共查询到18条相似文献,搜索用时 137 毫秒
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研究了增程弹丸气动布局对弹道增程效果的影响,主要是针对弹丸有无舵片以及安装舵片的位置两种情况分析,建立对应的弹体模型,并对其进行气动仿真,得出相应的升力系数和阻力系数,并计算出升阻比,进而判断有无舵片以及舵片的安装位置对弹道增程效果的影响.仿真结果表明:有舵片相对无舵片的弹丸增程效果明显,升阻比最多增加25.17%,最少增加0.49%;舵片安装位置不同,其增程效果也存在明显差异,并且升阻比在距离弹头90 mm时增加最为明显.因此认为在满足全弹气动布局、飞行稳定的基础上,在弹丸适当位置安装舵片并相应改变攻角,可有效增加弹丸射程. 相似文献
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气动喷射阀是微电子封装中不可或缺的封装设备,但现有气动喷射阀在喷射高黏胶液时仍不能完全满足工业界对胶滴一致性的需求,原因在于其喷射高黏胶液时常出现因喷射速度太小而导致的挂胶漏喷现象.要减小上述现象的发生概率,就必须提高现有气动喷射阀的高黏流体喷射能力.回流间隙作为气动喷射阀的关键尺寸,直接影响着喷射阀的喷射能力.为了通过优化回流间隙来提高喷射能力,首先建立气动喷射阀的胶液喷射数值仿真模型并通过实验验证其可靠性,同时基于不同回流间隙的仿真数据建立了相应的高斯拟合模型.然后利用拟合模型以胶滴滴落速度为优化目标对回流间隙进行优化,通过优化前后的喷射对比验证了优化结果的可靠性,最后获得气动喷射阀的最优回流间隙. 相似文献
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进行了小口径尾翼修正弹气动外形设计,并对其进行气动仿真,得出了阻力、升力、翻转力矩、导转力矩等空气动力数据.在分析小口径尾翼修正弹气动特性的基础上,对其大量气动数据进行方程拟合.通过气动和动力学仿真,模拟修正弹修正过程,对小口径尾翼修正弹飞行稳定性和修正能力进行分析.仿真结果表明,在满足全弹气动布局、飞行稳定、电机有效控制的条件下,经气动外形设计的小口径尾翼修正弹具有良好的飞行稳定性和修正能力. 相似文献
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针对燃气舵在启动瞬间会产生很大的冲击力,采用ADAMS和ANSYS软件对传动机构进行了动力学分析和有限元分析的联合仿真,得到了变负载下相邻零件的冲击力,并分析了危险零件的瞬态动力响应。分析结果表明,在一定范围内,冲击力随响应时间的增加响应速度变慢,最大值和最小值分别基本保持一致。建立了燃气舵系统的数学模型,在MATLAB Simulink软件中进行了系统的比例-积分-微分(proportional-integral-derivative, PID)控制仿真分析,并基于仿真结果进行了单片舵系统的运动控制试验。试验结果表明,该控制平台能达到良好的控制效果。 相似文献
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带偏角环形聚能装药射流汇聚性能研究 总被引:1,自引:0,他引:1
利用LS-DYNA软件对带偏角环形聚能装药射流的二次汇聚进行了数值模拟,研究了汇聚射流的质量和环形药型罩的锥角对射流汇聚性能的影响,并进行了试验验证。结果表明:带偏角环形聚能装药可提高药型罩材料转化为射流的转化率,增大射流的连续拉伸长度和头部速度,增强射流的稳定性;二次汇聚射流头部速度随着药型罩锥角的增大而减小,头部直径随着锥角的增大而增大;对于偏角为15°的药型罩,当锥角为40°时产生的汇聚射流头部空腔较小,破甲能力较好。研究结果可为环形聚能装药的工程设计提供参考。 相似文献
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为了研究集束式扩孔气动冲击器的排屑性能。建立了其排屑流场模型,运用计算流体力学理论和FLUENT仿真软件,对气固两相流场进行仿真计算,并进一步分析冲击器不同钻进速度和尾气质量流量对其排屑能力的影响,得到排屑流场气相特性规律,岩屑分布规律,不同钻进速度和入口气相质量流量下的颗粒浓度分布。研究结果表明:冲击器排气孔尾气进入排屑流场后流速降低,流场压力由入口到出口呈梯度分布且逐渐降低;岩屑颗粒向流场底部聚集,颗粒平均浓度沿着远离入口方向变化不大,最大浓度沿着远离入口方向逐渐下降,最终趋于平稳;施工时最大钻进速度应低于8.4m/h,增大尾气质量流量排屑能力增强。 相似文献
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针对飞行器升降舵、副翼角运动的测试需求,提出了单轴捷联姿态系统的原理及算法,介绍了基于MEMS陀螺仪和加速度计的舵面运动测量仪的构成,并对测量仪的工作过程进行了仿真.仿真表明,测量仪的性能满足舵面运动测量的需要. 相似文献
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Jialei Song Jorn A. Cheney Richard J. Bomphrey James R. Usherwood 《Journal of the Royal Society Interface》2022,19(187)
Aerodynamic functions of the avian tail have been studied previously using observations of bird flight, physical models in wind tunnels, theoretical modelling and flow visualization. However, none of these approaches has provided rigorous, quantitative evidence concerning tail functions because (i) appropriate manipulation and controls cannot be achieved using live animals and (ii) the aerodynamic interplay between the wings and body challenges reductive theoretical or physical modelling approaches. Here, we have developed a comprehensive analytical drag model, calibrated by high-fidelity computational fluid dynamics (CFD), and used it to investigate the aerodynamic action of the tail by virtually manipulating its posture. The bird geometry used for CFD was reconstructed previously using stereo-photogrammetry of a freely gliding barn owl (Tyto alba) and we validated the CFD simulations against wake measurements. Using this CFD-calibrated drag model, we predicted the drag production for 16 gliding flights with a range of tail postures. These observed postures are set in the context of a wider parameter sweep of theoretical postures, where the tail spread and elevation angles were manipulated independently. The observed postures of our gliding bird corresponded to near minimal total drag. 相似文献
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依据弹道修正基本原理,对弹道修正装置的气动布局进行分析.完成了弹道修正机构中永磁电机的设计,并对永磁电机齿槽力矩的影响因素进行分析.通过仿真,减小硅钢片槽口宽度可以减小永磁电机的齿槽力矩.利用应变式测力装置,对永磁电机的力矩实际测量可知,修正弹飞行在可修段时永磁电机的力矩大于风阻力矩的20%.结果表明,设计的永磁电机能够满足对舵机的精确控制要求. 相似文献
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As the use of complex multi-layer structures in defense, marine, aerospace and automotive applications becomes increasingly common, it is vital that the response of such structures to impact loading is better understood and that engineers have adequate analysis tools to design structures optimised for resistance to ballistic penetration. This paper presents the results of a series of ballistic impact experiments carried out on a range of spaced multi-layer fibre reinforced-plastic (FRP) composite targets, with a constant total number of plies per target, but varying numbers of plies per layer and varying layer arrangements. It is shown that varying the ratio of plies between layers can have a significant effect on resistance to ballistic penetration. In light of these experimental results, the validity of applying the Lambert–Jonas equation to spaced multi-layer structures is discussed and an extended framework developed to determine the ballistic limit of a projectile impacting such a structure. The extended Lambert–Jonas framework is then validated with data from the literature. It is hoped that this framework will allow engineers to quickly determine the optimum layer arrangement to maximise the ballistic resistance of complex spaced multi-layer structures. 相似文献
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使用Abaqus/Explicit有限元分析软件,开展平头弹撞击不同厚度双层TC4钛合金板数值模拟,研究双层TC4钛合金板撞击失效特性与失效模式随厚度变化规律及机理。通过对比撞击试验与仿真结果,验证数值模型和参数的有效性。在此基础上与等厚度单层TC4钛合金板的抗侵彻性能进行对比,结果表明,对于12.68 mm直径的平头弹,在靶板厚度2~16 mm内,双层结构的弹道极限与总厚度近似呈线性关系。由于单层靶板在4~10 mm内随着厚度增加,弹道极限无明显变化,所以等厚接触式双层结构在该厚度范围相比单层靶有明显的优势。在总厚度为8 mm时,双层靶优势最为明显,弹道极限相比单层靶提高了43%左右。 相似文献
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《Composites Part B》2004,35(4):291-297
The ballistic perforation test results of 4-step 3-dimensional (3D) braided Twaron®/epoxy composites, which were subjected to impact by conically cylindrical steel projectile, are presented. The residual velocities of projectile perforated composites target at various strike velocities were measured and also compared with that from finite element calculation. ‘Fiber inclination model’ for 3D textile composites was adopted to decompose the 3D braided composite at quasi-microstructure level for the geometrical modeling in preprocessor of FEM. The material modeling was also based on this simplified model. The finite element code of Ls-Dyna was used to simulate the impact interaction between projectile and inclined lamina. The residual velocity of projectile perforating the entire 3D braided composite can be calculated from the sum of kinetic energy loss of the projectile that obtained from FEM. From the simulation of ballistic penetration process and comparison between numerical results and experimental results, it proves that the analysis scheme of quasi-microstructure level in this paper is valid and reasonable. The simplified method in this paper could be extended to model other kinds of 3D textile composites under ballistic impact. 相似文献
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针对小口径高射频串联发射弹丸的内弹道力学特性测试问题,提出了基于弹载存储测试技术的弹底压力、弹前压力同步测试方法。设计了模拟弹和小型聚偏二氟乙烯(polyvinylidene difluoride, PVDF)压电式力传感器,将力传感器作为底螺与头螺部件承受并测量弹底压力与弹前压力,在发射过载条件下进行了传感器力学分析并推导了受力与输出的关系方程;分析了传力块的质量、厚度,PVDF薄膜的厚度、面积对传感器动态特性和温升的影响;进行了力传感器灵敏度理论建模与分析并开展了标定试验。结果表明,PVDF薄膜预紧力越大,传感器灵敏度越小。开展了串联发射试验,测试结果和内弹道数值模拟计算结果吻合较好。 相似文献
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考虑攻角的长杆弹斜穿透中厚铝靶机理 总被引:1,自引:0,他引:1
攻角对长杆弹斜侵彻有重要影响,该文通过大量数值模拟研究了攻角对长杆弹斜穿透中厚铝板的影响机理。基于实验验证的有限元模型,开展了变速度和攻角的多工况数值模拟,得到了侵彻过程中弹体的减加速度大小、速度方向以及整体弯曲的变化规律,分析了侵彻速度、倾角和攻角对侵彻阻力、弹体弯曲和弹道偏转的影响。结果表明:带攻角斜侵彻时,负攻角对弹体弯曲的影响明显大于正攻角,且弹体弯曲随着侵彻速度的增大而减小;随着斜侵彻速度的增大,攻角引起弹体甩尾和弹道偏转越明显,此时带攻角的斜侵彻过程的能量损耗机理明显不同于正侵彻和无攻角的斜侵彻。 相似文献