卫星支援弹道导弹反航母作战研究

阐述了航母编队的作战特点,对反航母弹道导弹的情况进行了分析,在此基础上,研究提出了弹道导弹反航母对卫星支援的需求。该研究为卫星支援在联合作战中的发展提供一定的参考。     

基于微小型四旋翼飞行器的目标监测与识别综述

综述了微小型四旋翼飞行器的分类与关键技术,以及目标监测与识别的主要应用与重要过程.     

ICP—AES法测定飞机润滑油中7种微量元素

波音飞机润滑油中磨损金属含量极低并具有大量有机物基体。采用活性碳粉末,加入样品中进行干法灰化处理,所得灰分用ＨＣｌ：ＨＮＯ３＝２：１溶解后用ＩＣＰ－ＡＥＳ法测定,研究结果表明该法具有较小干扰,简便、准确。     

老龄飞机的腐蚀与控制

本文阐述了老龄飞机腐蚀的必然性和严重性，同时也提出了预防和控制老龄飞机腐蚀的一系列措施。     

基于逆向设计的飞机腹部整流罩设计

以塞斯纳208 B机身腹部行李舱为研究对象,在缺乏理论数据的基础上,通过三维扫描设备获取机身底部的点云数据;应用逆向设计技术和CATIA三维数字化设计软件完成该区域的外形曲面的建模,并重新设计行李舱整流罩,将设计结果应用到该飞机的摄影系统改装过程中,显著提高了设计效率和装配精度。     

飞机起落架主起外筒起飞降落过程中应力分布

对近几年大型飞机起落架主起外筒焊接部位失效原因及主起外筒焊接部位受力进行分析计算并获得了飞机起飞着落过程中主起外筒焊接部位承受冲击载荷在580 MPa范围内。并通过对主起外筒进行适当的简化并建立其相应焊接过程的有限元模型,利用有限元软件分析了冲击载荷对主起外筒焊接部位的影响,并确定了裂纹高发区为主起外筒顶端、第1条焊缝区域及第2条焊缝区域。结果表明在主起外筒顶端出现裂纹的几率最高,其次是两条焊缝区域。     

The effect of thermal exposure on the mechanical properties of 2099-T6 die forgings, 2099-T83 extrusions, 7075-T7651 plate, 7085-T7452 die forgings, 7085-T7651 plate, and 2397-T87 plate aluminum alloys

Aluminum alloys 2099-T6 die forgings, 2099-T83 extrusions, 7075-T7651 plate, 7085-T7452 die forgings, 7085-T7651 plate, and 2397-T87 plate were thermally exposed at temperatures of 180 °C (350 °F), 230 °C (450 °F), and 290 °C (550 °F) for 0.1, 0.5, 2, 10, 100, and 1000 h. The purpose of this study was to determine the effect of thermal exposure on the mechanical properties and electrical conductivity of these alloys. The data shows that higher temperatures and longer exposure times generally resulted in decreased strength and hardness and increased percent elongation and electrical conductivity.     

Accelerated corrosion test and corrosion failure distribution model of aircraft structural aluminum alloy

Based on corrosion damage data of 1 0 years for a type of aircraft aluminum alloy, the statistical analysis was conducted by Gumbel, Normal and two parameters Weibull distribution function. The results show that aluminum alloy structural member has the corrosion history of pitting corrosion--intergranular corrosion-exfoliation corrosion, and the maximum corrosion depth is in conformity to normal distribution. The accelerated corrosion test was carried out with the complied equivalent airport accelerated environment spectrum. The corrosion damage failure modes of aluminum alloy structural member indicate that the period of validity of the former protective coating is about 2.5 to 3 years, and that of the novel protective coating is about 4.0 to 4.5 years. The corrosion kinetics law of aluminum spar flange was established by fitting corrosion damage test data. The law indicates two apparent corrosion stages of high strength aluminum alloy section material： pitting corrosion and intergranular corrosion/exfoliation corrosion. The test results agree with the statistical fit result of corrosion data collected from corrosion member in service. The fractional error is 5.8% at the same calendar year. The accelerated corrosion test validates the corrosion kinetics law of aircraft aluminum alloy in service.     

A320系列飞机炭刹车盘钢夹结构的改进研究

本文通过对比分析几种常用的飞机炭刹车盘钢夹结构,提出了用于A320系列飞机炭刹车盘的改进钢夹结构,有效地减少了由于钢夹损坏造成未磨损到寿的炭刹车盘不能继续使用的情况,提高了炭刹车盘使用的可靠性.     

飞机涂层材料美国军用规范MIL-PRF-85285D浅析

对飞机涂层材料美国军用规范MIL-PRF-85285D所引用的相关规范和标准、自身关键 技术指标以及测试方法等内容进行了简要的分析,并对该规范的技术特点以及该规范对飞机涂层材料配方设计的要求进行了探讨.