Abstract
Aiming at the problem of the precise design of the direct transfer trajectory of Mars probe, this paper proposes an algorithm of fast differential correction. It is based on the mathematical model of the difference between the control and target parameters, henceforth the matrix of partial derivatives of the system is solved. This can effectively reduce the number of times of integration in the process of solution. Taking the opportunity of the 2018 Mars probe as an example, the algorithm is verified. The results of emulation show that by using the initial values yielded by the method of patched conical curves, only 6–9 orbit integral iterations are needed to get a standard trajectory. Via the STK (satellite tool kit) technique, the results of computation are compared and justified.
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