Abstract:

To improve the computing efficiency of the ordinarily used variable stepsize RKF algorithm, an adaptive variable stepsize RKF method based on norm control is presented. The quantitative functional relationship between the local truncation error, tolerance and stepsize is given, and then the stepsizes are automatically adjusted, and the conditions under which the local error norm equals to zero or minimum are discussed. The description of the satellite orbit dynamic system can be attributed to the solution to the initial value problems of firstorder vector ordinary differential equations. The proposed method is used to solve this problem to achieve the satellite orbit integral under the consideration of earth nonspherical and a third body perturbation. Simulation results indicate that the proposed method can satisfy the requirements of high precision orbit prediction, improve computing speed, and is worthy of use in the orbit prediction.Key words:

Key words: RKF method;variable stepsize;norm control;tolerance