In order to simulate the jet flow field of attitude control motor in the case of rotating,and avoid using the complex sliding mesh technique,the governing equations and the numerical boundary conditions were given in the rotating frame of reference instead of the inertial fixed coordinates.

A mathematical model of the trajectory deviation from the line of sight was established, the guidance closed loop was compensated with a phase advance lag corrective network, a selecting algorithm of the attitude control motors used to steer the missile s attitude was presented.

Research on outlet pressure deviation calculation of pressure reducing valve for attitude control engine;

The side jet technology of foreign advanced surface-to-air missiles is analyzed,disperse thrust models of 180 attitude control engines of patriot-III missile is built,and some optimized methods of ignite technology is studied,then the result of the simulation is presented.

Using the plentiful software and USB interface of PC,taking FPGA as the core,controling the correspondence of the chip of USB,the automatic test of multi-pulse attitude control engine system status and the ignition of multi-pulse attitude control engines were carried out in this paper.

In missiles using direct force control systems, a high precision robust guidance law with low side jet consuming is required.

In this paper, an attitude control method using side jets of a kind of long-distance air defense missile is studied.

Experimental study on plume impingement effects of satellite attitude control thruster nozzle;

First a model of combined fire of motors for attitude control is developed,and then on the basis of this model,a firing rule of attitude control motor is designed and an analysis on the energy consumption efficiency is made under the condition of di-fferent position distribution of attitude control motors,finally the simulation result proves the fea.

The status and tendency of attitude control motors for satellites is briefly described.