Study Of Correction Control Technologies And Flight Stability

In modern warfare, the use of precision munitions is not only directly related tovictory and defeat of the war, but also can reduce the casualty rate of civilian. Thetrajectory correction projectile is one of the typical representatives. The Low-cost andhigh-performance correction implementing agencies and flight stability of trajectorycorrection projectiles is a technical difficulty needed to focus on resolving in thedevelopment process.By researching trajectory correction technology and development in domestic andinternational, the correction principle and its structural layout of the correctionprojectile is determined. The aerodynamic model of correction projectile is established.After making its flow field numerical simulation at different Mach number, the mainaerodynamic parameters of correction projectile are get. The parameters include dragcoefficient, lift coefficient, pole damping moment coefficient and equatorial dampingmoment coefficient.The permanent magnet motor of correcting mechanism is designed in the structureof the correction mechanism. And the basic structure of the permanent magnet motor isdetermined. Then, based on the electromagnetic field theory, applying the finite elementmethod, the structural factors of affecting the performance of permanent magnet motorare studied and analyzed. Effect of permanent magnet motor performance is get, whichis had pole-slot combination, the air-gap length, the slot width and the circumferencesize of permanent magnet. Depending on it, experimental prototype of the basicprinciples of the permanent magnet motor is produced.The measuring force sensor used in the experiments is built. And the smoothnessof motor rotation experiment and the output torque control experiment is completed.The effect of small fluctuation range and controllability of permanent magnet motortorque is achieved. Based on the theory of projectile trajectory, the force in the flying process of thecorrection projectile on the external trajectory is analyzed, and the trajectory equationsof the duck rudder type correction projectile are established. Combined with the resultsof the aerodynamic characteristics, applying the algorithm of fourth-order Runge-Kutta,the parameters of the external trajectory of the correction projectile are calculated Thecorrection ability of correction projectiles is get. The correction process and stabilityof correction projectiles under different interference conditions is analyzed.