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正确选择军用飞机型号研制合同的类型,对促进型号研制合同的签订和 型号任务的顺利完成,使使用方能以合理的费用,获得性能优良的武器装备有重要意义。本文探讨了型号研制的固定价格合同和成本补偿合同的特点及适应范围,以及选择合同类型时应注意的几个问题。 相似文献
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马占永 《航空标准化与质量》1988,(3)
由六三○所主编的《军用飞机科研试飞训练要求》、《军用飞机科研试飞复杂科目》、《军用飞机科研试飞风险科目》、《军用飞机科研试飞等级标准》、《军用飞机科研试飞代号》五项国家军用标准审查会于4月17日至21日在北京召 相似文献
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郭之鑫 《民用飞机设计与研究》2020,(4):125-131
飞行模拟机数据包试飞用于获取飞行模拟机研制及鉴定所需的试飞数据,涉及多项试飞科目。为提高试飞效率、降低试飞成本,针对飞行模拟机数据包试飞与型号试飞的优化结合方法进行了研究。通过分析飞行模拟机研制进度要求、型号试飞规划、型号构型到位计划,以及飞行模拟机数据包试飞和型号试飞各试飞科目的试飞要求等要素,分别在试飞科目分析阶段和试验点分析阶段提出了不同的优化结合原则,包括试飞方法相似原则、科目类别相似原则、前置试验满足原则及构型要求兼顾原则。并给出了直接结合、试验点连续结合、形态变换结合及架次结合四种优化结合方法,以及优化结合方法所适用的飞行模拟机数据包试飞阶段。该优化结合方法已在实际型号飞行模拟机数据包试飞任务规划中得到应用,起到了减少试飞任务量的作用。 相似文献
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军用飞机飞行载荷计算方法研究 总被引:5,自引:0,他引:5
以《军用飞机强度和刚度规范—总则》(GJB67.1-85)为标准,以《军用飞机强度和刚度规范—飞行载荷》(GJB67.2-85)、《军用飞机强度和刚度规范—其它载荷》(GJB67.3-85)为指南,结合型号研制,提出一套军用飞机飞行载荷计算方法,并开发了“军用飞机飞行载荷计算分析软件”,该方法及软件在型号研制中得到应用。 相似文献
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论述了军用飞机新机调整试飞应具备的条件、调整试飞内容、调整试飞目的、调整试飞基础文件、调整试飞应完成的工作、调整试飞结果文件,同时对调整试飞质量、调整试飞效益、新机调整试飞特点和有效开展军用飞机新机调整试飞等问题展开了讨论。 相似文献
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针对军用飞机标准件研制管理现状,充分借鉴军用飞机、机载设备研制程序和管理要求,以及相关型号标准件研制管理经验,研究确定了某型飞机标准件研制管理与应用规定,明确了职责与分工、细化了工作流程、内容和要求。 相似文献
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根据军用飞机试飞验证技术特点及标准需求,分析了试飞验证标准化存在的问题;基于标准化的原理、方法,提出了开展试飞验证标准的顶层规划,进行试飞验证标准体系建设,以及开展标准论证、标准编制方法、标准技术内容确定方法等军用飞机试飞验证标准化工作的技术途径,并提出了试飞验证标准的贯彻和应用等标准化工作的内容和方法,为军用飞机试飞验证技术标准化提供了借鉴和指导。 相似文献
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运载火箭研制费用估算是费用管理中的一个重要环节。正确估算研制费用对于方案选优、加强研制过程中的费用管理以及估算整个寿命周期的费用等都具有十分重要的意义。参考美国国家宇航局( NASA )的费用估算关系( CER )模型,提出了基于运载能力、起飞质量、外形尺寸等参数的参数-费用估算模型。鉴于我国运载火箭样本少的实际情况,采用偏最小二乘法( PLS)对该模型进行了实证检验,估计值与真实值之间的偏差较小,估计效果比较理想。为下一步运载火箭研制方案筛选和费用管理提供了依据。 相似文献
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NING Guo-dong ZHANG Shu-guang FANG Zhen-ping 《中国航空学报》2007,20(1):1-8
A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor, and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty. Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertain-ties are presented to demonstrate the capacity and reliability of this method. 相似文献
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基于飞机油箱模型形状特征油量测量切片步长选择方法研究 总被引:1,自引:0,他引:1
在分析飞机数字式油量测量过程中目前广泛使用的切片法油量测量原理的基础上,针对现有的定步长切片法无法得到准确、可靠的燃油质量特性数据库的缺陷,结合对飞机油箱模型形状特征的分析,提出了基于飞机油箱模型形状特征的油量测量切片步长选择方法。此方法包括切片步长整体和局部选择两个过程,整体选择以实现相邻两切片平面所夹油箱模型体积近似相等为目的来确定切片步长,以体现油箱模型截面整体变化规律;局部选择以设计切片平面与截面突变平面重合或尽可能接近的方式,突出油箱截面的局部变化特征。实验结果表明:该切片步长选择方法较定步长方法能够建立更为合理、可靠的燃油质量特性数据库,从而提高了油量测量精度。 相似文献
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The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow 总被引:1,自引:0,他引:1
This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation. 相似文献
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Abnormal Shape Mould Winding 总被引:1,自引:0,他引:1
Fu Hongya Wang Xianfeng Han Zhenyu Fu Yunzhong 《中国航空学报》2007,20(6):552-558
为解决网格化芯模的缠绕问题,本文提出了复合材料面片缠绕机理;接着详细分析了面片缠绕过程中的芯模凹曲面上纤维滑线和架空现象,应用微分几何曲面理论和空间几何理论,提出判据及其解决方案;最后,针对飞机发动机进气道的缠绕成型,编制缠绕控制程序并进行相应的实验,验证了面片缠绕方法的可行性。 相似文献
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FU Hong-jun MA Chong-qi KUANG Nai-hang LUAN Shi-lin 《中国航空学报》2007,20(2):124-128
This work was dedicated to performing surface oxidation and coating treatments on carbon fibers (CF) and investigating the changes of fiber surface properties after these treatments, including surface composition, relative volume of functional groups, and sur- face topography with X-ray photoelectron spectroscopy (XPS) and atom force microscopy (AFM) technology. The results show that, after oxidation treatments, interfacial properties between CF and non-polar polyarylacetylene (PAA) resin are remarkably modified by removing weak surface layers and increasing fiber surface roughness. Coating treatment by high char phenolic resin solution after oxida- tion makes interface of CF/PAA composites to be upgraded and the interfacial properties further bettered. 相似文献
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Xu Chenghai Meng Songhe Zhang Mingfu Zuo Hongbo Wang Guigen 《中国航空学报》2007,20(5):475-480
本文利用有限元法对冷心放肩微量提拉法(SAPMAC)生长大尺寸蓝宝石单晶过程中的热应力进行了模拟计算,应用临界缺陷理论解释了裂纹的萌生与扩展机理。研究表明,晶体内的热应力主要与晶体生长速率,环境温度和结晶取向有关;较大热应力多出现在结晶界面,放肩、收尾以及直径急剧变化等位置;最大热应力总是出现在籽晶与新生晶体的界面附近。裂纹将在临界缺陷位置产生,并在应力作用下沿a或m面扩展。计算结果与实验结果基本吻合,通过晶体生长系统和生长工艺的改进,对晶体的开裂问题得到了有效的抑制。 相似文献
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CHENG Wen-yuan CHANG Yan CUI De-gang XIE Xiang-hui 《中国航空学报》2007,20(1):55-59
To solve the topology optimization of complicated multi-objective continuous/discrete design variables in aircmit structure design, a Parallel Pareto Genetic Algorithm (PPGA) is presented based on grid platform in this paper. In the algorithm, the commercial finite element analysis (FEA) software is integrated as the calculating tool for analyzing the objective functions and the filter of Pareto solution set based on weight information is introduced to deal with the relationships among all objectives. Grid technology is utilized in PPGA to realize the distributed computations and the user interface is developed to realize the job submission and job management locally/remotely. Taking the aero-elastic tailoring of a composite wing for optimization as an example, a set of Pareto solutions are obtained for the decision-maker. The numerical results show that the aileron reversal problem can be solved by adding the limited skin weight in this system. The algorithm can be used to solve complicated topology optimization for composite structures in engineering and the computation efficiency can be improved greatly by using the grid platform that aggregates numerous idle resources. 相似文献