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PTAR Presentation

PTAR Presentation. Team Cronus. Jonathan DeLaRosa, Jessica Nelson, Ivan Morin, JJ Rodenburg, & Tim Stelly. Introduction. Launch Date May 20, 2013 Get to Apophis by 2014 Orbit Apophis Collect science data Send data back to Earth to study. Atlas V has a 91% launch success rate

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PTAR Presentation

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  1. PTAR Presentation Team Cronus Jonathan DeLaRosa, Jessica Nelson, Ivan Morin, JJ Rodenburg, & Tim Stelly

  2. Introduction • LaunchDate • May 20, 2013 • Get to Apophis by 2014 • Orbit Apophis • Collect science data • Send data back to Earth to study

  3. Atlas V has a 91% launch success rate Atlas V can take a satellite to LEO, GTO, or GEO Chemical propulsion is a proven method and can get to Apophis faster Propulsion Piggyback to GEO GEO to Apophis Pegasus XL Atlas V Delta IV Low Thrust Nuclear Chemical Propulsion Electric Ion Solar Sail

  4. Star trackers are reliable, small, and lightweight RCS thrusters will be used for station keeping Solar cells are lighter and are a renewable power source High-level command can keep the data rate lower Spacecraft Utilities Power Sources Command and Control Attitude Determination and Control Computation & Data Handling Operating System Batteries Fuel Cells Solar Cells & Batteries RTGs Linux Windows MAC Fully autonomous High-level cmd, autonomous task completion Tele-robotic operation Sensors Actuators Star Trackers CMGs Momentum Wheels Gyros RCS Thrusters

  5. Communication Data Rates Architecture High data rate, high level of information/control Low data rate, low level of information/control Always in communication Communicate when in range Cache/data dumps Links/Relays High power, direct link • Variable data rates can be used to stay in continuous contact, even at long ranges

  6. Proximity Operations Land Standoff Transponder part of spacecraft Land, then release seperate transponder Send equipment down Use IR/RF imaging to gather seismic information • Standoff is a lower-risk method to acquire the necessary scientific data • Spacecraft will monitor changes in the orbit of Apophis due to presence of an orbiting body

  7. Secondary Payload - Lander Barbed projectile Torpedo Robot(s) Release smaller equipment Gossamer net Cloud of cameras and sensors Release sample spikes and sensors Equipment contained inside Release smaller equipment/robot • Torpedo better suited for unknown composition • Equipment will take soil sample, provide secondary RF imaging, and induce a disturbance to study damping and response • Will relay data back to standoff spacecraft • Battery-powered communications and data handling

  8. Seismic Data Collection Remote Sensing Implanted Ground-Penetrating Radar Magnetic Sensing IR Spectrometer Separate Sensors Surface Sampler All-in-one Impulsive Disturbances • Ground-penetrating radar will be used to study structural makeup • IR spectrometer will be used to study surface composition Slugs Explosives Torpedo

  9. Imaging Data Laser Visible RF/Radar IR Surface Camera(s) Orbiting Camera(s) Included with seismometers Included with impact slugs/samplers Attached to main s/c Separate Cameras Camera “Cloud” • Visible imaging will provide tangible data for study and publicity • Star tracker can be used for ADC and visible imaging • Ground-penetrating radar will be used to study structural makeup • IR spectrometer will be used to study surface composition

  10. Mission Design • Piggyback to GEO • Chemical Propulsion to Apophis • Orbiting Apophis while accomplishing science tasks • Using satellite as transponder • IR spectrometer for composition • Camera imaging

  11. Elements • Launch • Atlas V • Propulsion • Chemical propulsion • Liquid propellant • Power • Solar Cells & Batteries • BTJ Triple-Junction High Efficiency Solar Cells for Space Applications (1000 W, 2.5 m2)

  12. Elements • Attitude Determination & Control • Star Trackers and Reaction Control System (RCS) Thrusters • Linux OS Computer • Data Acquisition Payload • Imaging Camera • IR Spectrometer • Ground-Penetrating Radar • Landing Torpedo • Communication System/ Transponder Goodrich Star Tracker IR Spectrometer

  13. Layout • Structure • Aluminum 6061-T6 • Specifications • Power= 1 kW • Volume=1 m3 • Mass= 300 kg

  14. Advantages of Our Design • High TRL for majority of components • Doubling the communications system as a transponder • Using the RCS for station keeping around Apophis instead of using main thruster • Doing imaging and composition of Apophis from orbit with cameras and spectrometer • Will study effect of orbiting masses on the orbit of Apophis

  15. Questions? Thanks!

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