1. AAE 450 – Spacecraft Design 1 Attitude Determination Methods Brienne Bogenberger January 18, 2004 Dynamics & Control Group Lead, Attitude Determination & Control (ADCS)

2. AAE 450 – Spacecraft Design  Star Tracker  Effective attitude determination for spinning spacecraft  Flight-proven hardware  Sun Sensor – DSS2 Digital Sun Sensor  Optic head mass: ~.35 kg  Optic head size size: 86x50x30 mm  Power dissipation: 0.5 W  Accuracy: 0.05° (FOV ±32°) 0.1° (FOV ±32° - ±64°) Attitude Determination Devices WeightDimensionsPower (at +20°C) Angular Accuracy CT-6322.5 kgØ13.46x14.22 cm8 W~11 arc-sec BATC CT-63x Series Star Tracker

3. AAE 450 – Spacecraft Design ADCS Development Information  Vehicle Configuration  Mission Stage  Orbit Insertion, Rendezvous, Transfer Phase, Maneuvers  Location of crew/movement  Disturbance Environment Analysis  Gravity-gradient torque, aerodynamic torque, torque due to magnetic disturbance, solar disturbance  Spacecraft Control Options

4. AAE 450 – Spacecraft Design References  Ball Aerospace & Technologies, Corp.  http://www.ballaerospace.com/ct63x.html http://www.ballaerospace.com/ct63x.html  http://www.ballaerospace.com/ct611.html http://www.ballaerospace.com/ct611.html  Texas Space Grant Consortium  http://www.tsgc.utexas.edu/archive/subsystems/sensors.pdf http://www.tsgc.utexas.edu/archive/subsystems/sensors.pdf  Astro Research Corp.  http://www.astro-r.co.jp/product/Sun%20Sensor.pdf http://www.astro-r.co.jp/product/Sun%20Sensor.pdf

5. AAE 450 – Spacecraft Design  Star Tracker  Autonomous attitude sensor – outputs an attitude quaternion  Flight-proven hardware  Man-rated – Space Shuttle Star Tracker Additional Options WeightDimensionsPower (at +20°C) Angular Accuracy CT-6332.5 kgØ13.46x14.22 cm8 W~6 arc-sec Weight*DimensionsPower (at +20°C)* Angular Accuracy* CT-611~7.7 kg12 W~ 3 arc-sec * Based on CT-601 available data