制导炸弹半实物仿真系统误差对仿真结果的影响
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摘要
在制导炸弹半实物仿真试验中经常发现,同一发制导炸弹多次仿真的俯仰角差别较大,同一批次制导炸弹投弹试验的遥测俯仰角与仿真俯仰角差别也较大,但是俯仰角的收敛趋势均一致,实测脱靶量与仿真脱靶量都合格,且具有一致性。为了分析出现上述现象的原因,基于协方差分析描述函数法(CADFT),建立了制导炸弹半实物仿真系统的误差传播理论,计算了仿真姿态角和姿态角速度的误差。分析了仿真姿态角和姿态角速度的误差对仿真结果的影响。结果表明,在仿真系统各种误差中,气动力和气动力矩误差是主要误差,是引起仿真俯仰角差别的重要原因;姿态角的动态验模方法不适用于制导炸弹仿真模型,而脱靶量的静态验模方法适用于制导炸弹仿真模型。
In the process of guided bomb hardware-in-loop simulation test,the difference among pitch angle simulation results of the same bomb is larger,and the difference between pitch angle telemetering results and simulation results is also larger by one batch guided bomb,but the convergence of pitch angles is consistent,and the tested miss quantity and the simulated miss quantity are also consistent. Aiming at this problem,the error propagation theory of guided bomb hardware-in-loop simulation system was established based on the covariance analysis describing function technique( CADFT). The simulated attitude angle errors were calculated as well as the errors of attitude angle velocity. The influence caused by simulated attitude angle errors and attitude-velocity errors on simulation results was analyzed. The result shows that the aerodynamic force error and aerodynamic torque error are the main reasons causing the difference among pitch angle simulation results. The dynamic verification method by attitude angle isn't suit for guided bomb simulation model,but the static verification method by miss quantity is suitable.
In the process of guided bomb hardware-in-loop simulation test,the difference among pitch angle simulation results of the same bomb is larger,and the difference between pitch angle telemetering results and simulation results is also larger by one batch guided bomb,but the convergence of pitch angles is consistent,and the tested miss quantity and the simulated miss quantity are also consistent. Aiming at this problem,the error propagation theory of guided bomb hardware-in-loop simulation system was established based on the covariance analysis describing function technique( CADFT). The simulated attitude angle errors were calculated as well as the errors of attitude angle velocity. The influence caused by simulated attitude angle errors and attitude-velocity errors on simulation results was analyzed. The result shows that the aerodynamic force error and aerodynamic torque error are the main reasons causing the difference among pitch angle simulation results. The dynamic verification method by attitude angle isn't suit for guided bomb simulation model,but the static verification method by miss quantity is suitable.
引文
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[2]FILHO W C L,MALLAC L M R,CARRIJO D S.Hardware in the loop simulation of an attitude control system:AIAA 99-4323[R].Revo,NV:AIAA,1999:423-426.
[3]ANDRIANOS N,DIEZ C,DEMORE L A.Flight table orientation error transparency for hardware-in-the-loop facilities[J].SPIE,2001(4366):269-282.
[4]LOUIS A.Design study for a high-accuracy tree-axis test table[J].Journal of Guidance,2010(1):104-114.
[5]万士正.某型导弹半实物仿真系统误差建模及影响分析[J].指挥控制与仿真,2014,36(1):117-120.WAN Shizheng.Error model and influence analysis of hardwarein-loop simulation system for a certain missile[J].Command Control&Simulation,2014,36(1):117-120.(in Chinese)
[6]肖卫国.雷达寻的制导半实物仿真误差研究[J].计算机仿真,2007,24(5):259-263.XIAO Weiguo.Research on the error of hardware-in-loop simulation for radar homing guidance[J].Computer Simulation,2007,24(5):259-263.(in Chinese)
[7]丁长明.半实物仿真系统误差研究[J].航空兵器,1996(2):32-36.DING Changming.Research on the error of hardware-in-loop simulation[J].Aerial Ordnance,1996(2):32-36.(in Chinese)
[8]康凤举.水下航行器半实物仿真精度统计的CADFT法应用研究[J].系统仿真学报,1999,11(6):423-425.KANG Fengju.An applied study on accuracy analysis of hardwarein-loop simulation of underwater vehicle by CADFT[J].Journal of System Simulation,1999,11(6):423-425.(in Chinese)
[9]刘藻珍.系统仿真[M].北京:北京理工大学出版社,1998:193-203.LIU Zaozhen.System simulation[M].Beijing:Beijing Institute of Technology Press,1998:193-203.(in Chinese)
[10]袁子怀.有控飞行力学与计算机仿真[M].北京:国防工业出版社,2001:139-171.YUAN Zihuai.Control flight mechanics and computer simulation[M].Beijing:National Defense Industry Press,2001:139-171.(in Chinese)
[11]焦鹏.导弹制导仿真系统VV&A理论和方法研究[D].长沙:国防科学技术大学,2001:61-69.JIAO Peng.Research on the VV&A theory and method of missile guidance system[D].Changsha:National University of Defense Technology,2001:61-69.(in Chinese)
[12]徐明友.弹箭飞行动力学[M].北京:国防工业出版社,2003:7-20.XU Mingyou.Flight dynamics of missile[M].Beijing:National Defense Industry Press,2003:7-20.(in Chinese)
[13]闫章更.试验数据的统计分析[M].北京:国防工业出版社,2001:102-114.YAN Zhanggeng.Statistics and analyzing for test data[M].Beijing:National Defense Industry Press,2001:102-114.(in Chinese)