共查询到16条相似文献,搜索用时 125 毫秒
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研究表明,主动式射流涡流发生器可有效控制超声速流动边界层的分离,且能根据实际情况进行自适应调节。该文基于制式122尾翼弹,通过在弹肩前端加装射流涡发生器控制边界层的流动分离,研究其对尾翼弹气动性能的影响。采用DES方法数值模拟了超声速条件下尾翼弹有无射流控制的流场变化情况,分析了加装射流前后尾翼弹表面流体边界层结构及其气动性能的变化规律。数值结果表明,射流控制可有效抑制弹体表面的流体分离,提高尾翼弹的升力与俯仰力矩、减少弹身震动,有利于提高其飞行稳定性及打击精度,可为超声速尾翼弹的改进提供指导。 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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超声速弹箭表面的流体分离是影响飞行稳定的主要影响因素之一。研究表明,微楔涡流发生器可有效控制超声速流体边界层的流动分离。该文基于制式122火箭弹,通过在弹肩前端安装微楔来研究边界层流动分离控制对火箭弹气动性能的影响。运用DES方法数值模拟了122火箭弹在有无加装微楔条件下的流场变化,对比分析了微楔对弹体表面边界层结构以及弹气动数据的改变,讨论了微楔对弹的气动力及稳定性作用。数值结果表明,微楔可以抑制弹体表面流体分离,提高火箭弹的升力及俯仰力矩,减小马格努斯力矩,有利于提高其飞行稳定性及射击精度,可为相关旋转火箭弹的改进提供指导。 相似文献
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阐述了二维修正弹的力矩电机控制的两种方案,分析了PWM控制方案的优点.提出了十字型固定翼鸭舵的修正机构设计方案,并详细说明了鸭舵控制原理和控制过程.对弹道修正弹飞行各时段所受的力矩进行分析.对舵机修正力矩的计算与分析说明,该控制力矩电机方案是可行的. 相似文献
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以某坦克炮出现发射尾翼稳定杀伤爆破弹故障为背景,对可能引起该故障的因素进行了故障机理分析,通过计算得出了满足尾翼张开的最低膛压条件,建立了近弹故障树,并对故障树进行了定性分析,然后按照故障树对故障模式进行逐一的排查,对排查过程中尚不能确定的可能引起尾翼弹飞行故障的膛压不足的故障模式,用Matlab软件混合装药的膛压进行模拟仿真,验证了尾翼弹近弹的原因为混合装药配比不合适导致膛压不足。以初速和膛压为考察对象,用Matlab软件对混合装药条件下装药方案进行了优选设计,经试验验证,使用装药优选方案的杀伤爆破弹飞行正常。 相似文献
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《中国测试》2016,(9):83-87
为给固定鸭舵式二维弹道修正引信设计适用的半实物仿真系统,在掌握修正引信工作原理和研究引信运动状态的基础上,采用两部电机实时模拟引信修正组件和弹体滚转通道的姿态角信息,并使用光电码盘标定地磁测角模块的测角准确度,在过程控制软件的协调下实现弹上计算机和仿真计算机的数据交互,实现弹上机对固定舵制动控制的有效模拟。研究二维弹道修正引信半实物仿真试验的试验步骤,并针对某型迫弹进行仿真试验。仿真试验表明:所设计的半实物仿真系统可有效检验引信制导控制系统各分系统和整机的性能。该半实物仿真系统适用于安装该型引信的所有尾翼稳定弹箭,对其他类型的采用双旋结构的制导弹箭具有借鉴意义。 相似文献
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研究了滑翔增程弹气动布局对弹道增程效果的影响,建立了不同气动布局下的弹体模型,并对其进行气动仿真,得出了不同空气动力数据.通过建立适合增程弹的弹体模型,得到了舵片在不同布局时的增程能力数据.仿真结果表明,舵片位置越远离弹体头部,相应增大舵偏角,增程能力将会增强,因此,在满足全弹气动布局、飞行稳定的基础上,尽量使舵片远离弹体头部,并相应增大舵偏角,可提高増程的能力. 相似文献
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The whole process of formation, flying and penetration of explosively-formed projectile (EFP) is simulated by a 3D coupled hydrocode of Ls_dyna. The caliber of the shaped charge is 60 mm and EFP is a kind of overturned shaped charge. The Arbitrary Lagrangian–Eulerian (ALE) method is adopted to consider the fluid–solid coupling problem. The velocity attenuation equation is fitted to forecast the flight distance of EFP. The penetration property of EFP to the armor plate is studied by similarity theory and numerical simulation. For validating the equation, a test is designed to study the residual velocity after penetrating a 25 mm thick steel plate from a distance of 48 m. Therefore, some important solutions are obtained from the comparison of the simulation and experiment. The solutions are optimized charge structure of EFP, the ideal shape of projectile, the attenuation rule of flight process and the penetration property after 48 m flight. The numerical solution fits the experimental data well and the study results provide important reference to the design of EFP in engineering. 相似文献
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Because of the periodically varying aerodynamic and inertial forces of the flapping wings, a hovering or constant-speed flying insect is a cyclically forcing system, and, generally, the flight is not in a fixed-point equilibrium, but in a cyclic-motion equilibrium. Current stability theory of insect flight is based on the averaged model and treats the flight as a fixed-point equilibrium. In the present study, we treated the flight as a cyclic-motion equilibrium and used the Floquet theory to analyse the longitudinal stability of insect flight. Two hovering model insects were considered—a dronefly and a hawkmoth. The former had relatively high wingbeat frequency and small wing-mass to body-mass ratio, and hence very small amplitude of body oscillation; while the latter had relatively low wingbeat frequency and large wing-mass to body-mass ratio, and hence relatively large amplitude of body oscillation. For comparison, analysis using the averaged-model theory (fixed-point stability analysis) was also made. Results of both the cyclic-motion stability analysis and the fixed-point stability analysis were tested by numerical simulation using complete equations of motion coupled with the Navier–Stokes equations. The Floquet theory (cyclic-motion stability analysis) agreed well with the simulation for both the model dronefly and the model hawkmoth; but the averaged-model theory gave good results only for the dronefly. Thus, for an insect with relatively large body oscillation at wingbeat frequency, cyclic-motion stability analysis is required, and for their control analysis, the existing well-developed control theories for systems of fixed-point equilibrium are no longer applicable and new methods that take the cyclic variation of the flight dynamics into account are needed. 相似文献
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An experimental impact test of a 7.62 NATO projectile perforating a helicopter tail rotor shaft is briefly presented. With the aim to reproduce the operational worst case, the damage occurs during the flight, the impacted specimen is subsequently tested with a multiaxial testing machine. This procedure allows the evaluation of the capability of the shaft to withstand a recovery mission, which is simulated by applying a torsional fatigue spectrum to the shaft. The nucleation and propagation of fatigue cracks have been monitored during the test.Finite element analyses have been carried out to simulate both impact and crack propagation. The state of stress is multiaxial: it is induced by torque, residual stress field and shape of the damage. Mixed mode propagation has hence been considered by means of an equivalent SIF. Numerical results are in agreement with experimental data. 相似文献
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A projectile is stabilised using either gyroscopic or aerodynamic stability. But subcalibre projectiles with sabot have both
spin and fins. Separate stability criteria are researched generally for each type of projectile. In this paper a stability
criterion which can be used for all such bodies has been developed through the Liapunov second method. 相似文献
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在计转数空炸引信测试中,可编程引信作用距离是关键量,而全备弹丸飞行转动圈数则是求取该关键量的测量难题.在分析连续波雷达测量弹丸瞬时转速的工作原理基础上,针对小口径弹丸特点,建立了转速调制模型,提出利用数字解调、运动补偿等处理方法,基于微多普勒信息提取榴弹转速,由瞬时转速求得转动圈数,并对其中产生的误差进行了有效消除,实现了高精度定距空爆.方法在相关试验中得到了验证,为小口径空炸弹的系统考核与毁伤效力发挥提供了技术支撑. 相似文献