排序方式: 共有139条查询结果,搜索用时 15 毫秒
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首先,在研究飞行器背景磁干扰模型与小信号模型的基础上,分析了地磁梯度沿纬度与高度的变化规律,分析可知由于飞行器的机动,地磁梯度会对测量结果造成影响;然后,考虑地磁梯度因素,对原有小信号模型求解方法进行了改进:飞行器在四个航向上做小角度的机动飞行,将地磁场沿纬度与高度的梯度作为未知量,与飞行器磁干扰模型中的剩磁参数、感磁参数和涡磁参数一起求解;最后,利用实测试验数据进行了验证,结果表明:考虑地磁梯度的影响与不考虑地磁梯度的影响相比,求解的模型参数可以在细节上进一步提高飞行器背景磁干扰的补偿效果。 相似文献
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响应时间是磁流变阻尼器(Magnetorheological Damper,MRD)重要性能指标之一。为分析MRD响应时间及影响因素,建立了MRD动态响应模型,提出了一种基于Ansoft和Adams联合仿真分析MRD响应时间的方法,并通过仿真与试验相结合的方法分析了阶跃电流幅值、活塞运动速度以及系统刚度等因素对MRD响应时间的影响。仿真结果和试验数据表明:MRD响应时间随活塞速度和系统刚度的增大呈减小趋势,随阶跃电流幅值的升高呈增大趋势。同时证明通过联合仿真分析MRD响应时间和影响因素的方法是有效的。 相似文献
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针对以往战场环境中目标跟踪背景下多传感器调度算法收敛性差、求解精度低的问题,在CS算法(布谷鸟搜索算法)的基础上,提出了一种基于差分进化的布谷鸟搜索算法.在跟踪目标模型的基础上,以跟踪精度、任务完成率以及传感器资源能源消耗为指标,建立多传感器调度模型;借鉴差分进化思想,对布谷鸟搜索算法进行改进;利用改进后的布谷鸟搜索算法(DE-CS算法)求解传感器调度模型.将DE-CS算法与基础CS算法进行仿真比较,仿真结果表明,改进后的算法在收敛速度和精度方面都得到了有效改善,证明改进后的算法有较好的求解质量. 相似文献
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In this paper, the kerosene/air rotating detonation engines(RDE) are numerically investigated, and the emphasis is laid on the effects of total pressures and equivalence ratios on the operation characteristics of RDE including the initiation, instabilities, and propulsive performance. A hybrid MPI + OpenMP parallel computing model is applied and it is proved to be able to obtain a more effective parallel performance on high performance computing(HPC) systems. A series of cases with the total pressure of 1 MPa, 1.5 MPa, 2 MPa, and the equivalence ratio of 0.9, 1, 1.4 are simulated. On one hand, the total pressure shows a significant impact on the instabilities of rotating detonation waves. The instability phenomenon is observed in cases with low total pressure (1 MPa) and weakened with the increase of the total pressure. The total pressure has a small impact on the detonation wave velocity and the specific impulse. On the other hand, the equivalence ratio shows a negligible influence on the instabilities, while it affects the ignition process and accounts for the detonation velocity deficit. It is more difficult to initiate rotating detonation waves directly in the lean fuel operation condition. Little difference was observed in the thrust with different equivalence ratios of 0.9, 1, and 1.4. The highest specific impulse was obtained in the lean fuel cases, which is around 2700 s. The findings could provide insights into the understanding of the operation characteristics of kerosene/air RDE. 相似文献
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