Hazardous Attitude Factors Influence Risk Perception in General Aviation Pilots

This manuscript presents a research proposal to investigate how hazardous attitudes among general aviation pilots influence pilot performance in aviation accidents. General aviation pilots train to maintain safe flying conditions, but accidents still occur, and human factors figure prominently among the causes of aviation accidents. The levels of hazardous attitudes among pilots may influence the likelihood of engaging in risky flight behaviors that can lead to accidents. This quantitative study aims to determine whether dangerous attitudes impact risk perception in general aviation pilots. The study will focus on two specific hazardous attitudes, “Anti-Authority” and Macho” behaviors. Among the hazardous attitudes identified by the Federal Aviation Administration (FAA), the two attitudes often stand out in accident investigations and pilot narratives. While all hazardous attitudes have inherent dangers, these two attitudes tend to be more frequently cited in accident reports and investigations. Despite rigorous training in safe flying conditions, general aviation accidents still transpire due to human factors. This research hypothesizes that the five attitudes from the hazardous attitude model, particularly Anti-Authority and Macho, significantly shape pilots’ risk perception. The insights from this study would benefit stakeholders, like the Aircraft Owners and Pilots Association (AOPA), Air Safety Institute, and aviation training programs, in creating training modules tailored to reduce such attitudes.

A Study on the Reform of China’s General Aviation

With the rapid development of China’s general aviation in recent years, the demand for general aviation aircraft is increasing, therefore, the standard for the security management of general aviation, technical standards and market access for general aviation companies, and flight crew is much higher than that of before. However, the current law and regulations of general aviation are based on the standard of public transport, taking the fact into account that the general aviation and public transport aviation are very different;the Chinese government has proposed a reform of general aviation management principles, contents and objectives, and aims to formulate legal system of general aviation by 2020.

The Influence of Demoiselle Aircraft on Light and General Aviation Design

In 1907, aviation pioneer Santos-Dumont had the idea of building a very light airplane. He designed and built the SD 19, the Demoiselle, an aircraft with a 6 meter wing span and a 24 HP engine of his own design. The Demoiselle was very successful in flying and, became very popular and its development continued as SD20, SD21 and SD22 （his last airplane）. The influence of the Demoiselle on design principles of light aircraft and general aviation were studied in this work, using statistical entropy, The designs number 20 and 22 may be considered dominant and influenced the design principles of light aircraft and general aviation.

水平内螺纹管中超临界RP-3航空煤油换热数值研究

针对航空换热器的应用,对水平内螺纹管中RP-3航空煤油的超临界换热进行了数值研究,着重考察煤油压力和螺纹升角对换热的影响。基于管截面温度、密度、局部质量流速、流线分布状况,揭示周向非均匀传热恶化的机理。通过类气膜温度梯度和旋流动能的演变以定量表征类气膜程度和旋流强度。提出了适用于周向四个位置努塞尔数预测的换热关联式。结果表明:流动性差的类气膜在冷流体和热壁面之间形成阻隔,导致传热恶化问题。浮升力作用致使流场和温度场出现畸变,类气膜厚度周向不均,产生局部超厚类气膜,对应的传热恶化加剧。厚类气膜区和二次流涡在浮升力和螺纹旋流耦合机制下沿流动方向不断逆时针改变位置。提高煤油压力有利于削弱和延后类气膜效应,且使旋流强度下降。随着螺纹升角增大,类气膜效应略有削弱和后延,旋流强度显著提高。换热关联式预测偏差普遍位于±10%的误差范围。

液环式航空燃油离心泵自吸性能

基于Mixture模型对液环式航空燃油泵进行自吸阶段的非稳态数值计算,研究自吸过程中燃油泵内气液两相分布的变化过程,对不同时刻下燃油泵内部含气率、气液两相分布、压力及速度流线、熵产率和湍动能变化规律进行分析.结果表明:燃油泵的吸气和排气主要集中在自吸过程的前期和中期;随着自吸时间的增加,各监测面的含气率逐渐降低,当自吸时间为3.00 s时,蜗壳出口含气率接近于0,自吸过程结束;泵内压力随相对距离的增加而增大,泵内同一相对距离平面压力随自吸时间的增加而增大;在气液混合时,高速区域主要集中在叶轮中间流道和蜗壳壁面处,低速区域则集中分布在隔舌附近和导叶出口;随着自吸过程的进行,泵内湍动能和熵产率也随之增大,泵内能量损失增大,主要集中在叶轮叶片、导叶叶片和蜗壳出口处.

关于氢能航空动力发展的认识与思考

近年来,在全球碳减排目标的驱动下,各国对发展氢能航空的热情空前高涨,在氢能飞机和氢能动力领域加速布局研究计划。通过研究国内外氢能飞机及动力发展历程和研究进展,发现人类对氢的认知始于其燃烧特性,认为氢能航空发展兴于“双碳”目标,指出燃氢涡轮发动机是航空业实现减碳目标的关键,分析了燃氢涡轮发动机和氢燃料飞机的性能优势,研判出氢能航空及动力发展难在全产业链重构和全链条颠覆创新,提出了创新氢能航空发展机制、加快发展燃氢涡轮发动机、健全氢能航空产业链条、实现全链条颠覆性创新和加强氢能航空基础建设等五方面的发展措施建议。

高空机载灭火剂流动输运数值仿真

为探究高空环境对飞机货舱灭火系统内灭火剂流动输运动态的影响,采用Fluent软件对一小型“哈龙”1301机载灭火系统装置管网中灭火剂的流动输运进行数值建模与仿真模拟,计算得到10000 m及13000 m高空下“哈龙”1301灭火剂在管网内的输运和释放动态,并与海平面高度下灭火剂输运释放过程中压力、相体积分数及相变传质速率三个特征变量进行对比分析。结果表明,高空环境下灭火剂的输运释放遵循“三阶段”,但高海拔环境不利于灭火剂的流动输运。该研究结果可为优化机载灭火系统在高空环境下的流动输运能力提供理论依据。

ADS-B Anomaly Data Detection Model Based on Deep Learning and Difference of Gaussian Approach

Due to the influence of terrain structure,meteorological conditions and various factors,there are anomalous data in automatic dependent surveillance-broadcast(ADS-B)message.The ADS-B equipment can be used for positioning of general aviation aircraft.Aim to acquire the accurate position information of aircraft and detect anomaly data,the ADS-B anomaly data detection model based on deep learning and difference of Gaussian(DoG)approach is proposed.First,according to the characteristic of ADS-B data,the ADS-B position data are transformed into the coordinate system.And the origin of the coordinate system is set up as the take-off point.Then,based on the kinematic principle,the ADS-B anomaly data can be removed.Moreover,the details of the ADS-B position data can be got by the DoG approach.Finally,the long short-term memory(LSTM)neural network is used to optimize the recurrent neural network(RNN)with severe gradient reduction for processing ADS-B data.The position data of ADS-B are reconstructed by the sequence to sequence(seq2seq)model which is composed of LSTM neural network,and the reconstruction error is used to detect the anomalous data.Based on the real flight data of general aviation aircraft,the simulation results show that the anomaly data can be detected effectively by the proposed method of reconstructing ADS-B data with the seq2seq model,and its running time is reduced.Compared with the RNN,the accuracy of anomaly detection is increased by 2.7%.The performance of the proposed model is better than that of the traditional anomaly detection models.

Does the Sleep-Related Neurons Modulate the Sensation of Pain under the Use of GA?

General anesthetics (GA) has been discovered for centuries and was often used in surgeries. However, many patients are dying from the usage of GA for different reasons. Although scientists are working on to solve the problems, the mechanism of GA is still a mystery. Recently, scientists from Duke University found neurons that are active during sleep can be activated in anesthesia. These neurons are called Anesthetic Activated Neurons (AANs). This is a massive step for us to break the mystery. In this paper, we designed an experiment that aims to reveal one mechanism of GA: the relationship between sleep-related neurons and sensation of pain under the use of GA. The designed experiment involves several control groups that consist of mice with different treatments on their genes and different GA.

某型涡喷发动机排气排出物测量研究

为考核以RP-3航空煤油为燃料的某涡喷发动机的污染物排放特性,按照ICAO、HB 6116和HB 6117的相关标准要求设计搭建一套排气排出物测量及分析系统,在某型涡喷发动机地面试车台上开展排气排出物测量试验。研究发现随着发动机状态的增加,CO的排放量显著降低;HC的排放量接近于0;CO_(2)和NO_(x)的排放量逐渐提高,同时冒烟数也随着发动机的状态增加而逐渐增大。经过理论分析,该研究的试验结果与经典燃烧学中的相关结论一致,验证了所设计的测量系统和实验的可靠性,可为后续军用和民用发动机排气排出物测量试验提供参考。

Development cost prediction of general aviation aircraft using combined estimation technique

Obtaining accurate development cost estimation results of general aviation aircraft is crucial for companies to adopt the best strategy in the development process.To address this problem,this paper proposes a combination of three commonly used single prediction methods.The optimal weight values of the three single prediction methods are determined by utilizing the shortest ideal point method.Ten cost datasets collected from literature are utilized for fitting and testing the combined prediction method,and the weight coefficients of the three individual prediction methods are calculated as 0.6859,0.0035 and 0.3106,respectively.The results of this study indicate that the developed method has better fitting and estimation accuracy than that of the three individual methods,with average fitting and predicting error values of 2.60%and 6.43%,respectively.Additionally,the cost data of military and civil aircraft development from literature are collected for verification.The results further confirm that the proposed method is not only superior to the single prediction methods in terms of high precision but has wider applications.More importantly,this research can provide important reference for general aviation aircraft companies in term of product cost planning and corporate sales strategies.

Development cost prediction of general aviation aircraft projects with parametric modeling

The study of the development cost of general aviation aircraft is limited by small samples with many cost-driven factors. This paper investigates a parametric modeling method for prediction of the development cost of general aviation aircraft. The proposed technique depends on some principal components, acquired by utilizing P value analysis and gray correlation analysis. According to these principal components, the corresponding linear regression and BP neural network models are established respectively. The feasibility and accuracy of the P value analysis are verified by comparing results of model fitting and prediction. A sensitivity analysis related to model precision and suitability is discussed in detail. Results obtained in this study show that the proposed method not only has a certain degree of versatility, but also provides a preliminary prediction of the development cost of general aviation aircraft.

低水油比航空煤油RP-3水蒸气重整制氢实验研究

本文以碳氢燃料航空煤油高效制氢为目的,进行了微通道常压重整实验,研究了反应温度和水油比等反应条件对RP-3蒸汽重整的影响,重点考察了产气率、气体产物分布等特征。实验结果表明,反应温度和水油比的增加均提高了重整反应的产气率,有利于H_(2)选择性的增加。随着反应进行,碳氢产物的选择性降低,其中烯烃成为主要碳氢产物,更高的水油比具有更低的烯烷比。含水量的提高增加了H_(2)收率,800℃时水油比3相较于1和2分别增大了152.3%和134.6%;同时降低了反应产生的积炭,较好的抑制高温结焦行为。在反应温度800℃、水油比为3:1时H_(2)选择性最高达到了57.83%,并达到了34.7%的氢气收率,在该重整条件下制氢效果最佳。

Aerodynamic/mechanism optimization of a variable camber Fowler flap for general aviation aircraft

A conventional Fowler flap is designed to improve the take-off and landing performances of an aircraft. Because the flight states of general aviation aircraft vary significantly. A Fowler flap with a double-sliding track has been designed, which is ca- pable of changing airfoil camber while cruising and climbing as well as meeting low-speed performance requirements. The aerodynamic characteristics of the variable camber Fowler flap were studied by computational simulation, and cambering was found to be beneficial for improving the lift-to-drag ratio when the lift coefficient was larger than the critical value, below which decambering was more effective; this critical value differed somewhat under different conditions. Taking the mecha- nism into account, the take-off and landing configurations were optimized on the basis of the GA （W）-1 airfoil with a 30% chord Fowler flap. Compared with reference configuration, the maximum lift coefficient of optimized take-off configuration was increased by 6.6% as well as the stalling angle and the lift-to-drag ratio were increased by 1.3° and 7.58%, respectively. Moreover, the maximum lift coefficient of the optimized landing configuration was increased by 6.3%, and the stalling angle was increased by 1.1°; however, the nose-down pitching moment of both configurations increased. Similar results were at- rained on a general aviation aircraft wing/body combination nism was established in a computer-aided design system, achieved by the double-sliding track. A 3D model of the variable-camber Fowler flap driving mecha- and the results showed that all design configurations could be

A Meta-Learning Approach for Aircraft Trajectory Prediction

The aviation industry has seen significant advancements in safety procedures over the past few decades, resulting in a steady decline in aviation deaths worldwide. However, the safety standards in General Aviation (GA) are still lower compared to those in commercial aviation. With the anticipated growth in air travel, there is an imminent need to improve operational safety in GA. One way to improve aircraft and operational safety is through trajectory prediction. Trajectory prediction plays a key role in optimizing air traffic control and improving overall flight safety. This paper proposes a meta-learning approach to predict short- to mid-term trajectories of aircraft using historical real flight data collected from multiple GA aircraft. The proposed solution brings together multiple models to improve prediction accuracy. In this paper, we are combining two models, Random Forest Regression (RFR) and Long Short-term Memory (LSTM), using k-Nearest Neighbors (k-NN), to output the final prediction based on the combined output of the individual models. This approach gives our model an edge over single-model predictions. We present the results of our meta-learner and evaluate its performance against individual models using the Mean Absolute Error (MAE), Absolute Altitude Error (AAE), and Root Mean Squared Error (RMSE) evaluation metrics. The proposed methodology for aircraft trajectory forecasting is discussed in detail, accompanied by a literature review and an overview of the data preprocessing techniques used. The results demonstrate that the proposed meta-learner outperforms individual models in terms of accuracy, providing a more robust and proactive approach to improve operational safety in GA.

微型燃气轮机技术

高效微型燃气轮机发电机组可用于航空、航天等领域 ,还可用于分布式发电、军用车辆辅助动力装置、车用混合动力装置等 ,因此研究这种动力装置有很重要的实用意义。首先介绍了微型燃气轮机的发展过程 ,简要说明了过去 40年内微型燃气轮机在结构上发生的变化。随后给出了组成微型燃气轮机的关键部件在设计过程中应注意的一些问题。最后回顾了国内一些研究单位在这一领域所进行的研究工作 ,并指出了今后的努力方向和工作重点。

高温作用下酯类航空润滑基础油的组分分析

用己二酸二异辛酯(DIOA)油样模拟酯类航空润滑基础油在高温下进行氧化裂解反应,考察了油样的酸值变化,并采用GC-MS联用技术检测了DIOA的结构组成随工作温度的变化情况。实验结果表明,当工作温度为100℃时,DIOA油样中已有小分子的单酯和双酯产生,随工作温度的升高,酯含量不断增加;当工作温度为170℃时,油样中有小分子的酮、酸等化合物生成,油样呈淡黄色;当工作温度为300℃时,油样中酮和酸的相对含量分别为0.605%和0.020%,酸值(每g油样消耗KOH的质量)高达12.597 mg/g,油样呈深黄色,且出现胶质状沉淀。该方法可用于分析酯类航空润滑基础油的热氧化安定性和主滑油性能变化,以确定合理的换油周期。

基于LS-SVM的航空发动机气路参数趋势在线预测

将最小二乘向量机(LS-SVM)应用于航空发动机气路参数趋势在线预测。首先,分析了PATS系统所接收的空地数据链(ACARS)报文的特点,构建用于实时存储和解析的发动机报文并行处理系统,获取在线模型的训练样本;其次,针对实时样本,利用最终误差预报准则(FPE)确定嵌入维数,采用直接搜索法优化LS-SVM建模参数,建立了基于LS-SVM的气路参数预测模型。与航路飞机建立ACARS链接,获取发动机实时气路数据,预测气路参数变化趋势。与已有神经网络预测模型相比,具有更高的一步预测和多步预测精度。该方法解决了发动机预诊断中的数据趋势预测问题。

毛细管气相色谱切割反吹技术归一化法定量分析航空煤油中的芳烃

用气相毛细管色谱切割反吹技术 ,和在FFAP毛细管预柱上芳烃比高它 3个碳数的烷烃之后出峰的特点 ,通过阀切换把芳烃反吹入非极性OV 1分析柱中 ,按照沸点进行分离。从预柱上先流出的组分和从分析柱上后流出的组分先后通过微型三通进入同一个FID检测器 ,因此可用校正响应因子归一化法进行定量分析。从预柱出口到检测器之间的阻尼柱阻力 6倍于分析柱阻力 ,反吹后因载气流速提高 5 .4倍而有效地压缩了谱带 ,提高芳烃等目标组分的检出灵敏度 2倍。通过切割反吹操作能很好地完成航空煤油中从苯到C11芳烃的检测 ,阀切换的可允许时间窗口达± 18s,且分析结果的重现性误差RSD≤ 4 .0 %。

航空润滑油热氧化衰变的高压差示扫描量热法分析

模拟实际使用条件 ,对ВНИИНП_50_1_4Φ航空润滑油进行热氧化试验 ,应用高压差示扫描量热法(PDSC)和气相色谱仪 (GC)评价抗氧剂N_苯基_α萘胺(NPAN)的热氧化衰变程度 ;结果发现在50_1_4Φ润滑油热氧化衰变过程中 ,抗氧剂NPAN质量分数 (w)的对数值与PDSC在一定条件下测得的氧化诱导期tOIT 具有良好的线性相关性 ,表明PDSC是研究润滑油热氧化衰变程度的理想手段。