Mission Spacecraft and Operations Overview MAVEN Science Community Workshop December 2, 2012
|
|
|
- Ashlee Cunningham
- 10 years ago
- Views:
Transcription
1 Mars Atmosphere and Volatile EvolutioN (MAVEN) Mission Mission Spacecraft and Operations Overview MAVEN Science Community Workshop December 2, 2012 Chris Waters Spacecraft Design Lead Lockheed Martin MAVEN MOS Technical Review June 5-6,
2 Spacecraft Overview Launch Configuration Monoprop Propulsion System 1640 kg capacity N 2 H 4 tank Regulated during MOI Blowdown during mission 3-Axis Stabilized Platform Reaction wheel control, Nominally sun-pointed during operations RWA Pyramid Articulated Payload Platform +/- 90º elevation travel (inner) +/ º azimuth travel (outer) 2x55 A-hr Li Ion Batteries Fixed Solar Arrays ~1200W power generation, 20º gull wing angle provides aerostability during atmospheric encounters Fixed High Gain Antenna 2m dual reflector X-band downlink rates up to 550 kbps 2
3 Instruments and Payloads (SSL) (GSFC) (LASP) Electra Relay Package (JPL) Bob Ergun, LASP Electra UHF Transceiver and Helix Antenna; Larry Epp, JPL Electra 3
4 Instrument and Payload Locations SWEA SWIA LPW (2) EUV MAG (2) PFDPU SEP (2) Particles and Fields STATIC EUT Helix NGIMS MAVEN MOS Technical Review June 5-6, 2012 Electra Remote Sensing RSDPU IUVS 4
5 Mission Architecture 20-Day Launch Period 18 Nov 2013 (Open) 7 Dec 2013 (Close) LV: Atlas V 401 Ten Month Ballistic Cruise to Mars Type-II Trajectory Early Cruise Late Cruise Northern Approach ~1233 m/s V Orbit Insertion: 22 Sept 2014 (Open) 28 Sept 2014 (Close) Capture Orbit: 35 hour period 380 km P2 75 inclination One Year of Science Operations 5
6 Mission Phases/Timeline Nov Dec Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec HGA UHF Thruster Science Boom Deployments Solar Cal Cal Cal Cals & Science Commissioning Conjunction Launch MOI Early Cruise Late Cruise Transition to Science 2022 Dec Jan Legend: TCM #1 #2 #3 #4 Significant Event Delta-V Maneuver PRM * As required Deep Dips Science Phase #1 #2 #3 #4 #5 Relay Tracks* Extended Mission & Relay Periapse Raise* Flight Software Phase Mission Operations Phase Phase Boundary Definition Prelaunch Launch Launch-1 day (power on) to Transfer to internal power on the pad (not part of Mission Operations Plan) Launch Transfer to internal power to Launch+1 day (approximately, depends on SPK/ephemeris availability) Early Cruise Cruise Operators configure for cruise, and set Mission Phase to Early Cruise (approximately L+1 day) Late Cruise Slew to HGA Earth point (approximately L+90 days) MOI MOI MOI sequence load (approximately MOI-3 days) Science Transition Immediately following confirmation of successful MOI Science Extended (approximately MOI+3 hours) Lost In Time (LIT) N/A Used for default safe mode state if spacecraft cannot autonomously resolve the mission phase Launch window: 11/18-12/7/2013 Ten month ballistic cruise Mars Arrival/MOI: 9/22-28/2014 Five week transition period One Earth-year nominal mission Extended science and/or relay Best estimate supports 29 additional months in the nominal orbit, plus 6 years in a raised orbit (~200 km periapse) 6
7 Cruise Cruise Configuration No science boom deployments until after Mars insertion 7
8 Science Operations Overview Orbit chosen to observe a wide range of geometries Right Ascension and Ascending Node precession rate ~ -0.6 deg/day Argument of Periapsis precession rate ~ -0.8 deg/day Two atmospheric regimes, defined by periapsis density Nominal ( kg/km 3 ) Deep Dips ( kg/km 3 ) 5 one week campaigns Numerous operational constraints to be managed Pointing control mode singularities Sun in FOV constraints Solar eclipses and Earth occultation Instrument high voltage management due to corona effects Limited Earth communications Daily ranging contacts (unattended) Two 5-hr DSN contacts per week for downlink of recorded science and engineering data and for S/C and instrument command uplinks Necessitates significant autonomy in S/C and instrument commanding Continuous DSN coverage for deep dip campaigns Limited tracking data for Navigation Requires autonomous Periapsis Timing Estimator (PTE) to meet orbit timing requirements 8
9 Science Orbit Timing and Geometry S/C generally sun-pointed for the body mounted instruments Orbit broken into 3 segments to accommodate APP pointing Apoapse (IUVS Disk Mapping) Mid-altitude sides -inbound and outbound (STATIC and IUVS) Periapse (NGIMS, STATIC, IUVS sharing) Small set of weekly ops scenarios Balance conflicting instrument requirements Account for S/C and instrument pointing constraints A nominal scenario used for the majority of the science phase Constraint scenarios used to accommodate various spacecraft and instrument constraints S Slew Slew Slew Periapse D E A T Outbound Side Apoapse Slew Inbound Side ALTITUDE (km) TIME (rel to Per.) Actual Periapsis (~ km)
10 Nominal Science Operations 10
11 Science Scenarios Definitions 1 1a 2 2a 2b 3 4 4a 4b 5 SC Apoapse IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan Sun-Nadir Orbit 1 Sides IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan Sun-Nadir Periapse Fly-Y Fly-Y Fly-Y Fly-Y Fly-Z Sun-Velocity Fly-Y Fly-Y Fly-Z Sun-Velocity Sun-Nadir APP@peri Ram-Nadir Ram-Horizontal Ram-Nadir Ram-Nadir Ram-Nadir Ram-Track Ram-Nadir Ram-Nadir Ram-Nadir Ram-Track Sun-Safe Apoapse IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan IUVS Disc Scan Sun-Nadir Orbit 2 Sides STATIC Sun-Nadir STATIC Sun-Nadir STATIC Sun-Nadir STATIC Sun-Nadir STATIC Sun-Nadir STATIC Sun-Nadir IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan IUVS Coronal Scan Sun-Nadir Periapse Sun-Velocity Sun-Velocity Fly-Y Fly-Y Fly-Z Sun-Velocity Fly-Y Fly-Y Fly-Z Sun-Velocity Sun-Nadir APP@peri Ram-Track Ram-Track Ram-Nadir Ram-Horizontal Ram-Nadir Ram-Track Ram-Nadir Ram-Horizontal Ram-Nadir Ram-Track Sun-Safe Represents difference from Nominal Scenario 1 Nominal Scenarios Scenario 1 Primary scenario used for ~70% of mission Scenario 1a Alternate Nominal Scenario to allow STATIC APP Ram-Horizontal (R-H) pointing during Periapsis Scenario 2 Used when attitude singularity precludes use of periapsis sun velocity pointing mode Scenario 2a Alternate Scenario 2 to allow STATIC APP R-H pointing during periapsis Scenario 2b (Fly-Z) Alternate Scenario 2 for use when simultaneous constraints preclude use of Fly-Y and Sun-Velocity attitudes Scenario 3 Used during power constrained periods of mission (precludes Fly-Y attitude during periapsis which takes solar arrays off the sun Scenario 4 Used when attitude singularities preclude use of side segment sun-nadir and periapsis sun-velocity pointing modes Constraint Scenarios Scenario 4a Alternate Scenario 4 to allow STATIC APP R-H pointing during periapsis Scenario 4b (Fly-Z) Alternate Scenario 4 for use when simultaneous constraints preclude use of Fly-Y and Sun-Velocity attitudes Scenario 5 Used during power constrained periods of mission and when attitude singularity prevents use of side segment sunnadir mode Solar Conjunction S/C Sun pointed with APP parked in sunsafe position Communications: 2x per week per DSN visibility constraints Deep Dips: executed with a selected scenario as the baseline, but when scheduled HGA comm is available, all non-periapse segments will be operated in Earth Point 11
12 Science Phase Timeline 12
13 Summary Relatively simple spacecraft design Enabled low cost/risk development Necessitates compromises between science optimization and operational complexity/cost Integrated plan to manage competing science desires Menu of pre-canned operational scenarios Default scenario balances pointing desires across instruments Alternate scenarios to manage S/C and instrument constraints Baseline operations defined for duration of primary mission Five deep dip campaigns One special event per month Magnetometer calibrations, IUVS stellar occultation observations Spacecraft and instrument constraints 13
14 BACK-UP MATERIAL MAVEN MOS Technical Review June 5-6,
15 Science Observation Modes Science Mode ACS Mode Slew Mode APP Mode Attitude IUVS Disc Scan Inertial Hold Semi-major Target IUVS Coronal Scan Inertial Hold Semi-minor Target STATIC Sun-Nadir Sun-Nadir Sun-Nadir Target Sun-Velocity Commanded Position Commanded Position Commanded Position Sun-Velocity Sun-Velocity Target Velocity Track Fly-Y Velocity-Nadir Velocity Target Commanded Position Aligns +Z to Sun, Constrains +X towards orbit semi-major axis; APP: +j aligned with orbit semi-major axis, -k towards orbit normal Aligns +Z to Sun, Constrains +X towards orbit semi-minor axis; APP: +j aligned with orbit semi-minor axis, -k towards orbit normal Aligns +Z to Sun, Constrains +X towards Nadir; APP: inner gimbal = 0, outer = 25 deg Aligns +Z to Sun, Constrains +/-Y towards planet-relative velocity; APP: +i tracks planet-relative velocity Aligns +/-Y to planet-relative velocity, Constrains +X towards nadir; APP: ram-nadir: inner = 0, outer = -65/115 deg to align +i with planet-rel velocity; ram-horizontal: inner = +/-90, outer = -65/115 deg to align +i with planet-rel velocity and +k towards nadir Fly-Z Velocity-Nadir Velocity Target Commanded Position Aligns -Z to planet-relative velocity, Constrains +X towards nadir; APP: ram-nadir: inner = 0, outer = 25 deg to align +i with planet-rel velocity; ram-horizontal not supported Deep Dip Velocity-Nadir Velocity Target Velocity Track Commanded Comm Earth Point Earth Target Position Stellar Occultations Inertial Hold Sun Inertial Commanded Position Damps rates to follow profile of planet-relative velocity vector around periapse; APP: +i tracks planet-relative velocity Aligns +Z to Earth, Constrains -Y towards Sun; APP: inner = 90, outer = -65 deg Aligns +Z to Earth, +X generally towards selected star; APP: IUVS stellar occ FOV pointed at star, APP +i normal to horizon (up) 15
16 Deep-Dip Schedule Deep Dip Number Region Start Date Science Mission Day Periapse Latitude (sun-rel) (deg) Periapse Longitude (sun-rel) (deg) Solar Zenith Angle (deg) Eclipse Duration (min) SPE (deg) 1 Anti-solar 12/26/ Dusk Term 2/6/ Sub-solar 4/10/ Dawn Term 6/26/ South Pole 8/21/ Sun Range (AU) Note: schedule may be adjusted during the science phase based on actual conditions Declination of Periapse in Sun-Mars Frame (deg) 11/4/14 11/18/14 12/3/14 12/18/14 Deep Dip Keep Out Deep Dip Concern Fly-Y Concern Fly-Y Keep Out 1st Year - Nominal 8/1/15 7/2/15 7/17/15 6/16/15 6/1/15 5/17/15 5/2/ /15/ /17/15 1/31/15 2/15/15 3/2/15 3/17/15 4/1/15 1/2/15 1/17/15 0 Deep Dips Dates Eclipsed Start of Science Phase 8/16/15 8/31/15 9/15/15 9/30/15-90 Right Ascension of Periapse in Sun-Mars Frame (deg) 16
17 Science Phase Timeline w/ Inst Constraints 17
The 2013 MAVEN Mission To Mars. Bruce Jakosky MAVEN Principal Investigator University of Colorado
The 2013 MAVEN Mission To Mars Bruce Jakosky MAVEN Principal Investigator University of Colorado Summary of MAVEN Status We ve been developing MAVEN since 2003; now under 3 months to launch! All science
STEREO Guidance & Control
STEREO Guidance & Control J. Courtney Ray [email protected] J. C. Ray 98/11/19 1 STEREO G&C Requirements Baseline System Software Some Analysis J. C. Ray 98/11/19 2 G&C Requirements - Drivers Spacecraft
A Fractionated Space Weather Base at L 5 using CubeSats & Solar Sails
A Fractionated Space Weather Base at L 5 using CubeSats & Solar Sails Paulett C. Liewer, Andrew T. Klesh, Martin W. Lo, Neil Murphy, Robert L. Staehle, Vassilis Angelopoulos, Jet Propulsion Laboratory,
AT&T Global Network Client for Windows Product Support Matrix January 29, 2015
AT&T Global Network Client for Windows Product Support Matrix January 29, 2015 Product Support Matrix Following is the Product Support Matrix for the AT&T Global Network Client. See the AT&T Global Network
MISSION DESIGN AND OPERATIONS CONSIDERATIONS FOR NASA S LUNAR RECONNAISSANCE ORBITER
MISSION DESIGN AND OPERATIONS CONSIDERATIONS FOR NASA S LUNAR RECONNAISSANCE ORBITER Mr. Martin B. Houghton NASA's Goddard Space Flight Center, Greenbelt, Maryland USA [email protected] Mr. Craig
Analysis One Code Desc. Transaction Amount. Fiscal Period
Analysis One Code Desc Transaction Amount Fiscal Period 57.63 Oct-12 12.13 Oct-12-38.90 Oct-12-773.00 Oct-12-800.00 Oct-12-187.00 Oct-12-82.00 Oct-12-82.00 Oct-12-110.00 Oct-12-1115.25 Oct-12-71.00 Oct-12-41.00
JPL ANOMALY ISSUES. Henry B. Garrett Jet Propulsion Laboratory California Institute of Technology Pasadena, CA, 91109
JPL ANOMALY ISSUES Henry B. Garrett Pasadena, CA, 91109 Space Weather Anomaly Concerns for JPL Robotic Mission AGENDA Overview of Space Weather Anomalies on JPL Missions Space Weather Products used by
COMPARISON OF FIXED & VARIABLE RATES (25 YEARS) CHARTERED BANK ADMINISTERED INTEREST RATES - PRIME BUSINESS*
COMPARISON OF FIXED & VARIABLE RATES (25 YEARS) 2 Fixed Rates Variable Rates FIXED RATES OF THE PAST 25 YEARS AVERAGE RESIDENTIAL MORTGAGE LENDING RATE - 5 YEAR* (Per cent) Year Jan Feb Mar Apr May Jun
COMPARISON OF FIXED & VARIABLE RATES (25 YEARS) CHARTERED BANK ADMINISTERED INTEREST RATES - PRIME BUSINESS*
COMPARISON OF FIXED & VARIABLE RATES (25 YEARS) 2 Fixed Rates Variable Rates FIXED RATES OF THE PAST 25 YEARS AVERAGE RESIDENTIAL MORTGAGE LENDING RATE - 5 YEAR* (Per cent) Year Jan Feb Mar Apr May Jun
Penn State University Physics 211 ORBITAL MECHANICS 1
ORBITAL MECHANICS 1 PURPOSE The purpose of this laboratory project is to calculate, verify and then simulate various satellite orbit scenarios for an artificial satellite orbiting the earth. First, there
2. Orbits. FER-Zagreb, Satellite communication systems 2011/12
2. Orbits Topics Orbit types Kepler and Newton laws Coverage area Influence of Earth 1 Orbit types According to inclination angle Equatorial Polar Inclinational orbit According to shape Circular orbit
Dawn - Overview, Science Objectives, Mission Progress. Hap McSween For PI Chris Russell
Dawn - Overview, Science Objectives, Mission Progress Hap McSween For PI Chris Russell Presentation to Decadal Survey Primitive Bodies Panel, Washington, DC, Sep 2009 Spacecraft configuration, assembly
LAUNCH AND COMMISSIONING OF THE LUNAR RECONNAISSANCE ORBITER (LRO)
(Preprint) AAS 10-085 LAUNCH AND COMMISSIONING OF THE LUNAR RECONNAISSANCE ORBITER (LRO) Neerav Shah, * Philip Calhoun *, Joseph Garrick, * Oscar Hsu, * and James Simpson INTRODUCTION The Lunar Reconnaissance
Tropical Horticulture: Lecture 2
Lecture 2 Theory of the Tropics Earth & Solar Geometry, Celestial Mechanics The geometrical relationship between the earth and sun is responsible for the earth s climates. The two principal movements of
Trajectory Design with STK/Astrogator. New Horizons Mission Tutorial
Trajectory Design with STK/Astrogator New Horizons Mission Tutorial STK/Astrogator New Horizons Mission Tutorial Page 2 Mission Overview In this tutorial, we will model a Mission to Pluto. Starting from
AIDA: Asteroid Impact & Deflection Assessment A Joint ESA-NASA Mission. Joint ESA NASA AIDA Team
AIDA: Asteroid Impact & Deflection Assessment A Joint ESA-NASA Mission Joint ESA NASA AIDA Team Chelyabinsk Meteor on 15 February 2013 AIDA Asteroid Deflection Test AIDA international cooperation First
Case 2:08-cv-02463-ABC-E Document 1-4 Filed 04/15/2008 Page 1 of 138. Exhibit 8
Case 2:08-cv-02463-ABC-E Document 1-4 Filed 04/15/2008 Page 1 of 138 Exhibit 8 Case 2:08-cv-02463-ABC-E Document 1-4 Filed 04/15/2008 Page 2 of 138 Domain Name: CELLULARVERISON.COM Updated Date: 12-dec-2007
Chapter 2. Mission Analysis. 2.1 Mission Geometry
Chapter 2 Mission Analysis As noted in Chapter 1, orbital and attitude dynamics must be considered as coupled. That is to say, the orbital motion of a spacecraft affects the attitude motion, and the attitude
Orbit Transfers for Dawn s Vesta Operations: Navigation and Mission Design Experience
Orbit Transfers for Dawn s Vesta Operations: Navigation and Mission Design Experience Dongsuk Han Senior Engineering Staff, Jet Propulsion Laboratory, California Institute of Technology, Mail Stop 264-820,
Lecture L17 - Orbit Transfers and Interplanetary Trajectories
S. Widnall, J. Peraire 16.07 Dynamics Fall 008 Version.0 Lecture L17 - Orbit Transfers and Interplanetary Trajectories In this lecture, we will consider how to transfer from one orbit, to another or to
Quest- 1 Satellite Functional Description
Quest- 1 Satellite Functional Description Overview The Quest- 1 Satellite is based on the CubeSat Standard that measures 10 cm x 10 cm x 10 cm and weighs less than 1.33 kilograms. The Quest- 1 Satellite
Autonomous Operations for Small, Low-Cost Missions: SME, EOR (STEDI), DATA, and Pluto Express OUTLINE. Visions for Future, Low-Cost Missions
Autonomous Operations for Small, Low-Cost Missions: SME, EOR (STEDI), DATA, and Pluto Express Introduction Challenges Solutions Technologies Technology Gaps OUTLINE Visions for Future, Low-Cost Missions
Renewable Energy. Solar Power. Courseware Sample 86352-F0
Renewable Energy Solar Power Courseware Sample 86352-F0 A RENEWABLE ENERGY SOLAR POWER Courseware Sample by the staff of Lab-Volt Ltd. Copyright 2009 Lab-Volt Ltd. All rights reserved. No part of this
Enhanced Vessel Traffic Management System Booking Slots Available and Vessels Booked per Day From 12-JAN-2016 To 30-JUN-2017
From -JAN- To -JUN- -JAN- VIRP Page Period Period Period -JAN- 8 -JAN- 8 9 -JAN- 8 8 -JAN- -JAN- -JAN- 8-JAN- 9-JAN- -JAN- -JAN- -JAN- -JAN- -JAN- -JAN- -JAN- -JAN- 8-JAN- 9-JAN- -JAN- -JAN- -FEB- : days
Analysis on the Long-term Orbital Evolution and Maintenance of KOMPSAT-2
Analysis on the Long-term Orbital Evolution and Maintenance of KOMPSAT-2 Ok-Chul Jung 1 Korea Aerospace Research Institute (KARI), 45 Eoeun-dong, Daejeon, South Korea, 305-333 Jung-Hoon Shin 2 Korea Advanced
Can Hubble be Moved to the International Space Station? 1
Can Hubble be Moved to the International Space Station? 1 On January 16, NASA Administrator Sean O Keefe informed scientists and engineers at the Goddard Space Flight Center (GSFC) that plans to service
Mission Design for the Lunar Reconnaissance Orbiter
AAS 07-057 Mission Design for the Lunar Reconnaissance Orbiter Mark Beckman Goddard Space Flight Center, Code 595 29th ANNUAL AAS GUIDANCE AND CONTROL CONFERENCE February 4-8, 2006 Breckenridge, Colorado
PART III IMPLEMENTATION OF THE MASTER SCIENCE PLAN
MASTER SCIENCE PLAN OVERVIEW DOCUMENTATION (MEX-EST-PL-11912, Draft Issue 1.5) PART III IMPLEMENTATION OF THE MASTER SCIENCE PLAN Planetary Missions Division Research and Scientific Support Department
Celestial Sphere. Celestial Coordinates. Lecture 3: Motions of the Sun and Moon. ecliptic (path of Sun) ecliptic (path of Sun)
Lecture 3: Motions of the and Moon ecliptic (path of ) ecliptic (path of ) The 23.5 degree tilt of Earth s spin axis relative to its orbital axis around the causes the seasons Celestial Sphere Celestial
Astrodynamics (AERO0024)
Astrodynamics (AERO0024) 6. Interplanetary Trajectories Gaëtan Kerschen Space Structures & Systems Lab (S3L) Course Outline THEMATIC UNIT 1: ORBITAL DYNAMICS Lecture 02: The Two-Body Problem Lecture 03:
Yield Reduction due to Shading:
1x4 1x16 10 x CBC Energy A/S x Danfoss Solar Inverters CBC-40W Poly 40 W TLX 1,5k 5 ; 1x11 3x4 0 1,5kW 1536 x CBC Energy A/S 1 x Power-One CBC-40W Poly 40 W TRIO-7,6-TL-OUTD 30 ; 4x14 0 7,6kW Location:
Mars Sample Return Campaign: An Overview. Dr. Firouz Naderi Associate Director NASA s JPL
Mars Sample Return Campaign: An Overview Dr. Firouz Naderi Associate Director NASA s JPL 1 Why Sample Return? Why Now? Compelling Science Informed Landing Site Selection International Interest Good Engineering
102 26-m Antenna Subnet Telecommunications Interfaces
DSMS Telecommunications Link Design Handbook 26-m Antenna Subnet Telecommunications Interfaces Effective November 30, 2000 Document Owner: Approved by: Released by: [Signature on file in TMOD Library]
Coverage Characteristics of Earth Satellites
Coverage Characteristics of Earth Satellites This document describes two MATLAB scripts that can be used to determine coverage characteristics of single satellites, and Walker and user-defined satellite
Satellite technology
Satellite technology Overview What is a satellite? The key elements of orbital position Satellite manufacturers and design The components of a satellite: payload and bus Digital versus analogue How do
RS platforms. Fabio Dell Acqua - Gruppo di Telerilevamento
RS platforms Platform vs. instrument Sensor Platform Instrument The remote sensor can be ideally represented as an instrument carried by a platform Platforms Remote Sensing: Ground-based air-borne space-borne
Chapter 5 Astronomy 110 Motions of the Sun and the Moon 1
Chapter 5 Positions of the Sun and Moon Objects in our Solar System appear to move over the course of weeks to months because they are so close. This motion caused ancient astronomers to use the name planets,
Ashley Institute of Training Schedule of VET Tuition Fees 2015
Ashley Institute of Training Schedule of VET Fees Year of Study Group ID:DECE15G1 Total Course Fees $ 12,000 29-Aug- 17-Oct- 50 14-Sep- 0.167 blended various $2,000 CHC02 Best practice 24-Oct- 12-Dec-
Auburn University s Solar Photovoltaic Array Tilt Angle and Tracking Performance Experiment
Auburn University s Solar Photovoltaic Array Tilt Angle and Tracking Performance Experiment Julie A. Rodiek 1, Steve R. Best 2, and Casey Still 3 Space Research Institute, Auburn University, AL, 36849,
Mars Earth Return Vehicle (MERV) Propulsion Options
46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 25-28 July 2010, Nashville, TN AIAA 2010-6795 Mars Earth Return Vehicle (MERV) Propulsion Options Steven R. Oleson, 1 Melissa L. McGuire, 2
Nanosat 4 Competition
Nanosat 4 Competition NMSUSat2 Team New Mexico State University College of Engineering Presented by Jeremy Bruggemann Topics Competition Overview Mission Overview Design Concept Tests and Analyses Hardware
Solar Power for Outer Planets Study
Solar Power for Outer Planets Study Presentation to Outer Planets Assessment Group November 8, 2007 Scott W. Benson/NASA Glenn Research Center 1 Background & Outline Alan Stern request: a quick look study
USE OF SCILAB FOR SPACE MISSION ANALYSIS AND FLIGHT DYNAMICS ACTIVITIES
USE OF SCILAB FOR SPACE MISSION ANALYSIS AND FLIGHT DYNAMICS ACTIVITIES Thierry Martin CNES Scilabtec 09 Use of Scilab for space mission analysis Page 1 Use of Scilab in CNES Scilab is now widely used
Frequencies for Mars Local High-Rate Links
IPN Progress Report 42-153 May 15, 2003 Frequencies for Mars Local High-Rate Links D. Hansen, 1 M. Sue, 1 T. Peng, 2 and F. Manshadi 2 This article considers the options for frequency choice for high-data-rate
Pioneer Venus: Mission Characterization. Dr. Andrew Ketsdever Lesson 2 AME 5595
Pioneer Venus: Mission Characterization Dr. Andrew Ketsdever Lesson 2 AME 5595 Background Pioneer Venus evolved from recommendations from the Space Science Board of the National Academy of Sciences Need
Overview of NASA s Laser Communications Relay Demonstration
Overview of NASA s Laser Communications Relay Demonstration April 2012 Bernard Edwards NASA Goddard Space Flight Center (301) 286-8926 [email protected] 1 LCRD Demonstration Scenarios Mission
The NASA Global Differential GPS System (GDGPS) and The TDRSS Augmentation Service for Satellites (TASS)
The Global Differential GPS System (GDGPS) and The TDRSS Augmentation Service for Satellites (TASS) Yoaz Bar-Sever, Larry Young, Frank Stocklin, Paul Heffernan and John Rush s Global Differential GPS System
CHAPTER 2 ORBITAL DYNAMICS
14 CHAPTER 2 ORBITAL DYNAMICS 2.1 INTRODUCTION This chapter presents definitions of coordinate systems that are used in the satellite, brief description about satellite equations of motion and relative
Douglas Adams The Hitchhikers Guide to the Galaxy
There is a theory which states that if ever anybody discovers exactly what the Universe is for and why it is here, it will instantly disappear and be replaced by something even more bizarre and inexplicable.
Resonant Orbital Dynamics in Extrasolar Planetary Systems and the Pluto Satellite System. Man Hoi Lee (UCSB)
Resonant Orbital Dynamics in Extrasolar Planetary Systems and the Pluto Satellite System Man Hoi Lee (UCSB) Introduction: Extrasolar Planetary Systems Extrasolar planet searches have yielded ~ 150 planetary
Orbital Mechanics and Space Geometry
Orbital Mechanics and Space Geometry AERO4701 Space Engineering 3 Week 2 Overview First Hour Co-ordinate Systems and Frames of Reference (Review) Kepler s equations, Orbital Elements Second Hour Orbit
Satellite Mission Analysis
CARLETON UNIVERSITY SPACECRAFT DESIGN PROJECT 2004 FINAL DESIGN REPORT Satellite Mission Analysis FDR Reference Code: FDR-SAT-2004-3.2.A Team/Group: Satellite Mission Analysis Date of Submission: April
The Four Seasons. A Warm Up Exercise. A Warm Up Exercise. A Warm Up Exercise. The Moon s Phases
The Four Seasons A Warm Up Exercise What fraction of the Moon s surface is illuminated by the Sun (except during a lunar eclipse)? a) Between zero and one-half b) The whole surface c) Always half d) Depends
SAC-C MISSION 2.0 CONAE INSTRUMENTS DESCRIPTION 2.1 MMRS
SAC-C MISSION Carlos Alonso Carlos Hofmann SAC-C Program Manager SAC-C System Engineer CONAE (Comisión Nacional de Actividades Espaciales), Paseo Colón 751 (1063) Buenos Aires Argentina 1 Abstract. SAC-C
PHSC 3033: Meteorology Seasons
PHSC 3033: Meteorology Seasons Changing Aspect Angle Direct Sunlight is more intense and concentrated. Solar Incidence Angle is Latitude and Time/Date Dependent Daily and Seasonal Variation Zenith There
Where On Earth Will Three Different Satellites Provide Simultaneous Coverage?
Where On Earth Will Three Different Satellites Provide Simultaneous Coverage? In this exercise you will use STK/Coverage to model and analyze the quality and quantity of coverage provided by the Earth
Performances Optimization of Remote Sensing Satellite Constellations: a Heuristic Method
Performances Optimization of Remote Sensing Satellite Constellations: a Heuristic Method Sergio De Florio Microwaves and Radar Institute, DLR Oberpfaffenhofen Münchner Str. 20, 82234 Wessling, Germany
Robotic Pre-Cursor Contribution to Human NEA Mission. H. Kuninaka JSPEC/JAXA
Robotic Pre-Cursor Contribution to Human NEA Mission H. Kuninaka JSPEC/JAXA Asteroid Explorer Hayabusa Dimensions 1.0m x 1.6m x 1.1m Weight : 380kg(Dry) Chemical Fuel 70kg Xe Propellant 60kg Total 510kg
SCOOP: The Future of NDBC Real-Time Data Collection and Reporting
SCOOP: The Future of NDBC Real-Time Data Collection and Reporting National Data Buoy Center Stennis Space Center, MS James Elliott INMARTECH 2014, Corvallis Oregon Self-Contained Ocean Observations Payload
Automated Spacecraft Scheduling The ASTER Example
Automated Spacecraft Scheduling The ASTER Example Ron Cohen [email protected] Ground System Architectures Workshop 2002 Jet Propulsion Laboratory The Concept Scheduling by software instead of
Interaction of Energy and Matter Gravity Measurement: Using Doppler Shifts to Measure Mass Concentration TEACHER GUIDE
Interaction of Energy and Matter Gravity Measurement: Using Doppler Shifts to Measure Mass Concentration TEACHER GUIDE EMR and the Dawn Mission Electromagnetic radiation (EMR) will play a major role in
Coordinate Systems. Orbits and Rotation
Coordinate Systems Orbits and Rotation Earth orbit. The earth s orbit around the sun is nearly circular but not quite. It s actually an ellipse whose average distance from the sun is one AU (150 million
HybridSail. Hybrid Solar Sails for Active Debris Removal Final Report
HybridSail Hybrid Solar Sails for Active Debris Removal Final Report Authors: Lourens Visagie (1), Theodoros Theodorou (1) Affiliation: 1. Surrey Space Centre - University of Surrey ACT Researchers: Leopold
DSL Mission Concept at Lunar Orbit
DSL Mission Concept at Lunar Orbit Jingye Yan Na9onal Space Science Center (NSSC) Chinese Academy of Sciences (CAS) 2015-02- 02, ASTRON, The Netherland 1 Payload onboard single nano- sat Element antenna
The National Strategy, Current Activities for Space Technology Development and Application
14-18 November 2011, Putrajaya, Malaysia The National Strategy, Current Activities for Space Technology Development and Application Lai Anh Khoi Space Technology Institute, VAST, Vietnam Bief History Space
Consumer ID Theft Total Costs
Billions Consumer and Business Identity Theft Statistics Business identity (ID) theft is a growing crime and is a growing concern for state filing offices. Similar to consumer ID theft, after initially
Orientation to the Sky: Apparent Motions
Chapter 2 Orientation to the Sky: Apparent Motions 2.1 Purpose The main goal of this lab is for you to gain an understanding of how the sky changes during the night and over the course of a year. We will
'l'ehisat. A IfICROSATBLLI'l'E SYS'l'EH FOR AlJ'rONOHOUS ENVIRONIfElI'.rAL IfONI'l'ORING SERVICR
'l'ehsat A fcrosatbll'l'e SYS'l'EH FOR AlJ'rONOHOUS ENVRONfEl'.rAL fon'l'orng SERVCR Brunella Paves! (1), Giuseppe Rondinelli (1) Nikolaos Balteas (2) (1) f!lesp1zo S.p.a. - Via 'l'iburtlna 965-00156 ROJa,
SATELLITE ORBIT DETERMINATION AND ANALYSIS (S.O.D.A) A VISUAL TOOL OF SATELLITE ORBIT FOR SPACE ENGINEERING EDUCATION & RESEARCH
SATELLITE ORBIT DETERMINATION AND ANALYSIS (S.O.D.A) A VISUAL TOOL OF SATELLITE ORBIT FOR SPACE ENGINEERING EDUCATION & RESEARCH 1 Muhammad Shamsul Kamal Adnan, 2 Md. Azlin Md. Said, 3 M. Helmi Othman,
PART II OVERVIEW OF MARS EXPRESS SCIENCE OPERATIONS
MASTER SCIENCE PLAN OVERVIEW DOCUMENTATION (MEX-EST-PL-11912, Draft Issue 1.5) PART II OVERVIEW OF MARS EXPRESS SCIENCE OPERATIONS Planetary Missions Division Research and Scientific Support Department
Dancing in the Dark: How GNSS Satellites Cross the Earth s Shadow
Dancing in the Dark: How GNSS Satellites Cross the Earth s Shadow F. Dilssner, T. Springer, G. Gienger, R. Zandbergen European Space Operations Centre (ESOC), Darmstadt 24 January 2011 Technische Universität
Lessons Learned during the Refurbishment and Testing of an Observatory after Longterm
Lessons Learned during the Refurbishment and Testing of an Observatory after Longterm Storage GSFC 2015 John Hawk, Sharon Peabody, and Richard Stavely NASA Goddard Space Flight Center Background The Triana
CAFIS REPORT 2015.10
CAFIS REPORT 2015.10 INDEX Message CAFIS Inbound 03-06 07-08 CAFIS Arch 09-10 CAFIS Brain 11-12 CAFIS Global 13-14 What We Do 15-16 About CAFIS 17-18 Services for Member Stores 19-34 Services for Card
Roles: Scrum Master & Project Manager
Roles: Scrum Master & Project Manager Scrum Master: Facilitate collaborative meetings Track team performance Remove impediments (Risk, Issue) Validate team alignment to Agile framework and scope Drive
The Spacewire interface for HERSCHEL/SCORE suborbital mission
The Spacewire interface for HERSCHEL/SCORE suborbital mission International Spacewire Conference, Dundee, 19 Sept. 2007 Session: SpaceWire missions and applications Pancrazzi Maurizio e Scienza dello Spazio
TOPIC: CLOUD CLASSIFICATION
INDIAN INSTITUTE OF TECHNOLOGY, DELHI DEPARTMENT OF ATMOSPHERIC SCIENCE ASL720: Satellite Meteorology and Remote Sensing TERM PAPER TOPIC: CLOUD CLASSIFICATION Group Members: Anil Kumar (2010ME10649) Mayank
ShindaiSat : A Visible Light Communication Experimental Micro-Satellite
ShindaiSat : A Visible Light Communication Experimental Micro-Satellite Atsushi Nakajima, Nobutada Sako, Masato Kamemura, Yuuki Wakayama, Arata Fukuzawa, Hironori Sugiyama and Naoki Okada Graduate School
CENTERPOINT ENERGY TEXARKANA SERVICE AREA GAS SUPPLY RATE (GSR) JULY 2015. Small Commercial Service (SCS-1) GSR
JULY 2015 Area (RS-1) GSR GSR (LCS-1) Texarkana Incorporated July-15 $0.50690/Ccf $0.45450/Ccf $0.00000/Ccf $2.85090/MMBtu $17.52070/MMBtu Texarkana Unincorporated July-15 $0.56370/Ccf $0.26110/Ccf $1.66900/Ccf
Iodine RF Ion Thruster Development Busek Co. Inc. Vlad Hruby PhD, President
Iodine RF Ion Thruster Development Busek Co. Inc. Vlad Hruby PhD, President Mike Tsay PhD busek.com 2015 Busek Co. Inc. All Rights Reserved. Iodine RF Ion Thruster Development Status Briefing NASA NRA
THE MESSENGER SPACECRAFT GUIDANCE AND CONTROL SYSTEM *
THE MESSENGER SPACECRAFT GUIDANCE AND CONTROL SYSTEM * ABSTRACT Robin M. Vaughan, Daniel J. O Shaughnessy, Hongxing S. Shapiro, and David R. Haley The Johns Hopkins University Applied Physics Laboratory
FREE ONLINE APPLICATION OF CALCULATION
HELPS YOU TO CALCULATE, OF RAPID AND EASY WAY, AN ISOLATED PHOTOVOLTAIC SOLAR, LOCATED IN ANY PART OF PLANET. FREE ONLINE APPLICATION OF CALCULATION EXAMPLE 4: CALCULATION OF SOLAR PHOTOVOLTAIC INSTALLATION
Bi-Directional DGPS for Range Safety Applications
Bi-Directional DGPS for Range Safety Applications Ranjeet Shetty 234-A, Avionics Engineering Center, Russ College of Engineering and Technology, Ohio University Advisor: Dr. Chris Bartone Outline Background
GNSS satellite attitude characteristics during eclipse season
GNSS satellite attitude characteristics during eclipse season F. Dilssner 1, T. Springer 1, J. Weiss 2, G. Gienger 1, W. Enderle 1 1 ESA/ESOC, Darmstadt, Germany 2 JPL, Pasadena, USA July 26, 2012 IGS
Computing & Telecommunications Services Monthly Report March 2015
March 215 Monthly Report Computing & Telecommunications Services Monthly Report March 215 CaTS Help Desk (937) 775-4827 1-888-775-4827 25 Library Annex [email protected] www.wright.edu/cats/ Last Modified
Mars Atmosphere and Volatile EvolutioN (MAVEN) Mission
Mars Atmosphere and Volatile EvolutioN (MAVEN) Mission MAVEN Science Community Workshop December 2, 2012 Particles and Fields Package Solar Energetic Particle Instrument (SEP) Davin Larson and the SEP
THE MASTER PLAN CAMPAIGN. Workshop RPAS (WS 03) 22 January 2015
THE MASTER PLAN CAMPAIGN Workshop RPAS (WS 03) 22 January 2015 Back-up The objectives of the campaign 2 Campaign objectives Following the endorsement from the PC, SPP and ADB of the PC Tiger Team recommendations
On May 27, 2010, the U.S. Air. Satellite. Antenna Phase Center and Attitude Modeling
GPS IIF-1 Satellite Antenna Phase Center and Attitude Modeling Florian Dilssner Logica/European Space Agency Calculating the distances between satellites and user equipment is a basic operation for GNSS
Astromechanics Two-Body Problem (Cont)
5. Orbit Characteristics Astromechanics Two-Body Problem (Cont) We have shown that the in the two-body problem, the orbit of the satellite about the primary (or vice-versa) is a conic section, with the
Section 2. Satellite Orbits
Section 2. Satellite Orbits References Kidder and Vonder Haar: chapter 2 Stephens: chapter 1, pp. 25-30 Rees: chapter 9, pp. 174-192 In order to understand satellites and the remote sounding data obtained
APOPHIS 2029 A UNIQUE MISSION OPPORTUNITY
APOPHIS 2029 A UNIQUE MISSION OPPORTUNITY Jean-Yves Prado CNES Toulouse - France Presentation Outline APOPHIS reminder The April 2029 flyby Mission objectives Sequence of events Launch Orbit transfer Relative