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.