摘要
The inter-satellite linkage antenna of the user satellite uses the Elevation-over-Azimuth type,and the zenith pass problem occurs during tracing TDRS. Firstly,the movement laws of the inter-satellite linkage is introduced for predicting the movement of the user satellite antenna. Then,the potential zenith pass moment is analyzed in detail. Some special orbits for the user satellite that can avoid the blindness zone are obtained. Finally,the zenith pass tracing strategies for the user satellite antenna based on the mechanical tilting are designed by using the trajectory preprocessor. The designs are based on the predicting results of the movement laws of the inter-satellite linkage. The strategies are proved to be reasonable and feasible for solving the zenith pass problem by simulation.
The inter-satellite linkage antenna of the user satellite uses the Elevation-over-Azimuth type, and the zenith pass problem occurs during tracing TDRS. Firstly, the movement laws of the inter-satellite linkage is introduced for predicting the movement of the user satellite antenna. Then, the potential zenith pass moment is analyzed in detail. Some special orbits for the user satellite that can avoid the blindness zone are obtained. Finally, the zenith pass tracing strategies for the user satellite antenna based on the mechanical tilting are designed by using the trajectory preprocessor. The designs are based on the predicting results of the movement laws of the inter-satellite linkage. The strategies are proved to be reasonable and feasible for solving the zenith pass problem by simulation.
