Space range estimate for battery-powered vertical take-off and landing aircraft

A novel method for estimating the space range of battery-powered vertical take-off and landing(VTOL) aircraft is presented. The method is based on flight parameter optimization and numerical iteration. Subsystem models including required thrust, required power and battery discharge models are presented. The problem to be optimized is formulated, and then case study simulation is conducted using the established method for quantitative analysis. Simulation results show that the space range of battery-powered VTOL aircraft in a vertical plane is an oblate curve, which appears horizontally long but vertically short, and the peak point is not located on the vertical climb path. The method and results are confirmed by parameter analysis and validations.

Problems and Barriers Impeding the Implementation of MagLev Assisted Aircraft Take-Off and Landing Concept

Nowadays, the success of the new technology development and deployment process depends not only on technical, technological solutions, but also on solving the non-technological problems and crossing the societal and psychological barriers. A large international European projects, GABRIEL1 had developed a maglev assisted aircraft take-off and landing, that was applied to conceptual design of aircraft and required on-board and ground systems, had analysed all impacts (effects of concept deployment on effectiveness, safety, security, noise, emissions) and had demonstrated the safe applicability by concept validation. The applied methodology, used methods and the results of the Gabriel projects had been described and discussed by 55 project deliverables. This paper has a special goal: investigating the problems and barriers of possible implementing of the radically new technology, aircraft MagLev assisted take-off and landing. The study was started by identification and classification of the problems and barriers. After it, the problems were systematically analysed by use of special methodology containing the understanding (description) of the problems, investigation of the possible solutions and discussing their applicability (mainly by use of the Gabriel project results). The paper has three major sections: 1) description of the Gabriel concept and project results, 2) introducing some related thoughts on general aspects of new technology developments, and 3) discussion on the problems and their solutions. The major classes of the problems are the 1) technical, technological problems as developing a radically new solution, landing the undercarriage-less aircraft on the magnetic tracks, 2) stakeholders’ problems as decision makers kicking against supporting the developments of so radically new technologies and 3) society barriers like society worrying on and fear of future passengers on flying by aircraft have not conventional undercarriage systems. The paper will show that these problems have safe and cost-effective solutions.

The Influence of Climate Change and Variability on Aircraft Take-off and Landing Performance;a Case Study of the Abeid Amani Karume International Airport-Zanzibar

Climate change (CC) and variability have been world widely reported to pose number of risks in aviation industry including accidents, astray, and other operational difficulties. The impact of weather on landing and take-off performances has been several times experienced at Abeid Amani Karume International Airport (AAKIA);however, the influence of climate change and variability to the aircraft performance needs to be assessed. Thus, this study investigated the influence of climate change and variability on aircrafts take-off and landing performances. Specifically, the study investigated;i) the influence of climate change on Take-off Distance Required (TODR) and Maximum Take-off Mass (MTOM) for different types of aircraft;ii) the influence of climate variability to the aircraft landing performance on light, medium and heavy aircraft and lastly, iii) the study investigated the seasonal and annual variability on aircraft landing performance due to climate variability. The datasets used in this study include the eight years (2014-2021), aircraft operational records (diversion and missed approach events) and Aviation Routine Weather Reports (METAR) records which were utilized as the indicators for landing performance, the long-term (1990-2020) annual maximum temperatures (Tmax) which was used to determine the TODR and MTOM. Statistical tools including mean, percentage changes, correlations, regression, and the chi-square test were used for analysis and hypotheses testing. The results revealed that light and medium aircraft categories were significantly most affected on diversion events as compared to the heavy categories;however, for the missed approach events the impact was vice versa. Moreover, the seasonal and annual variability on diversion and missed approach events were significantly different (at p ≤ 0.001). As for the take-off performance, results show that the TODR and MTOM were significantly increasing and decreasing (at p ≤ 0.001), based on increasing air temperatures. Therefore, the study concludes that the changing climate has significantly affected aircraft by increasing the TODR and decreasing the MTOM, while the climate variability has significantly affected landing performance by influencing the diversion and missed approach events. Thus, the study recommends (i) further research works including the feasibility study on runway extension for the safety of future aircraft operations at the AAKIA and (ii) proper maintenance and improvement of the Instrumental Landing Systems (ILS) as an adaptation measures to the landing aircraft during bad weather events.

Development of Novel Water-extraction System with Thermoelectric Module Using Solar and Wind Power in Arid Land

This study aimed to develop a water-extraction system which could produce the fresh water from the air in arid regions and which used renewable energies as the electric power source. In this paper, the experiments for water extraction from the air were carried out by using the novel multi-stage water-extraction device with Peltier deices for two cases of temperature and related humidity of the air. One was the case where the temperature and the related humidity of the air were constant, and the other was the case where they were simulated the variation of the temperature and related humidity of the air in a day of summer and spring in Loess Plateau, China. The effects of the temperature and related humidity of the atmospheric air and supply the electric power to Peltier devices on performance of water production of the device were investigated and reported.

大型客机机体噪声机理及控制技术

气动噪声问题不仅是大型客机适航取证的关键技术难题,更是关系到乘客舒适度的重要技术指标。增升装置噪声和起落架噪声是大型客机机体噪声的主要来源。本文针对我国大型客机研制中增升装置噪声和起落架噪声的产生机理及控制关键科学问题,开展噪声源、远场声辐射精细化数值模拟。针对噪声产生机理,发展了近壁面边界涡量流、拟涡能流等涡动力学过程与涡声理论相结合的噪声源分析方法;针对机体噪声控制难题,提出了缝翼凹腔小尺度波纹噪声控制方法和起落架支杆大尺度波纹噪声控制方法。数值模拟结果表明:缝翼凹腔是增升装置的重要噪声源之一;中低频噪声和纯音峰值主要来自缝翼凹腔和主翼前缘,后缘襟翼对噪声的贡献相对较小;起落架尾迹区域和轮胎空腔区域存在大量、复杂的大尺度湍流涡结构,是起落架的主要噪声源,起落架各部件噪声特性基本呈现宽频特性,支柱部件辐射噪声最大,轮胎次之,中间的连轴部件和扭杆部件辐射噪声相对较小;缝翼凹腔波纹噪声控制方法兼具减阻和降噪功效;起落架大尺度波纹噪声控制方法能有效降低远场辐射噪声。本文研究内容可为增升装置气动与噪声一体化设计、起落架降噪设计等提供技术支撑。

A multi-strategy pigeon-inspired optimization approach to active disturbance rejection control parameters tuning for vertical take-off and landing fixed-wing UAV

In this paper.Active Disturbance Rejection Control(ADRC)is utilized in the pitch control of a vertical take-off and landing fixed-wing Unmanned Aerial Vehicle(UAV)to address the problem of height fluctuation during the transition from hover to level flight.Considering the difficulty of parameter tuning of ADRC as well as the requirement of accuracy and rapidity of the controller,a Multi-Strategy Pigeon-Inspired Optimization(MSPIO)algorithm is employed.Particle Swarm Optimization(PSO),Genetic Algorithm(GA),the basic Pigeon-Inspired Optimization(PIO),and an improved PIO algorithm CMPIO are compared.In addition,the optimized ADRC control system is compared with the pure Proportional-Integral-Derivative(PID)control system and the non-optimized ADRC control system.The effectiveness of the designed control strategy for forward transition is verified and the faster convergence speed and better exploitation ability of the proposed MSPIO algorithm are confirmed by simulation results.

一种新型多旋翼无人机着舰装置及安全边界评估方法

[目的]为解决旋翼无人机在海上无人平台应用时的自主安全着舰问题,开展旋翼无人机着舰装置及其安全评估方法研究。[方法]以多旋翼无人机为对象,基于“鱼叉–格栅”式助降装置原理,设计一种新型的“V形足–网”式着舰装置。建立无人机和甲板的多刚体动力学模型,通过ADAMS在不同横摇幅值和周期条件下开展着舰过程仿真,得到无人机着舰的姿态变化过程、着舰临界周期和稳定时间。[结果]仿真结果显示,相比普通着舰装置,“V形足–网”装置具备更高的对接冗余度,可适应更小的横摇周期和更大的横摇幅值,并可更快达到姿态稳定。[结论]研究表明,所设计的装置相比普通装置安全性更优异,通过仿真得到的装置安全边界,可为无人机着舰控制提供参考依据,进而提高无人机在海上平台的自主着舰可靠性。

Development of a Bird-like Flapping-wing Aerial Vehicle with Autonomous Take-off and Landing Capabilities

The lack of autonomous take-off and landing capabilities of bird-like flapping-wing aerial vehicles(BFAVs)seriously restricts their further development and application.Thus,combined with the current research results on the autonomous take-off and landing technology of unmanned aerial vehicles,four types of technologies are studied,including jumping take-off and landing technology,taxiing take-off and landing technology,gliding take-off and landing technology,and vertical take-off and landing(VTOL)technology.Based on the analytic hierarchy process(AHP)-comprehensive evaluation method,a fuzzy comprehensive evaluation model for the autonomous take-off and landing scheme of a BFAV is established,and four schemes are evaluated concretely.The results show that under the existing technical conditions,the hybrid layout VTOL scheme is the best.Furthermore,the detailed design and development of the prototype of a BFAV with a four-rotor hybrid layout are carried out,and the vehicle performance is tested.The results prove that through the four-rotor hybrid layout design,the BFAV has good autonomous take-off and landing abilities.The power consumption analysis shows that for a fixed-point reconnaissance mission,when the mission radius is less than 3.38 km,the VTOL type exhibits longer mission duration than the hand-launched type.

Prognostics for Lithium-ion batteries for electric Vertical Take-off andLanding aircraft using data-driven machine learning

The health management of batteries is a key enabler for the adoption of Electric Vertical Take-off and Landingvehicles (eVTOLs). Currently, few studies consider the health management of eVTOL batteries. One distinctcharacteristic of batteries for eVTOLs is that the discharge rates are significantly larger during take-off andlanding, compared with the battery discharge rates needed for automotives. Such discharge protocols areexpected to impact the long-run health of batteries. This paper proposes a data-driven machine learningframework to estimate the state-of-health and remaining-useful-lifetime of eVTOL batteries under varying flightconditions and taking into account the entire flight profile of the eVTOLs. Three main features are consideredfor the assessment of the health of the batteries: charge, discharge and temperature. The importance of thesefeatures is also quantified. Considering battery charging before flight, a selection of missions for state-ofhealth and remaining-useful-lifetime prediction is performed. The results show that indeed, discharge-relatedfeatures have the highest importance when predicting battery state-of-health and remaining-useful-lifetime.Using several machine learning algorithms, it is shown that the battery state-of-health and remaining-useful-lifeare well estimated using Random Forest regression and Extreme Gradient Boosting, respectively.

火箭爆破器爆炸带落点位置受风影响动力学仿真研究

针对火箭爆破器作战运用过程爆炸带受风影响偏移问题,建立受风影响动力学模型和不同环境风发射角修正模型,分析研究风速、风向与火箭爆破器发射角之间的影响关系,并结合相关数据对模型进行仿真验证。该模型可为实战条件下,合理运用火箭爆破器、提升作战运用效能提供支持。

舰载直升机电驱动助降装置及其关键特性分析

针对现役综合系留和转运系统(Aircraft Ship Integrated Secure and Traverse,ASIST)存在的捕获冲击力大、转运时系统能耗高的问题,设计舰载直升机电驱动助降装置。通过分析助降装置的工况得出助降装置在执行捕获与转运任务时的性能要求,据此给出电驱动助降装置传动系统的设计方案。基于功率键合图理论建立传动系统的动力学模型,并与液压驱动助降装置进行对比仿真实验。仿真结果表明:电驱动助降装置的捕获速度降低约92%,捕获时最大冲击力降低约94%,能够在21 kN的外负载作用下执行直升机转运任务,在执行转运任务时能耗降低约29%,该成果对于拓宽ASIST的使用范围、降低系统能耗具有重要意义;所引入的兼顾系统动态特性与能耗特性的建模方法,为其余复杂机械系统的动力学建模提供了参考。

水下电子装备陆上试验装置及方法研究

为了保障开展水下电子装备陆上试验时能有效地模拟产品在水下的散热场景,提出了一种喷淋装置,其能够模拟水下环境,解决现有技术存在的陆上试验散热效率低、能耗高、散热水温不可控、不能持续散热、散热影响环境温度稳定、散热用水不能回收、溢出损坏其他试验设备和振动应力不能同步施加等缺点,有利于提高水下电子设备测试数据的准确性,更好地反映水下电子设备的性能。

New stabilization design for planar vertical take-off and landing aircrafts

This paper presents a new stabilizing control law for a planar vertical take-off and landing aircraft.The model is first transformed into an equivalent form,and then a control law consisting of a linear term and a saturated term is given for a related subsystem,with the saturation levels being assigned as large as possible.Compared to the existing saturation scheme in which all states are restricted by saturations,the design brings about a relatively fast convergence.The effectiveness and advantage of the design are validated by numerical simulations.

发射装置减振参数优化设计

为提升发射装置着陆的抗冲击性,本研究建立动力学模型,利用有限元仿真相同冲击荷载的弹体动态响应,以验算动力学模型的准确性。并采用粒子群优化算法对发射装置的减振系统进行参数优化,选取结构刚度与阻尼作为优化变量,以最小化弹体的动态响应峰值为目标。优化结果表明,适当调整刚度与阻尼能显著减少冲击过载和振动幅度,有效优化弹体在冲击荷载作用下的动态响应。这一研究可为发射装置的设计及其减振系统的优化提供科学依据和方向。

旱地自动移栽技术发展现状及分析

效率低下、经济效益不明显致使半自动移栽机在国内推广受阻,因此当前越来越多学者开始研究自动移栽技术。欧美、日本等国家自动移栽技术发展成熟,而国内大多处于研究阶段。自动移栽机主要工作部件有取苗部件、给苗部件和栽植部件。取苗部件可分为排式取苗和单株取苗,排式取苗又可分为顶出式取苗和拔出式取苗;给苗部件有纯机械驱动和电气联合驱动两种结构;而栽植部件结构形式与半自动移栽机相同。为此,对这3种部件分别进行阐述,介绍了不同结构的工作原理和优缺点,并对今后国内自动移栽机的研究方向提出了建议。

释水条件下地面沉降的滞后效应试验研究

过度抽取地下水造成的地面沉降正逐渐成为一种严重的地质灾害。在现有成果的基础上,设计、研制地面沉降室内试验装置,并改进试样的饱和方法。使用该装置模拟释水引起的地面沉降,从地面沉降对水位变化的响应和地面沉降过程中的孔隙水压力变化两方面研究地面沉降的滞后性。分析结果得出:(1)承压含水砂层和黏土层的变形均表现出滞后现象;(2)相同试验条件下,黏土层变形的滞后时间随着土层厚度的增大而增加。地面沉降试验完成后,分别从黏土层的底部和顶部取出试样进行室内常规压缩固结试验,试验结果表明:抽水引起的地面沉降在垂直层面方向上是不均匀的,距离抽水含水层越近的部分其压缩程度越大。

油麦兼用型气送式集排器匀种涡轮设计与试验

针对油麦兼用型气送式免耕播种机宽幅播种时各行排量一致性受地表坡度变化影响的问题,设计了一种利用输送气流驱动转动、安装于分配装置的匀种涡轮,分析了匀种涡轮进口工作角和出口工作角对输送气流速度的影响,确定了影响3种匀种涡轮工作特性的关键参数。应用CFD仿真中的6自由度动网格模型及台架试验,对比分析3种匀种涡轮对输送气流分布及匀种涡轮转速的影响,结果表明:进口工作角和出口工作角均为锐角的匀种涡轮可提高种子的输送及搅拌性能。选择叶片数量为4、6、8、10的匀种涡轮进行了分配装置内流场分布仿真试验,结果表明,增加匀种涡轮叶片数量可提高匀种涡轮出口处输送气流分布的稳定及均匀性。利用智能种植机械测试平台模拟田间作业不同地表坡度时,安装不同数量叶片的匀种涡轮对各行排量一致性的影响,结果表明:转速为20~50 r/min,沿播种机作业方向的前后与侧向单向组合摆动、前后与侧向往复组合摆动角相对平整地表在-5°~5°变化,叶片数量为8时,油菜及小麦各行排量一致性变异系数最小,分别为4.99%~5.82%和3.85%~4.92%;前后与侧向单向组合摆动角绝对值为5°时,叶片数量为8的匀种涡轮比无匀种涡轮排种油菜和小麦时各行排量一致性变异系数分别降低7.53、11.98个百分点,满足地表坡度变化时油菜及小麦的排种要求。

地表坡度对油菜宽幅精量免耕播种机排种性能的影响

针对油菜种植区域作业方向的地表坡度变化影响气送式油菜宽幅精量免耕播种机排种性能的问题,该研究以播种机及气送式集排器为研究对象,构建了不同地表坡度下种子与外切圆弧型孔、种子-气流与集中分配器间的力学模型,建立了气送式集排器供种速率和排种速率的随机过程模型,应用EDEM仿真开展了作业方向的地表坡度、供种装置转速对供种装置供种速率影响的双因素试验,建立了地表坡度、供种装置转速对供种速率影响的数学模型;利用DEM-CFD耦合仿真分析了地表坡度对集中分配器排种性能的影响规律。仿真试验结果表明:以平整地表为基准,供种速率随地表坡度在-5°~5°内先增大而后逐渐减小;地表坡度绝对值为3°~5°时,供种速率的变化量达到50%;各行排种粒数一致性变异系数随地表坡度的增加而增大,变化区间为4.95%~14.91%。利用智能种植机械测试平台模拟播种机田间作业时不同地表坡度下的作业效果,结果表明,随着作业方向的地表坡度、前后往复摆动角度、前或后单向摆动角度的增大,各行排种量一致性变异系数均逐渐增大;仿真模型计算的各地表坡度下的供种速率与台架试验的平均误差为4.28%。根据试验结果建立播种机沿作业方向前后往复摆动的供种速率与地表坡度和供种装置转速、沿作业方向前或后单向摆动的供种速率与地表坡度和供种装置转速的数学模型,确定了不同地表坡度下,排种量与作业方向地表坡度和供种装置转速的匹配关系,以实现有坡度地表的排种量与平整地表的排种量趋同,为满足不同地表坡度下的播种作业提供参考。

相阵列技术在民机机体气动噪声研究中的应用

麦克风相阵列测量技术是进行民机机体气动噪声研究的主要手段。针对民机机体气动噪声,开展了闭口风洞麦克风相阵列测量技术研究。提出了一种适用于闭口风洞气动噪声测量的阵列优化设计方法,分别设计了适用于民机增升装置、起落架气动噪声测量的阵列。将麦克风相阵列技术应用于某飞机增升装置缩比模型、起落架缩比模型气动噪声闭口风洞试验。研究结果显示:利用侧壁阵列清晰地识别出了增升装置主要气动噪声源,并显示出降噪措施的降噪效果;利用组合阵列,实现了较宽频率范围内起落架气动噪声源探测,识别出了起落架主要气动噪声源。

全向式气囊着陆装置缓冲过程的仿真研究

为了探索火星着陆器缓冲着陆技术,以"火星探路者"登陆系统的全向式气囊缓冲装置为对象,采用大型有限元仿真分析技术,实现气囊结构和着陆过程的数学和力学建模,获得全向式缓冲气囊着陆的动态过程仿真;同时得到重要结构部位的过载、重点部位的位移和速度、气囊内部的压力和温度以及气囊结构的动态应力分布等重要指标性参数和变化曲线,确定了"火星探路者"登陆系统的缓冲特性及其仿真分析方法的工程应用。