针对无人机系统安全可靠性以及经济性的需求,对基于无人机的双余度飞控系统架构和工作方式进行了分析,研究了适用于无人机的双余度飞控系统信号监控表决策略,实现了双余度信号故障—安全的保障体系.与传统三余度或四余度飞控系统相比,基于双余度配置及监控策略的飞控系统具有结构更简洁、体积更小、重量更轻、经济性更好的特点,其安全可靠性满足中型或大型无人机系统研制需求.
介绍了国外飞机在使用维护中的功能检查试飞情况,指出了国内用户资料体系对功能检查试飞考虑的不足.提出了功能检查试飞的时机和原则,阐述了功能检查试飞程序和功能检查试飞检查单的编写要求,最后提出了某型机的功能检查试飞建议.
从非指令横向运动问题的分类及特征出发,剖析了造成该类问题的气动机理及其复杂性,并结合某型飞机试飞过程中所遇到的非指令横向运动问题及解决措施进行了分析,总结了新型高性能飞机研发中避免出现该类问题的注意事项.
针对某型飞机前作动筒密封试验时的漏气问题,通过对漏气处的密封结构进行分析研究,确定了影响密封性能的多项因素,设计了正交试验,根据试验结果准确定位到了导致漏气的关键因素,采取了有效的处理措施解决了漏气问题.
通过分析基于性能保障的国内外发展现状,借鉴国外基于性能的保障的实施经验,并结合我国目前保障体制现状,提出选择备件供应保障作为推行基于性能的保障的重要实施项目.从军方需求、工业部门需求、通用质量特性提升需求三个方面和物流信息、数字化客户服务系统、工业部门能力三个方面分别阐述了推行基于性能的备件供应保障的迫切需求和可行性.最后,提出了关于推进基于性能的备件供应保障改革的建议.
基于美军联合出版物JP3-09.3条令,将近距空中支援作战实施流程归纳为从飞机报到至攻击结束总共10项细分流程.通过作战实施流程,对协同过程中涉及的两大要素进行了分析,包括联合末端攻击控制员及支援飞机的发展历史及职责.最后对我国近距空中支援作战给出了发展建议.
机场安全是飞机飞行安全的关键研究环节之一,降低飞机安全事故发生的概率是机场管理部门努力的目标.过去曾发生过飞机冲出跑道事故,要避免此类事故的发生,除延长跑道长度之外,还可使用一新型民航机用拦截系统,即工程材料阻挡系统(Engineered Material Arresting System,EMAS),但该系统虽获得认可,还无法提供一套完整的评估流程供参考.本文着力于建立一个完整的评估模式,根据评估机场跑道长度提出改善方案,并对改善方案进行经济分析,以得出方案对机场、航空公司及旅客长期的经济影响.
通过分析某型号复杂整流蒙皮机构及其成形工艺特点,研究了拉形工艺参数以及拉形工装结构对零件表面质量的影响,改善了零件表面质量,减轻了工人劳动强度和对工人操作熟练程度的依赖,提高了零件生产效率,可以推广应用于复杂整流蒙皮的制造工艺.
某型航空活塞发动机在外场工作时发生了主连杆断裂故障,给发动机的使用带来安全隐患.通过对压杆失稳理论进行研究,探索出主连杆表面应变片贴片方案,进而提出了测试主连杆失稳临界载荷的电测试验法,可为同类型的故障分析提供参考.
空气炮是鸟撞试验的重要设施,为了使鸟弹能以指定的速度撞击试验件,提高试验的成功率,需要研究鸟弹在空气炮中的运行规律.现有的CFD软件能对流场进行数值计算,结合动网格技术,即可对动态问题进行求解.本文基于动网格对空气炮进行了数值计算,研究了鸟弹的运动规律,为空气炮设计和改进提供数据支持.
针对某型教练机机身整体油箱内部的钢制铆钉腐蚀问题,考虑油箱装配到使用的过程,结合腐蚀样品的理化测试结果,对油箱内钢制铆钉腐蚀的原因进行了分析,认为腐蚀的主要诱因为油箱内残余的水分.对比同系列其他架次飞机的钢制铆钉锈蚀情况,对此类问题排故与改进提出了建议.
研究了飞机在平飞加减速过程中高度变化的原因,提出了一种根据升降速率信号进行自动补偿的纵向自动配平控制方法,设计了纵向自动配平接通断开逻辑,并进行了六自由度仿真和稳定裕度分析,结果表明,平飞加减速过程中高度变化较小,稳定裕度结果满足GJB 2191-1994要求.
现代战争中,无人机已在火力校射、战场侦察监视、目标打击等方面显示出突出作用,成为对战场局势影响的最大因素,这与强大的无人机操控人员培训能力密不可分.本文在总结现代军用无人机的特点和培训需求基础上,研究提出了军用无人机操控人员的培训模式.
针对活塞杆零件局部镀硬铬在实际生产中存在的镀铬工序复杂和铬层质量较差的问题提出了解决办法.采用零件专用螺纹头夹具和热塑管对活塞杆进行装挂和绝缘,可以将镀铬工序优化为:绝缘保护→装挂→镀硬铬,减少了退铬工序;加强镀铬槽液的维护和镀铬过程的控制,配合使用绝缘保护套和阴极保护圈,得到的铬层厚度均匀,且镀铬区域与非镀铬区域界线清晰.
This paper introduces the logic control mode of 1553B bus main/backup control system in avionics system of a certain-type of aircraft and carries out cause analysis and location of the failure of 1553B main bus controller and the backup bus controller taking over the bus control which occurs in the field.
This paper discusses the design of flight simulator sound simulation system for a certain type of trainer, including system functions, hardware composition and software design. XAudio2 assembly is used to broadcast ambient noise and warning tones and realize the audio mixing. Audio frequency matrix is designed to realize communication control between pilot and instructor in front/rear cockpit. The sound effects produced by simulation enables the trainees to have a strong sense of immersion.
Using the multi-body dynamics software LMS Virtual.Lab, the calculation model of the whole aircraft mooring load of a certain type of aircraft is established, in which the whole aircraft mass inertia, the cushioning performance of landing gears, and the mechanical performance of the steel cable has been put into considerations. According to the requirements of the aircraft mooring design, calculation on the whole aircraft mooring dynamics under complex working conditions has been accomplished. This paper presents the study on the influence factors of steel cable loads and works out the optimal mooring scheme.
The dimension tolerance of parts may affect the assembly accuracy of vertical stabilizer that is used to maintain the heading stability. Traditionally, designers always distribute the tolerance of relative parts according to their experiences without considering the mutual effects between butt joints during assembly process. Therefore, interference happening between parts compels the operator to file and correct the parts.Considering the jointing interaction between front and rear spars on the basis of dimension chain, this paper analyzes the dimension chain tolerance of vertical stabilizer by using of limits and probability methods according to space transfer of dimension chain. It also optimizes the upper and lower deviations of part’s dimension until the clearance of parts is not less than 0mm. Therefore, the vertical stabilizer can be normally fitted with advanced assembly efficiency and reduced unnecessary weight.
Aiming at precise, non-destructive recovery requirements of a certain type of small fixed-wing UAV in complex environments, by summarizing and learning the mature experience and research achievements on the UAV recovery technology at home and abroad, this paper raises a vertical rotation recovery technical proposal adopting the principle of rotation deceleration. Based on this proposal, simple dynamics modeling of vertical rotation recovery is conducted preliminarily, UAV-arresting deceleration process is analyzed, and two key design parameters（i.e. damping moment coefficient and rotation arm length） in general technical proposal are discussed. This paper also qualitatively proposes an optimal thought on the design parameters.
