Orbit Correction Strategy of LEO Vehicle Based on Linearized Orbital Motion Equation.

It is very necessary to execute orbit correction for ultra-low-orbit vehicle, which is badly influenced by near-earth environment. The orbital motion equation which considered the non-spherical perturbation and atmospheric perturbation was linearized. Then, an impulse correction method was introduced and used to keep a near-earth vehicle flying along the standard orbit. Furthermore, a method to eliminate errors caused by linearization was also studied. The feasibility of the correction method was validated by simulation. For a 120km-altitude vehicle, flying one hour, the optimal correction times is 6, the required Av is 63. 797 1 m/s. [ABSTRACT FROM AUTHOR]