对我公司开发民用产品的几点思考

分析了南飞公司民品开发中存在的问题及其产生原因；提出开发民品的对策和措施；探讨了开发民品的几种方法及应做好的几项基础工作。     

民航高技能人才培养现状调查分析

通过对广州民航职院1100余名学生的问卷调查,了解了学生对高技能人才的认识情况,掌握了民航高技能人才在培养目标、专业设置、课程结构、教学改革、师资水平的培养现状及存在的问题,并针对调查结果,提出了加强民航高技能人才培养的对策与建议。     

Regression model for civil aero-engine gas path parameter deviation based on deep domain-adaptation with Res-BP neural network

The variations in gas path parameter deviations can fully reflect the healthy state of aero-engine gas path components and units; therefore, airlines usually take them as key parameters for monitoring the aero-engine gas path performance state and conducting fault diagnosis. In the past, the airlines could not obtain deviations autonomously. At present, a data-driven method based on an aero-engine dataset with a large sample size can be utilized to obtain the deviations. However, it is still difficult to utilize aero-engine datasets with small sample sizes to establish regression models for deviations based on deep neural networks. To obtain monitoring autonomy of each aero-engine model, it is crucial to transfer and reuse the relevant knowledge of deviation modelling learned from different aero-engine models. This paper adopts the Residual-Back Propagation Neural Network (Res-BPNN) to deeply extract high-level features and stacks multi-layer Multi-Kernel Maximum Mean Discrepancy (MK-MMD) adaptation layers to map the extracted high-level features to the Reproduce Kernel Hilbert Space (RKHS) for discrepancy measurement. To further reduce the distribution discrepancy of each aero-engine model, the method of maximizing domain-confusion loss based on an adversarial mechanism is introduced to make the features learned from different domains as close as possible, and then the learned features can be confused. Through the above methods, domain-invariant features can be extracted, and the optimal adaptation effect can be achieved. Finally, the effectiveness of the proposed method is verified by using cruise data from different civil aero-engine models and compared with other transfer learning algorithms.     

民机风洞试验验证技术中的几点新发展

通过总结近年来与国内外风洞试验验证专业领域中的合作经验,提出了几点民机风洞试验验证技术中的新发展。它们有的已经广泛应用于工程实际,有的是在对外合作中刚刚获得的一些新经验,有的则是刚开始摸索并将要在后续的风洞试验验证中继续深入实施的措施等,一并提出,以期为后来者提供参考。     

信号仿真系统离散信号发送功能研究

2011年底中国民航局新发布的CCAR25.1709对于电气线路互联系统（ Electrical Wiring Interconnection Sys-tem,简称EWIS）安全性提出了更完全和结构化的评估要求。分析了原规章条款25.1309对于EWIS安全性评估的不足和对新规章条款25.1709的要求及其理解,并结合具体的民用飞机设计经验,分别从EWIS失效产生的功能性和物理性两方面安全性影响,探讨了EWIS对于25.1709的符合性设计和分析的过程与方法。     

Crashworthiness uncertainty analysis of typical civil aircraft based on Box–Behnken method

The crashworthiness is an important design factor of civil aircraft related with the safety of occupant during impact accident. It is a highly nonlinear transient dynamic problem and may be greatly influenced by the uncertainty factors. Crashworthiness uncertainty analysis is conducted to investigate the effects of initial conditions, structural dimensions and material properties. Simplified finite element model is built based on the geometrical model and basic physics phenomenon. Box–Behnken sampling and response surface methods are adopted to obtain gradient information.Results show that the proposed methods are effective for crashworthiness uncertainty analysis.Yield stress, frame thickness, impact velocity and angle have great influence on the failure behavior,and yield stress and frame thickness dominate the uncertainty of internal energy. Failure strain and tangent modulus have the smallest influence on the initial peak acceleration, and gradients of mean acceleration increase because the appearance of material plastic deformation and element failure.     

民用涡扇发动机多变量增广LQR控制器设计

针对民用涡扇发动机设计多变量控制器,提出将多变量增广LQR控制算法引入到民用涡扇发动机的方法。将发动机控制量作为增广的状态向量引入LQR算法设计,并根据控制系统回路的性能需求,设计期望动态响应曲线;期望动态响应与实际动态响应的差值范数作为优化目标用来调整、确定LQR控制算法的权阵取值;设计的控制器与民用涡扇发动机非线性模型仿真验证。结果表明,多变量增广LQR控制器满足民用涡扇发动机的控制需求。     

民用飞机阵风载荷及减缓技术的研究

由于民用飞机机翼具有大展弦比的特点,因此阵风载荷经常成为民用飞机飞行载荷的严重情况,是各国适航标准重点考察的飞行情况。而且,阵风干扰还会因飞机机体的自身弹性引起结构弹性振动,使飞机结构刚度降低,造成机体疲劳损伤,甚至引起颤振。因此,在民用飞机载荷设计过程中对阵风载荷及其减缓技术进行研究具有非常重要的意义。介绍了民用飞机阵风载荷的原理及相关技术,以及阵风载荷减缓技术中用直接升力控制方法来实现机翼的阵风载荷减缓。     

浅议民机舱内声学波音与空客研究现状

民机噪声对机场环境、客舱舒适性、民机的安全都会产生影响,为此要对其进行研究和控制。针对控制舱内声学环境的目地,简要介绍了欧洲及美国控制民机舱内噪声的研究手段及现状。     

民用飞机后机身结构静力试验方案设计

针对某民用飞机后机身结构特点和受载形式,设计了相应的静力试验方案。该方案合理模拟了后机身结构的支持和边界条件,同时对后机身严重载荷情况进行分析处理,实现了飞行载荷和惯性载荷在后机身结构上的施加,顺利完成了大部段复杂结构的静强度试验。试验结果表明,后机身结构能够承受极限载荷,其刚度和强度满足设计要求。