CAJ | 학술논문

为了根据空中飞行弹箭的一段实测弹道参数,准确预报弹道落点,并实施弹道修正,实现对目标的精确打击,在阐述弹道修正弹飞行原理的基础上,建立了扩展卡尔曼气动参数辨识弹道模型。该模型可对一段实测弹道参数进行弹道滤波,辨识出空中飞行弹丸的实际阻力和升力符合系数,并能较准确预报其后续飞行弹道。数值计算结果表明,经扩展卡尔曼弹道滤波后,能有效剔除测量弹道参数的噪声,且坐标滤波方差、阻力和升力符合系数迅速收敛；预报弹道落点的精度与飞行弹道参数的测量时间和采样时间间隔有关,考虑到实时弹道预报方法的预报弹道落点精度和解算时间等,飞行弹道参数测量时间宜取6~8 s,采样时间间隔宜在60~120 ms 范围内选取,为弹箭实现弹道修正提供了参考。
위료근거공중비행탄전적일단실측탄도삼수,준학예보탄도낙점,병실시탄도수정,실현대목표적정학타격,재천술탄도수정탄비행원리적기출상,건립료확전잡이만기동삼수변식탄도모형。해모형가대일단실측탄도삼수진행탄도려파,변식출공중비행탄환적실제조력화승력부합계수,병능교준학예보기후속비행탄도。수치계산결과표명,경확전잡이만탄도려파후,능유효척제측량탄도삼수적조성,차좌표려파방차、조력화승력부합계수신속수렴；예보탄도낙점적정도여비행탄도삼수적측량시간화채양시간간격유관,고필도실시탄도예보방법적예보탄도낙점정도화해산시간등,비행탄도삼수측량시간의취6~8 s,채양시간간격의재60~120 ms 범위내선취,위탄전실현탄도수정제공료삼고。
In order to accurately predict the traj ectory falling point according to a section measured traj ectory parameters of the flight proj ectiles and rockets so as to implement simple traj ectory correction and achieve precision strikes on the target,the extended Kalman aerodynamic parameters identification traj ectory model was established on the basis of elaborating the flight principles of traj ectory correction proj ectile.A section measured traj ectory parameters were filtered by model.The actual drag and lift coincidence coefficients of flight proj ectile were identified,and the subsequent flight traj ectory can be accurately predicted.The numerical results show that it can effectively remove the noise of measuring traj ectory parameters by extended Kalman traj ectory filtering,and the coordinate filtering variance,drag and lift coincidence coefficient converge quickly.The accuracy of predicted traj ectory falling point is related to the measuring time of flight traj ectory parameters and time sampling interval.Taking into account the accuracy of predicted traj ectory falling point and solving time of real-time traj ectory prediction methods,measuring time of flight trajectory parameters should rang from 6 s to 8 s,and the time sampling interval should be selected within the range of 60-120 ms.All the work offers reference for traj ectory correction of the proj ectile and rocket.