In order to figure out the interior ballistic characteristics of the micro-impulsive thruster,numerical calculation and simulation have been done,in which the effects of the transient burning were taken into consideration and steady burning rate under different pressure ranges were used.

Design and experiment of a pulse thruster with high combustion chamber pressure

Cold test of pulse thruster with high combustion chamber pressure

Study of ignition transient characteristic of impulsive microthruster was conducted.

The three sets of Ft curves from impulsive microthrusters tests were studied,which are used for the attitude correction of kinetic missiles or hypervelocity rockets.

Based on the model, the characteristic of the trajectory correction was studied with the impulse force.

By analyzing the layout of impulse thruster controllers, and the work process of laser detector and forces which acted on the trajectory correction projectiles, a impulse force control trajectory model on pitch plane was established.

On the experimental system for PPT;

Pulsed plasma thruster(PPT) is a kind of space electromagnetic propulsion system,which can be used as micro-sat or small-sat attitude/orbit control system.

Review of pulsed plasma thruster;

Analysis of equivalent circuit model for pulsed plasma thruster;

By way of Coupling the effects among the electric field,magnetic field and flow field in the pulsed plasma thruster,the process of the capacitor discharge,propellant ablation and plasma acceleration are characterized,and a one-dimensional time-dependent model based magnetohydrodynamic(MHD)for PPT is presented in this paper.