航空薄壁件铣削加工中保持工艺系统高刚性方法

针对航空铝合金薄壁工件铣削加工时易出现的颤振以及切削效率低的问题,从动力学角度出发进行了深入的分析研究,提出了通过采用保持工艺系统高刚性的加工过程工艺优化与铣削加工动力学仿真结合的方法进行铣削加工.试验结果证明本法可以收到很好的效果,较好地解决了航空铝合金薄壁结构工件加工的颤振问题,提高了工件的加工表面质量和切削效率.     

基于SLP方法的某支线客机尾锥生产线产能爬坡规划

为满足公司发展战略规划和客户交付数量增加的需求,采用系统性布局规划方法对尾锥生产线进行布局优化设计.首先,介绍了系统性布局规划(SLP)设计方法相关理论,并对尾锥生产线进行产能爬坡分析计算,包括生产线节拍平衡率计算、关键瓶颈工位识别、新增人力和关键设备分析;其次,利用物流相关图、空间关系图对尾锥生产线工装设备进行位置计...     

Old tail lobes effect on the solar-wind – Magnetosphere energy transport for the 27 August 2001 substorm

The magnetic flux of tail lobes Ψ is divided in two parts of comparable values Ψ₁ and Ψ₀₂, with the first that appears during substorm and the second, observed before substorm start. The first was named “new magnetic flux”, the second – “old magnetic flux”. The first, Ψ₁, is known to play a definitive role in the energy transport from the solar wind into the magnetosphere-ionosphere-atmosphere system, but the role of Ψ₀₂ in this transport is not well known. From the 27 August 2001 substorm data we study the involvement in the above transport process of the old flux Ψ₀₂. This involvement is observed in the polar cap (PC) area, which existed prior to the substorm and is called respectively “the old PC”. In this study, as distinct from earlier works, we use the balance equation of the energy stored in magnetosphere and energy consumed. Activation of the old PC magnetic flux Ψ₀₂ was found to increase the energy input by ∼85% in the event under consideration.     

自动制孔设备在某飞机尾翼装配中的应用研究

通过自动制孔技术在某飞机尾翼装配中的应用,介绍了自动制孔技术的特点。在自动制孔系统的应用过程中对其关键技术及相关工艺参数进行了试验研究,对比了自动制孔技术与传统制孔方法的效果。     

ISEE Ion Composition Data with Implications for Solar Wind Entry into Earth's Magnetotail

Energetic (0.1-16 keV/e) ion data from a plasma composition experiment on the ISEE-1 spacecraft show that Earth's plasma sheet (inside of 23 RE) always has a large population of H+ and He++ ions, the two principal ionic components of the solar wind. This population is the largest, in terms of both number density and spatial thickness, during extended periods of northward interplanetary magnetic field (IMF) and is then also the most "solar wind-like" in the sense that the He++/H+ density ratio is at its peak (about 3% on average in 1978 and 79) and the H+ and He++ have mean (thermal) energies that are in the ratio of about 1:4 and barely exceed the typical bulk flow energy in the solar wind. During geomagnetically active times, associated with southward turnings of the IMF, the H+ and He++ are heated in the central plasma sheet, and reduced in density. Even when the IMF is southward, these ions can be found with lower solar wind-like energies closer to the tail lobes, at least during plasma sheet thinning in the early phase of substorms, when they are often seen to flow tailward, approximately along the magnetic field, at a slow to moderate speed (of order 100 km s-1 or less). These tailward flows, combined with the large density and generally solar wind-like energies of plasma sheet H+ and He++ ions during times of northward IMF, are interpreted to mean that the solar wind enters along the tail flanks, in a region between the lobes and the central plasma sheet, propelled inward by ExB drift associated with the electric fringe field of the low latitude magnetopause boundary layer (LLBL). In order to complete this scenario, it is argued that the rapid (of order 1000 km s-1) earthward ion flows (mostly H+ ions), also along the magnetic field, that are more typically the precursors of plasma sheet "recovery" during substorm expansion, are not proof of solar wind entry in the distant tail, but may instead be a time-of-flight effect associated with plasma sheet redistribution in a dipolarizing magnetic field.     

导弹水下发射近筒口点火时机选择影响研究

潜射导弹蒸汽-燃气弹射出筒时,弹尾会附着燃气泡,该尾空泡的发展形态会对水下点火燃气射流流场的建立产生影响。为了研究水下发动机不同工作状态发射流场结构变化及原因,采用Mixture模型和动网格技术对发动机处于尾空泡的三种包覆状态:扩张初期、收缩初期、完全闭合状态(对应点火位置分别为2.2m,4.3m,6.5m)的燃气射流动态流场进行数值模拟。仿真结果表明,尾空泡收缩程度越大,发动机喷管流场结构越复杂,尾空泡不断地膨胀-颈缩,使得发射平台受到较大的压强脉动;当尾空泡未处于收缩状态阶段且发动机运动一定安全距离4.3m时点火,既有利于燃气射流流场的建立,同时发射筒及艇体受到的压力脉动最小,从而有效地提高了水下点火发射的安全性。     

翼刀腹鳍对JL8型飞机尾旋影响的计算和分析

针对ＪＬ８型飞机尾旋振荡模态特性,结合几种尾旋试飞操纵规律对ＪＬ８型飞机翼刀腹鳍进行了探索性地研究和计算。结果表明,带翼刀腹鳍构型并不是对所有尾旋模态都会有影响,而是在一定的操纵规律下有影响尾旋运动振荡特性的作用。     

再入弹头大攻角俯仰运动的非线性状态反馈控制

为提高大攻角飞行时具有非线性特性的姿态系统的控制精度,在弹头俯仰运动的非线性数学模型基础上,以弹头攻角为被控制信号,尾翼偏角指令为输入信号,设计了一种全状态反馈非线性姿态控制律,并进行了仿真试验。结果表明,所设计的控制律的稳态精度高、动态响应快。