奖状560飞机“NO TAKEOFF”警告系统排故分析

“NO TAKEOFF”(不起飞)警告属于飞机指示告警系统的重要组成部分,用于提醒机组,飞机当前构型不符合起飞条件,要求机组采取措施及时中断起飞过程,待排除故障、修正构型,以保证飞机适航和飞行安全。本文以奖状560飞机NO TAKEOFF警告系统的工作原理为出发点,阐述其典型故障隔离的分析思路、排故流程,分享故障隔离实际经验,共同提升民航维修安全与效率。

Wing/body kinematics measurement and force and moment analyses of the takeoff flight of fruitflies

In the paper, we present a detailed analysis of the takeoff mechanics of fruitflies which perform voluntary takeoff flights. Wing and body kinematics of the insects during takeoff were measured using Based on the measured data, high-speed video techniques. inertia force acting on the insect was computed and aerodynamic force and moment of the wings were calculated by the method of computational fluid dynamics. Subtracting the aerodynamic force and the weight from the inertia force gave the leg force. The following has been shown. In its voluntary takeoff, a fruitfly jumps during the first wingbeat and becomes airborne at the end of the first wingbeat. When it is in the air, the fly has a relatively large ＂initial＂ pitch-up rotational velocity （more than 5 000~/s） resulting from the jumping, but in about 5 wingbeats, the pitch-up rotation is stopped and the fly goes into a quasi-hovering flight. The fly mainly uses the force of jumping legs to lift itself into the air （the force from the flapping wings during the jumping is only about 5%-10% of the leg force）. The main role played by the flapping wings in the takeoff is to produce a pitch-down moment to nullify the large ＂initial＂ pitch-up rotational velocity （otherwise, the fly would have kept pitching-up and quickly fallen down）.

Effects of Deck Motion and Ship Airwake on Ski-Jump Takeoff Performance of Carrier-Based Aircraft

We first analyzed the force and motion of naval aircraft during launching process.Further,we investigated the ship deck with the form of a ramp and established deck motion model and ship airwake model.Finally,we conducted simulations at medium sea.Results showed that the effects of deck motion on takeoff varied with initial phases,and airwake could help reducing aircraft′s sinkage.We also found that the deck motion played a major role in the effects caused by the interaction of deck motion and ship airwake.

Hover performance estimation and validation of battery powered vertical takeoff and landing aircraft

Battery powered vertical takeoff and landing(VTOL) aircraft attracts more and more interests from public, while limited hover endurance hinders many prospective applications. Based on the weight models of battery, motor and electronic speed controller, the power consumption model of propeller and the constant power discharge model of battery, an efficient method to estimate the hover endurance of battery powered VTOL aircraft was presented. In order to understand the mechanism of performance improvement, the impacts of propulsion system parameters on hover endurance were analyzed by simulations, including the motor power density, the battery capacity, specific energy and Peukert coefficient. Ground experiment platform was established and validation experiments were carried out, the results of which showed a well agreement with the simulations. The estimation method and the analysis results could be used for optimization design and hover performance evaluation of battery powered VTOL aircraft.

Engine-Out Takeoff Path Optimization for Large Civil Aircraft

Maximum regulated takeoff weights and hence payloads of large commercial jets are limited by government regulations which take into account local airport conditions as well as a variety of safety factors. One of the challenging conditions that must be met is linked to a minimum obstacle clearance in the unlikely event of an engine failure on the runway at the worst possible time. This requirement becomes an overriding factor for airports surrounded by challenging terrain, and therefore a well defined takeoff path out of these airports has the potential to transform a financially unsustainable operation into a commercially viable one. The research described in this paper represents an ongoing attempt to resolve this important problem and makes use of recent advances in robot path planning techniques.

Theoretical and Experimental Investigations of Gyroplane Jump Takeoff Dynamics

A nonlinear and time-varying gyroplane jump takeoff dynamics model considering the unsteady ground effect and the rapid blade-pitch increase(RBPI) is developed and validated against the experiment data.The precisions of the proposed model,an experienced Hollmann model and three other simplified models are compared by displaying the height and rpm time histories of those models and the experimental data.The mean square errors(MSE) of the height histories and maximum height errors(MHE) between those models are calculated and given out.The statistics provide a kind of evaluation method of importance of the unsteady ground effect,RBPI,and the induced velocity on jump takeoff performance in vertical phase.The impact of the unsteady ground effect and RBPI on the thrust and induced velocity of the experimental rotor of a small scale platform is analyzed.The study indicates that the proposed model agrees better with the experimental data than other models.It is useful for predicting the gyroplane jump takeoff performance for design.

Mathematical Model for Takeoff Simulation of a Wing in Proximity to the Ground

Aircraft flying close to the ground benefit from enhanced efficiency owing to decreased induced drag and increased lift. In this study, a mathematical model is developed to simulate the takeoff of a wing near the ground using an Iterative Boundary Element Method （IBEM） and the finite difference scheme. Two stand-alone sub-codes and a mother code, which enables communication between the sub-codes, are developed to solve for the self-excitation of the Wing-In-Ground （WIG） effect. The aerodynamic force exerted on the wing is calculated by the first sub-code using the IBEM, and the vertical displacement of the wing is calculated by the second sub-code using the finite difference scheme. The mother code commands the two sub-codes and can solve for the aerodynamics of the wing and operating height within seconds. The developed code system is used to solve for the force, velocity, and displacement of an NACA6409 wing at a 4° Angle of Attack （AoA） which has various numerical and experimental studies in the literature. The effects of thickness and AoA are then investigated and conclusions were drawn with respect to generated results. The proposed model provides a practical method for understanding the flight dynamics and it is specifically beneficial at the pre-design stages of a WIG effect craft.

ANALYSISOFOPERATIONALCAUSESOFAIRPLANETAKEOFFACCIDENTS

The possibility and causes of flight accidents by operational error/deviation in takeoff are analyzed in this paper. The following three stages are each described individually: before liftoff, near liftoff and initial climb. Relations of accident/incident causal factors by operational error with intrinsical flight mechanics are discussed.

Modeling and Verification of Aircraft Takeoff Through Novel Quantum Nets

The formal modeling and verification of aircraft takeoff is a challenge because it is a complex safety-critical operation.The task of aircraft takeoff is distributed amongst various computer-based controllers,however,with the growing malicious threats a secure communication between aircraft and controllers becomes highly important.This research serves as a starting point for integration of BB84 quantum protocol with petri nets for secure modeling and verification of takeoff procedure.The integrated model combines the BB84 quantum cryptographic protocol with powerful verification tool support offered by petri nets.To model certain important properties of BB84,a new variant of petri nets coined as Quantum Nets are proposed by defining their mathematical foundations and overall system dynamics,furthermore,some important system properties are also abstractly defined.The proposed QuantumNets are then applied for modeling of aircraft takeoff process by defining three quantum nets:namely aircraft,runway controller and gate controller.For authentication between quantum nets,the use of external places and transitions is demonstrated to describe the encryptiondecryption process of qubits stream.Finally,the developed takeoff quantum network is verified through simulation offered by colored petri-net(CPN)Tools.Moreover,reachability tree(RT)analysis is also performed to have greater confidence in feasibility and correctness of the proposed aircraft takeoff model through the Quantum Nets.

Streamlining Takeoff and Estimating with BIM:A Case Study of a Construction Cost Estimating Course

Since the construction industry has been adopting Building Information Modeling(BIM)as the standard practice for design,engineering,and fabrication in the recent decade,many Construction Management(CM)programs at U.S.universities have started to introduce BIM for cost estimating in their curriculum.Although considered as the fifth dimension beyond 3D and schedule,BIM for cost estimating in many cases is still used merely as an alternative model-based quantity takeoff method to the traditional plan-based approach.The disconnection between automated quantity takeoff and cost estimating,however,still exists,and the benefits of the BIM process in a project life cycle can not be fully understood by CM students without realizing its impact in the preconstruction phase.To bridge these gaps in a CM curriculum,an Advanced Cost Estimating course for CM programs has been developed that focuses on integrating BIM in both the takeoff and estimating process.The new course streamlines the connection between model-based quantity takeoff and cost estimating with the help of a combination of multiple construction software programs.Through the integration between the software,quantity data from a BIM model can be seamlessly transferred to a construction cost database for bid pricing and reporting.This paper presents the development of the new Advanced Cost Estimating course as a case study,including its objectives,layout,and assessment methods,and provides empirical and valuable insights on how to integrate BIM in a cost estimating course for a CM curriculum.

Optimal Design and Force Control of a Nine-Cable-Driven Parallel Mechanism for Lunar Takeoff Simulation

Traditional simulation methods are unable to meet the requirements of lunar takeo simulations, such as high force output precision, low cost, and repeated use. Considering that cable-driven parallel mechanisms have the advantages of high payload to weight ratio, potentially large workspace, and high-speed motion, these mechanisms have the potential to be used for lunar takeo simulations. Thus, this paper presents a parallel mechanism driven by nine cables. The purpose of this study is to optimize the dimensions of the cable-driven parallel mechanism to meet dynamic workspace requirements under cable tension constraints. The dynamic workspace requirements are derived from the kinematical function requests of the lunar takeo simulation equipment. Experimental design and response surface methods are adopted for building the surrogate mathematical model linking the optimal variables and the optimization indices. A set of dimensional parameters are determined by analyzing the surrogate mathematical model. The volume of the dynamic workspace increased by 46% after optimization. Besides, a force control method is proposed for calculating output vector and sinusoidal forces. A force control loop is introduced into the traditional position control loop to adjust the cable force precisely, while controlling the cable length. The e ectiveness of the proposed control method is verified through experiments. A 5% vector output accuracy and 12 Hz undulation force output can be realized. This paper proposes a cable-driven parallel mechanism which can be used for lunar takeo simulation.

多情景下中型航空公司碳排放预测研究

在国际国内减碳的大背景下,文章选择国内某中型航空公司作为研究对象,首先利用ICAO碳排放计算法,依据航班进程的两个阶段(LTO和CCD阶段),对2015—2019年的碳排放量状况进行计算分析,再通过设置不减碳情景、基础减碳情景、快速减碳情景和理想减碳情景4个民航发展情景,使用基于Python语言的蒙特卡洛模拟方法,以2021年为基准,对该航空公司2022—2035年内的碳排放进行仿真预测。结果表明:由于中型航空公司的发展需求,4种情况下都无法完成碳排放总量达峰,但其每万架次碳排放量明显降低,表明碳减排措施的有效性。最后从国内外理论研究和现实应用的角度出发,为中型航空公司提出了多条低碳发展建议,以助力我国民航业早日实现碳达峰、碳中和的重要目标。

垂直起降系统的互补滑模与情感神经网络控制

针对具有未知扰动的垂直起降机双闭环控制系统,提出一种基于连续径向基情感神经网络的互补积分滑模控制策略。建立了包含未知扰动项的垂直起降机的数学模型,为系统内外环分别设计滑模控制器和互补积分滑模控制器,基于对系统鲁棒性的考量,利用连续径向基情感神经网络逼近系统未知扰动项,给出神经网络权重的自适应律,形成一套新型的复合控制策略,利用Lyapunov方法分析了系统的稳定性。通过对垂直起降机的仿真实验与实物实验进行分析对比,证明了所设计的控制器具有更快的收敛速度、更高的跟踪精度和更佳的鲁棒性。

近距平行跑道机场绕行滑行道使用策略研究

为了给近距平行跑道机场制定和优化航空器场面运行策略提供理论依据,提升跑道运行安全水平和效率、减少机场运行场面冲突、降低安全隐患。分析并建立基于进、离港航班平均地面滑行时间最小为目标的绕滑(end-around taxiway,EAT)运行决策模型,并以某机场两条近距平行跑道绕滑运行为例,采用数值计算和AirTOp运行仿真软件两种方式验证了该模型的可行性。算例结果表明:由该模型确定的绕滑使用策略,可以同时降低机场进、离港航班的延误水平,提高地面滑行效率。通过对该机场航班运行数据的进一步研究发现,起飞跑道交通密度与绕滑使用率之间存在较为明显的正相关关系,进而提出针对该机场在高峰小时运行架次和起降比变化情况下的绕滑运行策略。

基于改进YOLOv8的飞机起降飞行姿态风险检测

飞机在执行飞行任务时,其起飞和降落两个阶段是整个飞行过程中最关键和最具挑战性的时刻之一,其起降飞行姿态的变化程度关系到整个飞机的安全性。为了降低飞机在起降过程的风险性,提出了一种基于改进YOLOv8的飞机起降飞行姿态的风险检测方法。该检测方法综合利用了CBAM注意力机制、GSConv轻量化卷积模块和HIOU准则函数等深度学习和目标检测技术,实现了对飞机机翼、起落架等关键结构部位的准确检测,以便利用识别到的飞行姿态特征参数来对飞机当前的安全状态进行分析和评估。经实验验证表明,该改进方法对于飞机起降阶段中的飞行姿态风险状况能够进行精准识别和检测,具有较高的可靠性。

基于仿生技术的尾座式VTOL无人机起降稳定控制及轨迹优化

尾座式垂直起降(Vertical takeoff/landing,VTOL)无人机(Unmanned aerial vehicle,UAV)稳定性差,与传统起落架的适配性低。针对上述问题,提出了一种采用自由尾翼技术的新型起落架。该起落架采用串联多级结构,在降低机身高度的同时,保证了巡航状态下尾翼力臂的长度,并通过虚拟中心点力分布技术对动态着陆过程进行调控,简化了控制过程,有利于模式转换过程中的无缝轨迹优化。随后基于猫中心点单点数据集,利用神经网络对起落架控制进行训练,有效提高了起落架自适应起落速度和精度。最后,结合无人机不同模式的参数要求,进行多目标优化和相似性转换,有效提高了尾座式垂直起降无人机的着陆适应性和稳定性。

基于多目标规划的机队运力优化配置研究

为提高航空公司的收益,减小其运行成本,以航空公司空中运营成本和地面运营成本最小作为目标函数,以航班连续、飞机飞行时长、航线上旅客需求量、特殊机场条件、飞机最大航程等作为约束条件建立机队运营成本控制模型。通过仿真计算确定机队运力配置方案,并将优化后各运行成本与航空公司原始成本进行对比,结果发现成本大大优化,由此可以验证所提出模型的有效性。

火星表面起飞上升热控技术研究与分析

火星表面起飞上升热控技术是火星取样返回探测的关键技术,涉及探测器在火星表面存储控温、火星表面起飞上升控温及火星在轨飞行控温等,具有温度指标要求高、控温维度大、资源紧张的特点。本文对国内外主要火星车及美国航空航天局(NASA)火星上升器的热控方案进行了调研和总结。分析表明火星表面探测器热控技术根据资源分配情况主要采用2种方式:当热控质量受限不明显时,可采用机械泵驱动流体回路技术配合常规热控措施,对大热耗单机进行热量收集和传输,实现废热的再利用;当热控质量受限严重时,需采用轻量化低功耗的控温措施,可采用复合纳米气凝胶隔热技术配合常规热控措施,高效隔绝火星表面低温对流环境,实现低功耗控温。随后提出了火星表面起飞上升的热控关键技术,主要包括纳米气凝胶隔热技术、火星原位资源隔热技术、机械泵驱动两相流体回路技术、气动热防护技术及热试验模拟技术等,可为后续火星探测提供一定的参考。

涡轴-涡扇变循环发动机方案及性能匹配设计研究

针对旋转机翼式垂直起降高速巡航飞行器,提出了一种新概念结构形式的涡轴-涡扇变循环(TSFVCE)发动机,能够分别在涡轴和涡扇两种模态工作。首先对涡轴-涡扇变循环发动机的结构及工作模式进行了介绍,并建立基于变比热的部件级性能仿真模型;然后通过循环分析,确定发动机第二涵道比为3,Flade外涵风扇压比为1.98,第一涵道比为0.11,完成发动机设计点性能方案设计;最后分析了核心机驱动风扇(CDFS)可调机构对发动机性能影响机理,得出CDFS放气阀对发动机涡扇模态下的推力与涡轴模态下的功率影响较大,对涡扇模态的推力影响最大为61.5%,对涡轴模态的功率影响最大为33.3%,可利用此特性实现发动机在涡扇和涡轴模态下推力和功率输出的匹配。