operationso The helicopter will be “dropped off” at arelatively flat location.o 5 tech demo flights in 30-sol period of 30120 sec eachn EDL Impact: due to its location, thehelicopter increases the risk due to arock strike by 0.5-1%Credits: NASA/JPL-CaltechMars 2020 Project 9
ATLO Hardware Status2018 IPPW 15n Major hardware integration on the cruise and descent stage is complete(thermal, propulsion) or in progress (e.g. GNC sensor integration)n First power on occurred in Apriln System testing begins February 2019Descent StageCS Propulsion Tanks and Power DistModule InstalledCredits: NASA/JPL-CaltechMars 2020 Project 10
Supersonic Parachute Testing Status2018 IPPW 15n Mars 2020 is doing supersonic parachute testing as a risk reduction activityfor canopy stresses during the inflation processn One flight test each of the MSL design and a strengthened Mars 2020design have been successfully completedo 2nd flight was highest load ever survived by a supersonic parachute! (56 klbf/ 249 kN)n A third flight test, 2nd of the strengthened design, at a margined loadcondition is planned for late July 2018; target load will be even higher thanthe prior flightMars 2020 Project 11
Issues in Work (1/2)2018 IPPW 15n Parachute Deployment Snatch Forces Disturbance on Descent IMUMortar Reaction Start 799.217o Recent analysis of the MSL flight datarevealed an excitation that causedunexpected large rates (120 /s)Snatch Events 799.27o The timing suggests it is likely due toa snatch event associated with themortar sabot and/or the confluencefitting (hardware connecting the triplebridle to the parachute single riser)o There are concerns this excitation could cause temporary IMU saturation and/or navigationerrors which can lead to large EDL attitude errors and potentially loss of missiono Mitigationsl Mechanical design changes are being considered to reduce the magnitude or coupling ofthe disturbance; these include softer triple bridles, a lighter confluence fitting, adding massto the descent stage panel where the IMU is mounted, etc.l The primary GNC mitigation being considered is enabling a low pass filter in the IMU;there is also the potential to use the Rover IMU (lower quality data, less susceptible tosaturation) as a sanity check on the descent IMU.Mars 2020 Project 12
Issues in Work (2/2)2018 IPPW 15n Heatshield Static Test Failureo The flight heatshield developed a circumferential crack during statictesting in Marcho Root cause is still under investigation while Project is moving to build areplacement heatshieldo Adequate schedule margin exists to build the new heatshield and stillmeet the Mars 2020 launch opportunityMars 2020 Project 13
Summary2018 IPPW 15n Mars 2020 Project development is making good progress andcontinues to be on track for the 2020 launch opportunityn Landing Site Selection efforts will likely wrap up this year, leading to afinal site selection by NASA HQ in early 2019n The EDL team continues to work technical issues while supportinghardware deliveries, FSW testing, and the start of activities in ATLOMars 2020 Project 14
to the descent stage panel where the IMU is mounted, etc. lThe primary GNC mitigation being considered is enabling a low pass filter in the IMU; there is also the potential to use the Rover IMU (lower quality data, less susceptible to saturation) as a sanity check on the descent IMU. Issues in Work (1/2) Mortar Reaction Start 799.217
Venus and Mars Chapter 22 I. Venus A. The Rotation of Venus B. The Atmosphere of Venus C. The Venusian Greenhouse D. The Surface of Venus E. Volcanism on Venus F. A History of Venus II. Mars A. The Canals of Mars B. The Atmosphere of Mars C. The Geology of Mars D. Hidden Water on Mars E. A History of Mars
August 31, 2017 Page 5 Step 4: Launch MARS To launch the MARS software application, click Start All Programs MARS MARS or double- click the MARS desktop shortcut (Figure 1) that was created during installation. Figure 1: MARS desktop icon If the following message (Figure 2) appears upon startup, please use the link to contact MARS Sales,
and the hubness phenomenon (Section 2.2), which, as we will de-monstrate later, has a significant impact on NN-Descent. 2.1 NN-Descent The main purpose of the NN-Descent algorithm is to create a good approximation of the true K-NNG, and to create it as fast as possi-ble. The basic assumption made by NN-Descent can be summarized
Mirror descent 5-2 Convex and Lipschitz problems minimizex f (x) subject to x ! C f is convex andLf-Lipschitz continuous Mirror descent 5-35 Outline Mirror descent Bregman divergence Alternative forms of mirror descent Convergence analysis f (xt) !! f (xt),x " xt " " 1 2!t #x " xt#2
Method of Gradient Descent The gradient points directly uphill, and the negative gradient points directly downhill Thus we can decrease f by moving in the direction of the negative gradient This is known as the method of steepest descent or gradient descent Steepest descent proposes a new point
Venus? Mars is too cold. Why? – What happened to Mars’ greenhouse? – What happened to Mars’ atmosphere – Mars Odyssey/ Search for water Homework 4 is due 6am on Tues, 20 Feb. Goldilocks #1 Venus is too hot; Mars is too cold. Why is the earth just right, not too cold and not too hot?
Mars 2020 Project Mars 2020 Mission. April 5, 2018. MEPAG Meeting. CL 18-1654 . Ken Farley . Project Scientist (Caltech) The technical data in this document are controlled under the U.S. Export Regulations. Release to foreign persons may require an export authorization. PreDecisional: For Planning and Discussion Purposes Only.- Mars 2020 Project. 2016 KDP-C SMD Program Management Council. Mars .
27 Science Zoology Dr. O. P. Sharma Amrita Mallick Full Time 18/2009 11.06.2009 Evaluation of Genotxic Effects & Changes in Protein Profile in Muscle Tissue of Freshwater Fish Channa Punctatus Exposed to Herbicides Page 3 of 10. Sl. No. Faculty Department Name of the supervisor Name of the Ph.D. Scholar with Aadhar Number/Photo ID Mode of Ph.D. (Full Time/Part-Time) Registration Number Date of .
