To solve the problem of impact point position and inclination angle dispersion control of a two stage solid sounding rocket, a method using both adaptive ignition time control and second stage closeloop guidance is put forward in this paper. Taking advantage of that the rocket's range and launching direction are relatively fixed, affecting factors such as atmospheric drag, spin and shape of the earth, are treated as systematic error and equivalently compensated, thus a simplified trajectory transfer guidance model is obtained. On this basis, an adaptive ignition time control algorithm based on rendezvous point of the two ellipse trajectories before and after second stage boosting is designed. A second stage closeloop guidance algorithm with no energy dissipation nor iteration calculation but given velocity of the virtual target is derived as well. MonteCarlo simulation result shows that the sounding rocket's flight test requirements are met well, with impact point position error less than 2.2 km and inclination angle error less than 0.5°.