2 Lightsail Objectives Demonstrate viability of Solar Sails Ability to alter orbit energy in positive directionAbility to manage orbital energyAbility to control spacecraft under solar sail powerDevelop and demonstrate key technologiesSail deploymentSail material management during flightDemonstrate pathway to deep space flight with solar sailsLightweight spacecraftCompact and lightweight boomsNavigation technologies
3 Our LightSail Program Km LightSail-3 escapes Earth orbit and flies outside of Earth gravity300 sq meters, 15 kg1,000,00010,0001,000KmLightSail-2 flies further, longer to raise orbit energy100 sq meters, 5 kgLightSail-1 demonstrates controlled flight by light40 sq meters, 5 kg
6 PPOD Launch Interface Poly Picosatellite Orbital Deployer PPOD Ejector – flown > 20 timesArrives fully integratedMass < 10 kg totalVolume envelope: 14x14x40 cmEjection through single voltage signalBolted mechanical interfaceOrbit > 825 km altitude, I > 75 degreesLaunch after January 2011PPOD Ejector (right) with companion satellite (left)PPOD Integrated on 4th stageLouis Friedman, Bill Nye The Science Guy, Jordi Puig-Suari
7 LightSail-1 Concept of Operations Sail uses sun energy to gain orbit energy (up to 4.29x10-5 m/s2 when “on”) week mission life.Drift away from primary vehicle, eject from PPOD, deploy whip antenna, 3 axis stabilization. Solar panel deployment followed by Solar Sail(Sail deployment video stored for downlink)9.6 Kbps 437 MHz downlink FSK. Acceleration data and 2 camera images/daySun Synchronous Orbit 824 km, inclined 98°Command and Control from Cal Poly and Ga. Tech and other ground stations as appropriateDeltaSecondary launch with NPP (June 2011) Vandenberg AFBAmateur Optical trackers to provide position data
9 Orbit Determination: Feeling the Force 05/20/10Orbit Determination: Feeling the ForceLaser RangingInternational Laser Ranging Service measures ranges from ground stations to satellite retro- reflectors to millimeter accuracyStatus: ILRS contactedOptical ObservationsEngage amateur astronomy network to provide optical measurementsRight ascension and declination (angles) determined by reference to known starsObservation times synchronized to international time signalsStatus: In discussions with Gil Moore, Project Starshine Director
10 Orbit Determination (cont.) 05/20/10Orbit Determination (cont.)Radar ObservationsNORAD Two-Line ElementsMean elements based upon Earth true equator, mean equinox of epoch frameFrequency of observation varies based upon orbitAccelerometer MeasurementsOn-board measurements of body-fixed accelerations in 3-axesLumidyne Test Experiment – sensitive to0.1 µg,6 accelerometers, mass <200 gmOrbit Determination SolutionsOrbit solution based upon flight-proven OD methods
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