Abstract:

Optimal interception orbit calculation is important content of spacecraft onorbit interception question, and is one of the core technical problems of spacebased weapons development. It’s difficult to analytically analyze and calculate because of the nonlinearity and implicitness of orbit calculation equations and interception equations. Aiming at interception trajectory optimization problem with noconstant interception point, the law of interception trajectory parameter and characteristic velocity in transfer point changing with interception time and interception true anomaly is summed up. On this basis, the calculation of the initial interception parameters from interception orbit true anomaly has been researched and rapid iterative algorithm for minimumenergy interception trajectory has been designed. Finally, practicability and rapidity of the algorithm is verified by simulation.