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Dynamics Modeling and First Design of Drag-Free Controller for ASTROD I

Dynamics Modeling and First Design of Drag-Free Controller for ASTROD I. Hongyin Li, W.-T. Ni Purple Mountain Observatory, Chinese Academy of Sciences S. Theil, L. Pettazzi, M. S. Guilherme. ZARM University of Bremen, Germany. Outline. Introduction of the Mission Simulator

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Dynamics Modeling and First Design of Drag-Free Controller for ASTROD I

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  1. Dynamics Modeling and First Design of Drag-Free Controller for ASTROD I Hongyin Li, W.-T. Ni Purple Mountain Observatory, Chinese Academy of Sciences S. Theil, L. Pettazzi, M. S. Guilherme ZARM University of Bremen, Germany

  2. Outline • Introduction of the Mission • Simulator • Controller Development • Conclusion • Outlook

  3. Science goal Solar-system gravity mapping & relativistic gravity test Orbit Heliocentric orbit, 0.5AU-1AU Orbit launch in 2015  SC configuration Cylinder : 2.5 (diameter)m ×2 m covered by solar panels. FEEP(Field Emission Electric Propulsion) Star Sensor, Gyroscope (??) EPS(Electrostatic Positioning/ Measurement System) 1 test mass Mission Introduction

  4. Simulator • Equations of Motion • Disturbance & Environment

  5. Heliocentric inertial frame Center of mass of sun i Earth-fixed Center of earth e Spacecraft body-fixed frame Center of mass of spacecraft b Sensor frame for test mass Geometrical center of sensor sens Body-fixed frame for test mass Center of mass of test mass tm Coordinates I

  6. Frame Base point x direction z direction Heliocentric inertial frame Center of mass of sun Aries Normal of ecliptic Spacecraft body-fixed frame Center of mass of spacecraft Parallel to symmetry axis of telescope Symmetrical axis Sensor frame for test mass Geometrical center of sensor Normal of the surface of the house nearby the telescope Normal of the upper surface of the house Body-fixed frame for test mass Center of mass of test mass Normal of the surface nearby the telescope Normal of the upper surface of test mass Coordinates II

  7. Equations of Motion

  8. Disturbance & Environment • Gravity Field (first order--spherical) Elements of Elements of

  9. Disturbance & Environment • Gravity Field (second order… ) One of the Science goal of ASTROD I is to test the gravity field parameter of the solar gravity. So, It must be included in the further model.

  10. Disturbance & Environment • Solar Pressure

  11. Solar Pressure • Solar pressure at 0.5 AU is 4 times that of 1AU • A low-pass filter is used to get the stochastic part with a white noise passed deterministic part Solar pressure at 1AU

  12. Coupling between SC&TM Translation coupling Rotation coupling

  13. Sensors and actuators • Star-Sensor • EPS-position measurement • EPS-attitude measurement • EPS-attitude suspension • FEEP-force • FEEP-torque White noise  shaped noise Need to consider sample frequency, nonlinearity in the future model….

  14. Simulator

  15. Controller Design • Structure of Controller • Requirements of controller • Synthesis • Closed loop Analysis

  16. Structure of Controller DFACS 3 Sub-system

  17. Requirements of Controller

  18. Synthesis I LQR: Linear-Quadratic-Regulator With the LQR method we can derive the optimal gain matrix K such that the state-feedback law minimizes the quadratic cost function Given following linear system : Just as the kalman filter we can get the minimum steady-state error covariance

  19. Synthesis II • LQG ＝LQR ＋ KF Linear-Quadratic-Gaussian ＝Linear-quadratic-regulator + kalman filter(Linear-quadratic-filter) • With DC disturbance need feed forward DC disturbance

  20. LQG Design Plant

  21. Controller Standard LQR used here is MIMO PD controller. It’s feedback is proportion (position, angle ) and derivative (velocity and angular velocity) of outputs of system. Feed forward part can cancel the static error.

  22. Synthesis III • What does feed forward do to the frequency Response of the controller? Improve the performance in low frequency range.(integral ) but reduce the stability of the closed loop ,need to trade-off … • Stability of the closed loop system? with some weight gains, there is still some poles on the right phase because the negative stiffness. So we need to chose the weight gain carefully. Try and tuning to get better performance as well as a stable system.

  23. Closed loop analysis • Transfer function & PSD of Simulation Data • Pointing accuracy :

  24. Test mass position

  25. Transfer functionanalysis

  26. PSD analysis

  27. Conclusion • A model for ASTROD I is built. However it is simple, the structure is established and each subsystem can be extended to get a more detailed model. • LQG (LQR+KF) was developed which can meet the requirements of the mission.

  28. Outlook • Detailed model Based on SC design • Inertial sensor：Cross-coupling between DOFs • Star sensor：Sample frequency，data fusion of two sensors. • Gyroscope to help the attitude estimate. • FEEP nonlinearity，frequency response.Location of FEEP clusters. • Advanced control strategy • Loop-Shaping with weighted LQR • Decoupling of controllers and DOFs • Robust Control method

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