Flight Attitude Control Techniques For A Mechanical And Electrical Systems

In this dissertation, the technique of the attitude control on the infantry smart grenade.has been studied systematically in theory. Aiming at the characteristics especially itsdeficiency of the infantry smart grenade, the scheme of semi-active laser guide and theimpulse control of the infantry smart grenade has been put forward. The characteristics ofall kinds of the attitude control were analyzed, the structural attitude control was designedand the shape of its fins has been improved. A relatively systematic research on thetrajectory correction by impulse thruster array has been carried out. The digital ignitingcontrol system which was based on MCU and CPLD has been designed. At the same time,the control circuit of trajectory correction by impulse thruster array was designed and thecontrol logic of vector motor ignition is established.The flowfield structure of the grenadewas studied under low altitude and subsonic flow. With regard to the trajectory correctiontechnique, the simulation of the infantry smart grenade which flied under the low velocityhas been analyzed. The results of simulation were compared with the results ofnon-lateral-control-jet and lateral control jet under different velocity or different attackangle. The velocity and pressure distributions of the interaction flowfields around jet andnear the tail of smart ammunition were obtained. The results have validated the feasibilityof the impulse correction technique.