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1991年9月15~18日在沈阳飞机研究所召开了“歼8Ⅱ型飞机翼身组合体疲劳试验技术评审会”。由空军工程部可靠性办公室主持,来自航空航天部和空军的专家、学者共29人。 歼8Ⅱ型飞机翼身组合体疲劳试验是歼8系列飞机疲劳定寿的一项关键性试验项目。它将为歼8系列各型飞机机体结构的使用寿命提供试验依据;通过这项试验将进一步确定 相似文献
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本文是我从1956年至1964年间参加苏制飞机仿制、歼教一型飞机设计和美制F-86、F-4B飞机分析的总结,现结合歼八系列飞机的设计实践,作为科技讲座出版。 全篇共分6章,重点是第二章:设备舱的形式;第三章:设备安装形式分类与设计,对各 相似文献
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当第二代改型机和第三代战机成为中国空军的主要作战装备时,贵航集团基于第二代歼击机设计的歼教-7飞机已无法满足训练需求,迫切需要一种能够适应主战装备改装训练、过渡训练的新型高级教练机来担当重任.为此,贵航集团启动了"山鹰"飞机的研制. 相似文献
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某型飞机机翼防冰系统计算分析 总被引:5,自引:4,他引:1
主要针对某型飞机机翼的热气防冰系统计算分析,得到水滴直径变化对撞击极限的影响,飞行马赫数变化对机翼表面换热系数的影响,分析了不同飞行高度湿表面和干表面的温度分布.结果表明水滴撞击区随着水滴直径增加而增大;机翼表面的换热系数随飞行马赫数的增加而增加;在相同计算条件下,干表面温度比湿表面温度要高.对多个典型截面以及其在不同飞行状态的计算结果表明,在给定的计算条件下,4km及7km时防冰系统工作都是有效的,7km时表面部分位置湿表面温度低于0℃. 相似文献
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《国际航空》2005,(3):26-26
编者按:当前国际教练机市场十分看好.各国空军上世纪七八十年代装备的高级教练机面临退役,第三代或三代半战斗机逐步在各国空军机队构成中成为主流,对新型高级教练机的需求向市场发出了颇具诱惑力的呼唤.为此,各国航空企业纷纷推出新型高级教练机.国产军用教练机市场前景同样看好.我国空军目前装备的初级、中级、高级教练机分别为初教6、JL8和歼教7.空军正在换装第三代战斗机,而作为第二代战斗机的同型教练机,歼教7很难承担新时期通用高级教练机的任务,且第三代战斗机均有其双座型可作为教练机使用,歼教7已无法满足空军的要求.因此,研制一种通用的高级教练机来满足新时期空军飞行训练的需求,成为中国航空工业企业十分关注的商机.为此,贵州航空工业集团公司和洪都航空工业集团公司,分别发展了两款高级教练机,即JL9"山鹰"和L15"飞狮,拉开了中国航空整机产品市场竞争的帷幕,同时也是中国航空企业全面走向市场经济的重要一步. 相似文献
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With the evaporation of funding support for the National Aero Space Plane (NASP), realization of a single stage to orbit night system has been deferred. With the resource down sizing of the NASP management and technical team, development of the NASP concept appears to be delayed beyond the year 2030. To fill this gap for shorter flight times to remote destinations over 8,000 km, it is now proposed to convert the existing NASA shuttle to a passenger configuration and air launch horizontally from a Boeing 747 aircraft as the first stage carrier after climb to launch altitude. This US Shuttle concept may permit the transport of 100 passengers to destinations 10,000 km distant during a flight duration of 90 minutes, and during flight durations of about 120 minutes to any commercial destination on the planet Earth. This long distance system takes advantage of the existing shuttle and Boeing 747 airframe and propulsion technology, and can be implemented within the next decade 相似文献
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本文讨论弹性飞机的纵向稳定性问题。包括带与不带飞行控制系统两种情况。文中通过算例,分析讨论弹性飞机的总体运动模态和弹性运动振型之间的藕合以及弹性飞机本身和飞行控制系统之间的耦合。分析与计算表明,带有飞行的控制系统的飞机,其结构弹性变形运动对纵向稳定性的影响,即使对于算例中的“小”飞机,也是不可忽视的。飞机的弹性影响,不但会降低飞机的飞行品质,有时还会引起飞机与系统之间的耦合不稳定。 相似文献
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Manoeuvre Load Alleviation (MLA) is the concept of redistribution of forces and moments on airframe through optimal actuation of control surfaces. The effect is to minimise the stresses near wing root and improve fatigue life of airframe components, such as, the frequently studied wing root fitting connecting wing to the fuselage. The configuration is a typical tailless delta wing aircraft having inboard and outboard Elevons (a combination of Elevator and Aileron) placed symmetrically on starboard and port side. The problem is formulated as minimisation of independent conflicting multiple objectives of wing root bending and twisting moments, with stability equations as equality constraints and actuator hinge moments as inequality constraints. Hybrid method is used as optimisation technique, which is evolved from the combination of heuristic based Elitist non-dominated Sorting Genetic Algorithm (NSGA-II) and calculus based Goal Programming methods. The primary objective of this paper is to bring out the structural benefits attainable for some of the combined critical manoeuvre load cases at subsonic and supersonic flight points. The combined critical manoeuvre load cases demarcate the limit to which airframe is loaded. The minimisation achieved is better for flight points at supersonic as compared to subsonic Mach numbers. 相似文献
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民机机体噪声及其降噪研究 总被引:2,自引:1,他引:1
分析了机体噪声源的主要机理及其基本性质。机体噪声由绕起落架装置和高升力系统的流动引起的压强脉动产生。起落架和前缘缝翼产生的基本上是宽频噪声,它们和襟翼的宽频噪声的强度分别随速度的6次方、4.5次方和5次方变化。实际飞行中还应注意存在的"寄生"噪声。此外,较为详尽地讨论了包括QTD II、RAIN、SILENCE(R)和TIMPAN等降噪措施在内的研究项目及其可获得的效果,还讨论了噪声的计算方法,介绍了国外航空界提出的未来民机需降噪的目标,表明民机设计面临降噪的巨大挑战。 相似文献
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A型飞机机翼主梁结构的使用寿命研究 总被引:1,自引:0,他引:1
确定A型飞机机翼主梁结构的使用寿命,是保证A型飞机使用安全的关系。通过对全机第一关键危险部位-机翼主梁下凸缘第2螺栓孔部位的寿命估算、模拟件疲劳对比试验、模拟件耐久性试验,全机疲劳试验,经过综合分析研究,得到A型飞机机翼主梁结构的使用寿命满足3000飞行小时的结合。这一结论为全机使用寿命的确定奠定了基础。而全机使用寿命的确定是A型飞机生产定型的重要依据,也是对现役A型飞机进行维护及大修的重要依据。 相似文献
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Shapiro E.Y. Schenk F.L. Decarli H.E. 《IEEE transactions on aerospace and electronic systems》1979,(2):245-252
The feasibility of providing flight control systems with software-managed redundancy is investigated. It is shown that sufficient information can be extracted from aircraft attitude sensors to allow analytic reconstruction of the stability augmentation system (SAS) sensor signals in the event of SAS sensor failures. The sensor signal reconstruction is performed in a deterministic setting by using a Luenberger observer. A simple and efficient design procedure is presented based on Gopinath's [1] work. As an illustrative example, the proposed sensor signal reconstruction technique is exercised on the L-1011 aircraft lateral axis rigid body simulation. It is shown that with an accurate airframe model perfect reconstruction is feasible. In addition, it is also shown via simulation results that with imperfect knowledge of the airframe model (based on standard wind tunnel data), the proposed reconstruction is accurate enough to have a negligible impact on the overall aircraft performance. 相似文献
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《Progress in Aerospace Sciences》2005,41(3-4):175-191
This paper provides a review of the out-of-ground-effect propulsion-induced interference on the aerodynamics of jet-lift short take-off and vertical landing (STOVL) aircraft. Two main flight regimes are discussed; hover and transition wherein the main fluid dynamics phenomena that cause the interference are presented. Where possible, an engineering assessment is made of the effect of jet and/or airframe configuration parameters on the observed interference effects. 相似文献
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Switched Ethernet testing for avionics applications 总被引:1,自引:0,他引:1
Switched Ethernet is being implemented as an avionics communication architecture. A commercial standard (ARINC-664) and an aircraft vendor-specific implementation known as avionics full duplex switched Ethernet (AFDX) have been developed that defines the topology and use of switched Ethernet in an avionics application. In avionics applications, the movement of data between devices must take place in a deterministic fashion and must be delivered reliably. All aircraft flight hardware must be tested to be sure that it will communicate information properly in the switched Ethernet network. The airframe manufacture must test the integrated network to verify that all flight hardware is communicating properly. Testing and maintenance testing is required to perform data communication level testing of switched Ethernet architectures for avionics applications to insure that all communication is deterministic and reliable. This paper provides an overview of a switched Ethernet avionics network and identifies the testing challenges associated with a switched Ethernet avionics application. A practical implementation performing the required tests is discussed. 相似文献