Based on analytical solutions of T-H equations and the respective state transition matrix, an open-loop control method of spacecraft impulsive relative hovering is studied, which proves promising for use in practical engineering. The true anomaly intervals of the hovering impulse are optimized by a nonlinear mathematical programming. Through calculation of collision probability, a method of safety analysis and risk management is proposed. Numerical simulations show that the relative hovering method can be used for circular and elliptical reference orbits hovering. A local optimal solution can be obtained by applying the true anomaly intervals optimization method. The maximum collision probability and the minimum relative distance appear almost simultaneously. Furthermore, a smaller relative distance could generate a largercollision probability. Based on analytical solutions of TH equations and the respective state transition matrix, an open-loop control method of spacecraft impulsive relative hovering is studied, which proves promising for use in practical engineering. The true anomaly intervals of the hovering impulse are optimized by a nonlinear mathematical programming. Through calculation of collision probability, a method of safety analysis and risk management is proposed. Numerical simulations show that the relative hovering method can be used for circular and elliptical reference orbits hovering. A local optimal solution can be obtained by applying the true anomaly intervals optimization method. The maximum collision probability and the minimum relative distance appear almost simultaneously.