Analysis and modeling of spacecraft with flexible solar panel disturbed by thermally induced motion

Thermally induced motion of flexible solar panel have significant impact on attitude dynamics and control when the spacecraft experience eclipse transitions. Based on two analyses methods thermally induced attitude dynamics of a rigid hub with flexible beam is developed. The principle of thermally induced vibration is explained. Thermally induced disturbance toque which initiates attitude error of control system is obtained. The effects of key structural parameters on thermally induced attitude disturbance are investigated. A stability criterion of thermally induced motion including the effect of the spacecraft is established related to structural damping, solar incident angle, and the ratio of structural and thermal response times. Numerical simulations illustrate that thermally induced disturbance distort the attitude of spacecraft and larger value of structural damping; larger difference between structural and thermal response times are likely to voiding thermal flutter and unstable motion of the spacecraft.

[1]  Ji-Hwan Kim,et al.  Thermally Induced Vibrations of Spinning Thin-Walled Composite Beam , 2003 .

[2]  Stanley E. Woodard,et al.  Experimental Investigation of Spacecraft In-Flight Disturbances and Dynamic Response , 1997 .

[3]  Changduk Kong,et al.  Study on thermally induced vibration of flexible boom in various thermal environments of vacuum chamber , 2005, SPIE Micro + Nano Materials, Devices, and Applications.

[4]  Richard Y. Chiang,et al.  THERMAL SNAP DISTURBANCE IDENTIFICATION VIA IN -FLIGHT DATA , 2003 .

[5]  Ohseop Song,et al.  Thermoelastic Modeling and Vibration of Functionally Graded Thin-Walled Rotating Blades , 2003 .

[6]  Sang-Young Park,et al.  Thermally Induced Attitude Disturbance Control for Spacecraft with a Flexible Boom , 2002 .

[7]  C. Foster,et al.  Solar-array-induced disturbance of the Hubble Space Telescope pointing system , 1995 .

[8]  Takanori Iwata,et al.  Thermally Induced Dynamics of Large Solar Array Paddle: from Laboratory Experiment to Flight Data Analysis , 2011 .

[9]  Zhangzhi Cen,et al.  Robust Optimization of Thermal-Dynamic Coupling Systems Using a Kriging Model , 2010 .

[10]  John D. Johnston,et al.  Thermally Induced Attitude Dynamics of a Spacecraft with a Flexible Appendage , 1998 .

[11]  Jin Duan,et al.  Thermally-induced bending-torsion coupling vibration of large scale space structures , 2007 .

[12]  Earl A. Thornton,et al.  Thermally induced bending vibrations of a flexible rolled-up solar array , 1993 .

[13]  Ohseop Song,et al.  Active Vibration Control of Composite Spacecraft Booms Exposed to Solar Radiant Heating , 2004 .

[14]  Joseph R. Blandino,et al.  Thermally Induced Vibration of an Internally Heated Beam , 2000 .

[15]  Alessandro Dallocchio,et al.  Dynamic Response of Rapidly Heated Cylindrical Rods: Longitudinal and Flexural Behavior , 2008 .

[16]  Wei Li,et al.  Coupled Thermal-Dynamic Stability Analysis of Large-Scale Space Structures by FEM , 2006 .

[17]  J. Kidawa-Kukla.  Application of the Green functions to the problem of the thermally induced vibration of a beam , 2003 .

[18]  G. Heppler,et al.  Nonlinear Transient Response of Thermally Loaded Laminated Panels , 2004 .

[19]  Stanley E. Woodard.  The Upper Atmosphere Research Satellite In-Flight Dynamics , 1997 .

[20]  E. Thornton,et al.  Thermally Induced Dynamics of Satellite Solar Panels , 2000 .

[21]  In Lee,et al.  Thermal snapping and vibration characteristics of cylindrical composite panels using layerwise theory , 2001 .

[22]  J. Y. Liu,et al.  Thermal effect on the deformation of a flexible beam with large kinematical driven overall motions , 2007 .