CAJ | 학술논문

为提高拦截精度并减少消耗数量,对大气层内末端飞行动能拦截器的微型脉冲发动机点火控制进行分析和研究.给出了弹体滚转角速度效能公式,优化滚转圈数;依点火时刻弹体是否滚转,从直接力响应时态和滚转扇扫点火算法分析影响耗散数量的因素;建立直接力环节被控模型,采用补偿偏差方法修正偏差.仿真结果表明,该控制策略能保证理想动态响应,节省需点火的微型脉冲发动机数量.
위제고란절정도병감소소모수량,대대기층내말단비행동능란절기적미형맥충발동궤점화공제진행분석화연구.급출료탄체곤전각속도효능공식,우화곤전권수;의점화시각탄체시부곤전,종직접력향응시태화곤전선소점화산법분석영향모산수량적인소;건립직접력배절피공모형,채용보상편차방법수정편차.방진결과표명,해공제책략능보증이상동태향응,절성수점화적미형맥충발동궤수량.
In order to improve the intercept precision and reduce the consumption, the micro pulse motor’s ignition control for kinetic kill vehicle during the terminal flight in the atmosphere was analyzed and researched. The efficiency formula of rolling missile’s angular velocity was proposed to optimize the number of turns. Based on whether the missile body was rolling or not, the influence factor on consumption was analyzed from the direct thrust's response tense and the sector scanning ignition algorithm of rolling. With the controlled model for the direct force, deviation compensation method was applied to reduce the error. The simulation results showed that the control strategy can ensure the ideal dynamic response and reduce the quantity of micro pulse motors that needed to be ignited.