Approximate calculation of zero effort miss vector for space target interception

Based on the trajectory equation for restricted two-body problem and Taylor series linearization method, the approximate function between the initial guidance errors and the end zero effort miss vector was proposed for space interception by neglecting the effect of gravity on motion state of interceptor and target. Experimental results show that the zero effort miss vector calculated by using approximate formulas is close to the real miss vector. Under the conditions of small initial errors, the satisfied results can be obtained by approximate function. The zero effort miss vector obtained can be used for the preliminary design and analysis of kinetic interceptor guidance.