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

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

3. Propulsion Piggyback to GEO GEO to Apophis Pegasus XLAtlas VDelta IVChemical Propulsion Low Thrust ElectricSolar Sail Nuclear Ion 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

4. Spacecraft Utilities Power SourcesComputation & Data Handling BatteriesRTGs Operating System LinuxSolar Cells & Batteries Fuel Cells WindowsMAC Fully autonomous High-level cmd, autonomous task completion Tele-robotic operation Command and Control Attitude Determination and Control CMGsGyrosStar Trackers RCS ThrustersMomentum Wheels SensorsActuators Solar cells are lighter and are a renewable power source High-level command can keep the data rate lower Star trackers are reliable, small, and lightweight RCS thrusters will be used for station keeping

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

6. Proximity Operations LandStandoff Land, then release seperate transponder Transponder part of spacecraft Use IR/RF imaging to gather seismic information Send equipment down  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 Gossamer netBarbed projectile Robot(s) Equipment contained inside Torpedo Release smaller equipment/robot Release smaller equipment Cloud of cameras and sensors Release sample spikes and sensors  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 Impulsive Disturbances All-in-one Slugs Surface Sampler Separate Sensors ExplosivesTorpedo Ground- Penetrating Radar IR Spectrometer  Ground-penetrating radar will be used to study structural makeup  IR spectrometer will be used to study surface composition Magnetic Sensing

9. Imaging Data VisibleRF/RadarIRLaser Surface Camera(s)Orbiting Camera(s) Included with seismometers Included with impact slugs/samplers Attached to main s/c Separate CamerasCamera “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 m 2 )

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 m 3 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!