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Advancing Payload Positioning and Attitude Control: Insights from ERAU's ASCEND Program

The ERAU ASCEND project focuses on enhancing payload positioning and motion analysis through advanced instrumentation and data analysis. Key objectives include determining the position, velocity, and acceleration of the payload while employing various instruments such as accelerometers, gyros, and solar sensors to understand forces acting upon the system. Data from the November 22, 2008 flight revealed inconsistencies in sensor readings due to temperature fluctuations, highlighting the need for better calibration methods. Future goals aim to improve solar sensor reliability and develop a robust attitude control system.

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Advancing Payload Positioning and Attitude Control: Insights from ERAU's ASCEND Program

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Presentation Transcript

  1. ERAU ASCEND!Attitude determination Andrew Grant

  2. Overview • Flight Objectives • Instruments • Data • Conclusions • Future Goals

  3. Flight Objectives • Determine the position and motion of our payload • Positions • Velocities • Accelerations/Forces _ ω _ F _ S

  4. Instruments • Acceleromoter • Determine the forces acting upon the payload to determine X-Y-Z translations • Gyros • Determine the rotations acting around the X-Y-Z axis to determine relative reference axis for acceleromoter • Sun Sensor • Use multiple solar cells (3-4) to determine the location of the sun with respect to the coordinate frame of the payload

  5. Instruments • Sparkfun IMU 6 degrees of freedom • ±1.5g-6g Three Axis Low-g micromachinedAccelerometer • 3-ADXRS300 ±300°/s Single chip yaw rate gyro with signal conditioning

  6. Instruments • Solar Sensor • .45V 200mA Silicon Polycrystalline Solar Cell • Polycrystalline Silicon Solar Cell 0.5V 400mA to 500mA Source: www.goldmine-elec-products.com

  7. Data-Acceleromoter Flight launch November 22, 2008 The Y-direction is the Direction of the Earths Gravitational Acceleration. (above)

  8. Data-Gyros Flight launch November 22, 2008

  9. Data-Calibration Inconsistent Accelerometer readings for temperature fluctuations (above) Non-linear/poor functioning gyros at temperature fluctuations (left)

  10. Data-Calibration Comparable for first part of temperature calibration test

  11. Data-Solar

  12. Conclusions • IMU • Received Launch Data • Need to calibrate data to temperature fluctuations • Calibration Techniques Failed (Poor IMU Quality) • Solar Cells • Received information on voltage change with temperature and altitude.

  13. Future Goals • Further develop and test solar cells to be able to acquire the position of the sun for payload attitude • Develop more reliable way of acquiring Attitude • Develop an attitude control system

  14. Future Goals • Solar Sensor

  15. Questions?

  16. Data Analysis GeimiDeLarge

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