【摘要】：立方星的姿態(tài)測量與控制系統(tǒng)常采用磁測磁控結(jié)合偏置動量輪的方案,整星剩磁干擾力矩是影響姿態(tài)控制精度的重要因素之一。提出了一種利用磁強(qiáng)計實(shí)現(xiàn)剩磁矩在軌辨識與利用磁力矩器實(shí)現(xiàn)剩磁矩主動補(bǔ)償?shù)男路桨?基于磁強(qiáng)計輸出和衛(wèi)星姿態(tài)動力學(xué)建立了剩磁矩在軌辨識模型,并利用采樣濾波器(UKF)提高單磁強(qiáng)計條件下的辨識效果;把控制對象簡化成線性定常系統(tǒng),分析了剩磁干擾力矩對姿態(tài)的影響數(shù)學(xué)模型,并針對磁力矩器和磁強(qiáng)計分時工作的特點(diǎn),基于疊加性原理提出了基于角速度的剩磁矩主動補(bǔ)償算法。仿真研究表明,在1000 s內(nèi)剩磁矩在軌辨識精度為0.001 A×m~2量級,主動補(bǔ)償后,偏航角、滾動角與俯仰角控制誤差分別從4.3°、4.6°與2.1°均減少至0.4°以內(nèi)。提出的方法為類似配置衛(wèi)星減少剩磁干擾力矩的影響提供了一種新思路。
[Abstract]:The attitude measurement and control system of cubic star usually adopts the scheme of magnetic measurement and control combined with biased momentum wheel. The residual magnetic disturbance moment is one of the important factors that affect the precision of attitude control. In this paper, a new scheme is proposed to identify the residual magnetic moment in orbit by using magnetometer and to realize active compensation of residual magnetic moment by using magnetic torque device. Based on the output of magnetometer and the dynamics of satellite attitude, a model of on-orbit identification of residual magnetic moment is established. The sample filter (UKF) is used to improve the identification effect under the condition of single magnetometer. The control object is simplified as a linear time-invariant system, the mathematical model of the influence of residual magnetic disturbance moment on attitude is analyzed, and the characteristics of time-sharing of magnetic torque and magnetometer are analyzed. Based on the principle of superposition, an active compensation algorithm of residual magnetic moment based on angular velocity is proposed. The simulation results show that the accuracy of the residual magnetic moment in orbit identification is 0.001 A 脳 m ~ (2) in 1000 s. After active compensation, the control errors of yaw angle, rolling angle and pitch angle are reduced from 4.3 擄, 4.6 擄and 2.1 擄to less than 0.4 擄, respectively. The proposed method provides a new way for similar satellites to reduce the influence of residual magnetic disturbance moment.
【作者單位】： 航天恒星科技有限公司;南京航空航天大學(xué)航天學(xué)院;
【基金】：國家自然科學(xué)基金資助項目(61203197)
【分類號】：V448.22

【相似文獻(xiàn)】

相關(guān)期刊論文 前5條

1 易忠;;中低軌道衛(wèi)星的磁補(bǔ)償[J];環(huán)模技術(shù);1997年04期

2 易忠;史堯宜;;地磁場中測量衛(wèi)星磁矩的一種新的方法[J];環(huán)模技術(shù);1996年04期

3 李楊,涂歆瀅;星體剩磁矩對姿控系統(tǒng)影響的仿真研究[J];系統(tǒng)仿真學(xué)報;2002年02期

4 程麗麗;肖琦;張志強(qiáng);董勇偉;張力;;某型號衛(wèi)星磁環(huán)境兼容性分析與控制[J];航天器環(huán)境工程;2009年04期

5 ;[J];;年期

，

本文編號：2321371