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LightSail PowerPoint Presentation

LightSail

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LightSail

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  1. LightSail

  2. Lightsail Objectives • Demonstrate viability of Solar Sails • Ability to alter orbit energy in positive direction • Ability to manage orbital energy • Ability to control spacecraft under solar sail power • Develop and demonstrate key technologies • Sail deployment • Sail material management during flight • Demonstrate pathway to deep space flight with solar sails • Lightweight spacecraft • Compact and lightweight booms • Navigation technologies

  3. Our LightSail Program LightSail-3 escapes Earth orbit and flies outside of Earth gravity 300 sq meters, 15 kg 1,000,000 10,000 1,000 Km LightSail-2 flies further, longer to raise orbit energy 100 sq meters, 5 kg LightSail-1demonstrates controlled flight by light 40 sq meters, 5 kg 2010 2013 2015

  4. The LightSail-1 Spacecraft Solar Panels (10) Cameras (2) Sail (4) 3 axis Accelerometer (2) Trac Booms (4) Sun Sensor (4) Momentum Wheel • Avionics Package • C&DH Board • Power Regulation • Transceiver • Payload interface Board Battery Torque Rod (3) Single Axis Gyro (3) Solar Sail Storage (4) Sail Deployment Mechanism 3 axis Accelerometer (2) Whip Antenna

  5. SpacecraftStowed, Deployed

  6. Poly Picosatellite Orbital Deployer • PPOD Ejector – flown > 20 times • Arrives fully integrated • Mass < 10 kg total • Volume envelope: 14x14x40 cm • Ejection through single voltage signal • Bolted mechanical interface • Orbit > 825 km altitude, I > 75 degrees • Launch after January 2011 PPOD Launch Interface PPOD Ejector (right) with companion satellite (left) PPOD Integrated on 4th stage Louis Friedman, Bill Nye The Science Guy, Jordi Puig-Suari

  7. LightSail-1Concept of Operations Sail uses sun energy to gain orbit energy (up to 4.29x10-5 m/s2 when “on”). 3 - 4 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/day Sun Synchronous Orbit 824 km, inclined 98° Command and Control from Cal Poly and Ga. Tech and other ground stations as appropriate Delta 7920-10 Secondary launch with NPP (June 2011) Vandenberg AFB Amateur Optical trackers to provide position data

  8. Project Organization Huntress Cunningham Kerzhanovich Schurmeier Stetson Shirley Yost

  9. Orbit Determination: Feeling the Force • Laser Ranging • International Laser Ranging Service measures ranges from ground stations to satellite retro-reflectors to millimeter accuracy • Status: ILRS contacted • Optical Observations • Engage amateur astronomy network to provide optical measurements • Right ascension and declination (angles) determined by reference to known stars • Observation times synchronized to international time signals • Status: In discussions with Gil Moore, Project Starshine Director

  10. Orbit Determination (cont.) • Radar Observations • NORAD Two-Line Elements • Mean elements based upon Earth true equator, mean equinox of epoch frame • Frequency of observation varies based upon orbit • Accelerometer Measurements • On-board measurements of body-fixed accelerations in 3-axes • Lumidyne Test Experiment – sensitive to 0.1 µg, • 6 accelerometers, mass <200 gm • Orbit Determination Solutions • Orbit solution based upon flight-proven OD methods

  11. LightSail-1: Ready for Launch 2011

  12. Join the team: http://planetary.orghttp://planetary.org/special/fromearth/sail