摘要
在航天测控任务中,对轨控效果进行标定并合理利用可以实现更为精准的轨道控制目标。提出一种用虚拟等效推力来替代姿态偏差所带来的影响,利用控前控后精密轨道同时标定轨控执行过程轨道切向、径向、法向三方向速度增量的方法,介绍该方法在我国交会对接任务中的应用情况,及其标定结果对定轨精度的敏感程度,试图在理论上进一步说明利用精密轨道进行轨控标定的可行性。
The orbit maneuver accuracy of the spacecraft can be greatly improved by calibrating the orbit maneuver effect. A method for calibrating the real velocity increment of RTN directions with precise orbit parameters was proposed, in which virtual equivalent thrust was adopted to replace the impact of attitude error during the control. Then, the successful application of this method in Chi- nese Rendezvous and Docking missions was introduced. Finally, the sensitivity of the calibrating re- sult to the accuracy of orbit was analyzed. The results demonstrated that the calibration of control effect was feasible.
出处
《载人航天》
CSCD
2014年第1期16-20,共5页
Manned Spaceflight
关键词
交会对接
轨道控制
标定
rendezvous and docking
orbit maneuver
calibration
