Based on practice,the airborne rockets guidance techniques have been studied elementarily,a terminal correction means of rockets using impulse engine has been put forward,the control equations of the impulse correction have been built,and the key problems have been studied and analyzed.

The exhaust gas ingredients of pulse engines,with five different combustion chamber volumes,throttle valve at small,middle and wide opening positions respectively,are tested.

The blended control switch-time and the formula for deciding the pulse motor .

In solving problems of breakage in nozzle throat inserts for a pulse motor,analysis on the strength of nozzle throat insert have been carried out using the MSC Patran 2004r2 finite element soft-ware.

Optimum design of the composite shell of pulse motor has been presented using ANSYS soft ware.

To study the attitude stabilization control effect on short-range antitank rockets using pulse jets.

If the angle of fire is large,using pulse jets to correct the rocket trajectory,the error in theory in the relation between thrust vector produced by pulse jets and the error vector corrected will arise,which is established by the general coordinate transform in order to decide which pulse jet will be fired.

The pulsed proportional navigation(PPN) guidance and attitude pursuit guidance(APG) by the concept of zero effort miss(ZEM) were established,and the corresponding ignition control strategy of the pulse jet was presented.

In the condition of definitive structural parameter and part of operative parameter of impulse engine,the effect of controlling force of impulse engine on correct trajectory is analysed.

Aiming at the impulse engine in the trajectory correction projectile,one dynamic experiment method is put forward to measure the correction ability of the impulse engine.