采用遗传算法的弹托迎风窝结构设计
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摘要
针对一体化弹丸弹托易分离性和轻质化的设计要求,构建弹托迎风窝参数化外形模型,基于激波和膨胀波理论建立弹托气动力计算模型;以弹托分离加速度和弹托质量综合最优为目标函数,采用遗传算法对弹托迎风窝的外形参数进行优化设计,从而得到弹托迎风窝的优化外形。以中口径尾翼稳定脱壳穿甲弹的弹托设计为例,采用提出的优化设计模型对其迎风窝结构进行优化设计,并采用基于动网格技术的弹托分离仿真模型验证其最优性。仿真结果表明:所提优化模型能够得到最优的弹托迎风窝结构;针对现有的中口径尾翼稳定脱壳穿甲弹,可进一步对其弹托结构进行优化,以提高其分离快速性。
Aiming at the design requirements of easy separation and light mass for the sabot of integrated launch projectile,an optimization design model was obtained by combining the aerodynamic calculation model by the genetic algorithm,in which the aerodynamic calculation model was established on the basis of the theory of shock and expansion wave through building the parameterized structure model for windward nest.And the discard acceleration and sabot's mass were used as the indicators to build performance function.Taking the sabot design of armor piercing fin stabilized discarding sabot of medium caliber as an example,the proposed optimization model was used for the optimum structural design of the windward nest,and the simulation model of sabot discard based on dynamic grid technique was adopted to verify the optimality.Simulation results show that the proposed optimization design model can obtain the optimal wind's eye of the sabot;in view of the existing armor piercing fin stabilized discarding sabot of medium caliber,the sabot structure can be further optimized to improve its rapidity.
Aiming at the design requirements of easy separation and light mass for the sabot of integrated launch projectile,an optimization design model was obtained by combining the aerodynamic calculation model by the genetic algorithm,in which the aerodynamic calculation model was established on the basis of the theory of shock and expansion wave through building the parameterized structure model for windward nest.And the discard acceleration and sabot's mass were used as the indicators to build performance function.Taking the sabot design of armor piercing fin stabilized discarding sabot of medium caliber as an example,the proposed optimization model was used for the optimum structural design of the windward nest,and the simulation model of sabot discard based on dynamic grid technique was adopted to verify the optimality.Simulation results show that the proposed optimization design model can obtain the optimal wind's eye of the sabot;in view of the existing armor piercing fin stabilized discarding sabot of medium caliber,the sabot structure can be further optimized to improve its rapidity.
引文
[1]William H,Richard D,Louise D.Sabot design for a 105 mm APFSDS kinetic energy projectile[R].Army Ballistic Research Lab Aberdeen Proving Ground MD,1978.
[2]Huang Z G,Wessam M E,Chen Z H.Numerical investigation of the three-dimensional dynamic process of sabot discard[J].Journal of Mechanical Science and Technology,2014,28(7):2637-2649.
[3]Erengil M E.An aerodynamic model for symmetric sabot separation[C]//Proceedings of 37th Aerospace Sciences Meeting and Exhibit,1999:AIAA 1999-992.
[4]Acharya R S,Naik S D.Modelling of shockwave force and its effect during sabot discard process[J].Defence Science Journal,2007,57(5):677-690.
[5]Acharya R S,Naik S D.Motion analysis during sabot opening process[J].Defense Science Journal,2007,57(2):229-241.
[6]于煜斌,张靖,王克勤.新型有翼弹托脱壳机理研究[J].兵工学报,2009,30(6):668-671.YU Yubin,ZHANG Jing,WANG Keqin.Research on the discarding characteristic of a novel sabot with wing[J].Acta Armamentarii,2009,30(6):668-671.(in Chinese)
[7]姬永强,陈小伟,黄含军,等.高速非稳定弹体次口径发射试验技术研究[J].弹箭与制导学报,2014,34(4):162-164,168.JI Yongqiang,CHEN Xiaowei,HUANG Hanjun,et al.Experimental technique of sub-caliber launch for high-speed unstable projectile[J].Journal of Projectiles,Rockets,Missiles and Guidance,2014,34(4):162-164,168.
[8]Guillot M J,Dick J N,Reinecke W G.Pressure distribution on sabots in hypervelocity flight[J].Journal of Spacecraft and Rockets,1997,34(3):279-285.
[9]Bhange N P,Sen A,Ghosh A K.Technique to improve precision of kinetic energy projectiles through motion study[C]//Proceedings of AIAA Atmospheric Flight Mechanics Conference,2009:AIAA 2009-5720.
[10]Gilchrist R L,Parker G B,Mishima J.Radiological and toxicological assessment of an external heat(burn)test of the105 mm cartridge,APFSDS-T,XM-744[R].Battelle Pacific Northwest Labs.,Richland,WA,1978.
[11]Nielsen J N,Hemsch M J,Smith C A.A preliminary method for calculating the aerodynamic characteristics of cruciform missiles to high angles of attack including effects of roll angle and control deflections:ONR-CR215-226-4F[R].USA:Office of Naval Research,Report,1977.
[12]郑锐,冯振明,陆明泉.基于遗传算法的无人机航路规划优化研究[J].计算机仿真,2011,28(6):88-91,152.ZHENG Rui,FENG Zhenming,LU Mingquan.Application of particle genetic algorithm to path planning of unmanned aerial vehicle[J].Computer Simulation,2011,28(6):88-91,152.(in Chinese)
[2]Huang Z G,Wessam M E,Chen Z H.Numerical investigation of the three-dimensional dynamic process of sabot discard[J].Journal of Mechanical Science and Technology,2014,28(7):2637-2649.
[3]Erengil M E.An aerodynamic model for symmetric sabot separation[C]//Proceedings of 37th Aerospace Sciences Meeting and Exhibit,1999:AIAA 1999-992.
[4]Acharya R S,Naik S D.Modelling of shockwave force and its effect during sabot discard process[J].Defence Science Journal,2007,57(5):677-690.
[5]Acharya R S,Naik S D.Motion analysis during sabot opening process[J].Defense Science Journal,2007,57(2):229-241.
[6]于煜斌,张靖,王克勤.新型有翼弹托脱壳机理研究[J].兵工学报,2009,30(6):668-671.YU Yubin,ZHANG Jing,WANG Keqin.Research on the discarding characteristic of a novel sabot with wing[J].Acta Armamentarii,2009,30(6):668-671.(in Chinese)
[7]姬永强,陈小伟,黄含军,等.高速非稳定弹体次口径发射试验技术研究[J].弹箭与制导学报,2014,34(4):162-164,168.JI Yongqiang,CHEN Xiaowei,HUANG Hanjun,et al.Experimental technique of sub-caliber launch for high-speed unstable projectile[J].Journal of Projectiles,Rockets,Missiles and Guidance,2014,34(4):162-164,168.
[8]Guillot M J,Dick J N,Reinecke W G.Pressure distribution on sabots in hypervelocity flight[J].Journal of Spacecraft and Rockets,1997,34(3):279-285.
[9]Bhange N P,Sen A,Ghosh A K.Technique to improve precision of kinetic energy projectiles through motion study[C]//Proceedings of AIAA Atmospheric Flight Mechanics Conference,2009:AIAA 2009-5720.
[10]Gilchrist R L,Parker G B,Mishima J.Radiological and toxicological assessment of an external heat(burn)test of the105 mm cartridge,APFSDS-T,XM-744[R].Battelle Pacific Northwest Labs.,Richland,WA,1978.
[11]Nielsen J N,Hemsch M J,Smith C A.A preliminary method for calculating the aerodynamic characteristics of cruciform missiles to high angles of attack including effects of roll angle and control deflections:ONR-CR215-226-4F[R].USA:Office of Naval Research,Report,1977.
[12]郑锐,冯振明,陆明泉.基于遗传算法的无人机航路规划优化研究[J].计算机仿真,2011,28(6):88-91,152.ZHENG Rui,FENG Zhenming,LU Mingquan.Application of particle genetic algorithm to path planning of unmanned aerial vehicle[J].Computer Simulation,2011,28(6):88-91,152.(in Chinese)