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Inertial Sensor and Its Application for Space Fundamental Experiments

3rd ASTROD, 14-17 July, 2006, Beijing. Inertial Sensor and Its Application for Space Fundamental Experiments Ze-Bing Zhou ( 周泽兵 ), Jun Luo ( 罗俊 ) zhouzb@mail.hust.edu.cn Center for Gravitational Experiment, Huazhong University of Science and Technology. Outline.

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Inertial Sensor and Its Application for Space Fundamental Experiments

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  1. 3rd ASTROD, 14-17 July, 2006, Beijing Inertial Sensor and Its Application for Space Fundamental Experiments Ze-Bing Zhou (周泽兵), Jun Luo (罗俊) zhouzb@mail.hust.edu.cn Center for Gravitational Experiment, Huazhong University of Science and Technology

  2. Outline • Principle of inertial Sensor • Space application of inertial sensor • Progress of inertial sensor in HUST • Summary

  3. y xr =x - y k x m 1、Principle of Accelerometer/Inertial Sensor If To obtain the acceleration of the mobile objects by monitoring the relative motion of the proof mass w.r.t. it; Lower of natural frequency (softer linkage), higher sensitivity

  4. Accelerometer Structure Test Mass Senor Open- Output Sensor Test Mass Closed- Controller Actuator Output Linkage：Mechanic, Electrostatic, Magnetic, Optical Position Sensor: Optical, Capacitance, SQUID Force Actuator: Electromagnetic, Electrostatic, Piezo- Control Unit:simulative,digital, mixed

  5. Electrostatic Suspension/Space Accelerometer • Capacitance transducer + Electrostatic Actuator • One Proof Mass with Six degree-of-freedom measurement

  6. Superconducting Inertial Sensor Optical Suspension Inertial Sensor • SQUID technique Inertial sensor with atom-interferometer • Optical read out (phase) and control (power)

  7. 2、Space Application of Inertial Sensor Operation modes in space applications Acceleration Measurement Model Test mass tracks with spacecraft Inertial Reference Model (Geodesic) Spacecraft tracks with test mass

  8. Space Application of Inertial Sensor 2015 LISA 1975 CACTUS 2009 ? MICROSCOPE 1996 ASTRE: µgravity survey 2006? GRADIO GOCE 2000 STAR : CHAMP 2002 SuperSTAR : GRACE Ref. ONERA

  9. Projects of EGF Measurement CHAMP GFZ,Germany 2000.7.15 GRACE NASA/GFZ 2002.3.19 3*10-9 m/s2 3*10-10 m/s2 Accelerometer provided by P. Touboul, ONERA, France

  10. MICROSCOPE (ONERA-ESA 2009?) • Proof-mass material : • Platinum - Titanium • Pt/Pt - 186g/500g • Pt/Ti - 186g/106g Expected Precision: 5*10-15 m/s2

  11. Inertial Sensor for LISA Univ. Trento, Italy, 2003 2*10-13 m/s2/Hz1/2 at 3mHz Predicted Accelerometer Noise: 3×10-15 m/s2/Hz1/2 0.1mHz ~1mHz

  12. 3、Development of inertial sensor in HUST Background: • Member of ASTROD-1: Inertial sensor research • TISS: Test of Inverse-law Square in Space proposed by Prof. Jun Luo Present status: Preliminary progress of CESA on ground (Chinese Electrostatic Suspension/Space Accelerometer)

  13. Terrestrial Scheme for Electrostatic Suspension Inertial Sensor/Accelerometer Main difficulty: 1g Earth’s gravity acceleration limit High-Voltage Suspension Fiber Suspension ONERA, France, 2000 2*10-10 m/s2/Hz1/2 [RSI 71 2000 302] Univ. Trento, Italy, 2003 10-13 m/s2/Hz1/2 [PRL 91 2003 151101]

  14. CESA Scheme Fiber Suspension Electrostatic feedback

  15. Experimental setup Original prototype Fiber • Vacuum: 100Pa. • Position in center of +10um • Preamplifier in vacuum • Digital PID Control Probe Turntable

  16. Experimental parameters

  17. Calibration steps: (1)To change the capacitive electrodes position with respect to the test mass by the rotate table; (2)The capacitive sensor detects the relative motion, and then acts an electrostatic torque on the test mass; (3) The test mass follows the capacitive electrodes, and its rotational angle is simultaneously monitored by an optical level. * In this case, the electrostatic torque is equal to the fibre restoring one.

  18. Calibration Result Angle variation (5.173mrad) Feedback voltage variety (0.170V) Sensitivity:

  19. Preliminary Result (8th July,2006) 1SD=1.5mV Resolution: 3*10-12 Nm/Hz1/2 at 1mHz 2.4*10-10 m/s2/Hz1/2 at 1mHz

  20. Dynamic range measurement Error signal Feedback voltage Dynamic range: + 2.8*10-8 Nm

  21. Predicted of Inertial sensor for ASTROD-1 Capacitance gap: 0.8 mm 1 cm (156 times) TM: 320g (Al) 1.68 kg (5*5*3.5cm3, Au-Pt) (5 times) 2.4*10-10 m/s2/Hz1/2 at 1mHz If the capacitance sensor keeps same resolution 3*10-13 m/s2/Hz1/2

  22. Fpm,g Xn Fsp,g Fsp,ng Fpm,n xa Xs SC TM Coupling Kcp Coupling Kcp Electrostatic Actuator Ha Thruster Ht Capacitance Transducer Hs Verr Vn Tn Vfed Controller Hc Disturbance model • Intrinsic noise • Disturbance on TM • Coupling between TM and SC

  23. Key of further research: • To add translation control • To improve the vacuum • To add vibration isolation • To analyse and test the disturbance effects • To change probe parameters for ASTROD-1 condition: • TM material, capacitance gap….

  24. 4. Summary • Inertial Sensor/Accelerometer is one of key technologies for space fundamental experiments. It will be developed with the requirement of space mission, and inversely then it will push the space mission. • Electrostatic suspension/space accelerometer has been studied for over 30 years, and succeed to be used in space. • CESA should be studied step by step, too much disturbances need be analyzed, tested, and suppressed.

  25. Thank you very much!

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