CAJ | 학술논문

火箭靶弹无控飞行过程中飞行攻角较小且无法准确模拟,为提高靶弹弹道理论预估精度,弹道理论计算可假定飞行攻角为零,将飞行攻角产生的诱导阻力贡献折算为对零升阻力系数的修正.建立了火箭靶弹气动特性工程计算方法,针对火箭靶弹零升阻力系数计算模型不确定性问题,利用火箭靶弹A飞行试验GPS遥测数据对其零升阻力系数进行了参数辨识,基于辨识结果对火箭靶弹零升阻力系数工程计算方法进行了修正.经火箭靶弹B飞行试验结果验证,由于综合考虑了飞行攻角产生的诱导阻力贡献,采用修正后的零升阻力系数,弹道理论预估精度大大提高,满足工程要求.
화전파탄무공비행과정중비행공각교소차무법준학모의,위제고파탄탄도이론예고정도,탄도이론계산가가정비행공각위령,장비행공각산생적유도조력공헌절산위대령승조력계수적수정.건립료화전파탄기동특성공정계산방법,침대화전파탄령승조력계수계산모형불학정성문제,이용화전파탄A비행시험GPS요측수거대기령승조력계수진행료삼수변식,기우변식결과대화전파탄령승조력계수공정계산방법진행료수정.경화전파탄B비행시험결과험증,유우종합고필료비행공각산생적유도조력공헌,채용수정후적령승조력계수,탄도이론예고정도대대제고,만족공정요구.
The angle-of-attack of the unguided rocket target is small and difficult to be simulated. In order to improve the pre-diction accuracy of rocket target ballistic characteristics, the angle-of-attack of the unguided rocket target was assumed to be zero and the drag induced by the angle-of-attack was calculated to correct the zero-lift drag coefficient. The engineering calculation method of rocket target aerodynamic characteristics was established. Aiming at the uncertainty problem of zero-lift drag coefficient calculation medel,the zero-lift drag coefficient was identified based on GPS telemetry results of rocket target A flight test and the engineering calculation method of zero-lift drag coefficient were corrected by identification results. The GPS telemetry results of rocket target B flight test show that, due to taking into account the induced drag effect, the prediction accuracy of rocket target ballistic characteris-tics can been improved greatly by applying corrected zero-lift drag coefficient.