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2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)最新文献

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Research on autonomous capability assessment technology for large civilian UAVs 大型民用无人机自主能力评估技术研究
Wenqiang Yin, Yalong Wang
Based on its advantages of wide application fields, low manufacturing cost and long working hours, the mission demand of large civilian UAVs in the market is expanding, and their usage patterns and safety features have become the future development direction, which has put forward higher requirements on the autonomous capability of UAVs. Carrying out the autonomous capability assessment of large civil UAVs is of great significance to their market positioning and application scenarios. In this paper, an autonomous capability assessment method is proposed for large civil UAVs. The method classifies the autonomous capability level of large civil UAVs, then sorts out the autonomous capability evaluation elements, and finally determines the autonomous capability flight test verification content and formulates corresponding assessment guidelines, which can provide guidance for the autonomous capability assessment of large civil UAVs and that can also provide guidance for other types of UAVs.
基于其应用领域广、制造成本低、工作时间长的优势,市场上大型民用无人机的任务需求不断扩大,其使用模式和安全特性成为未来的发展方向,这对无人机的自主能力提出了更高的要求。开展大型民用无人机自主能力评估对其市场定位和应用场景具有重要意义。提出了一种大型民用无人机自主能力评估方法。该方法对大型民用无人机的自主能力等级进行分类,然后对自主能力评估要素进行梳理,最后确定自主能力飞行试验验证内容并制定相应的评估导则,可为大型民用无人机的自主能力评估提供指导,也可为其他类型无人机提供指导。
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引用次数: 0
Study on the correlation between characteristic peaks of infrared absorption spectra and maximum elongation of HTPB propellant HTPB推进剂红外吸收光谱特征峰与最大伸长率的相关性研究
Zhihong Yan, X. Sui
In order to explore the correlation between the characteristic peaks of infrared absorption spectrum and the maximum elongation of HTPB propellant, the tensile test and Fourier infrared spectrum test of HTPB propellant after accelerated aging at 50 centigrade,60 centigrade and 70 centigrade were carried out. S-G smoothing filtering method and derivative spectrum method were used to process the infrared spectrum data, and the correlation between the infrared spectrum data and the maximum elongation was analyzed. The results show that the characteristic peak wave number of infrared absorption spectrum is highly related to the maximum elongation, and the fitting formula between the characteristic peak of infrared absorption spectrum and the maximum elongation is established at the wave number 1785cm-l; It was found that the maximum elongation of HTPB propellant decreases first in the aging process, then after a plateau period or rising period, and finally maintains a downward trend.
为了探索HTPB推进剂红外吸收光谱特征峰与最大伸长率之间的相关性,对HTPB推进剂在50℃、60℃和70℃加速老化后的拉伸试验和傅里叶红外光谱试验进行了研究。采用S-G平滑滤波法和导数光谱法对红外光谱数据进行处理,分析红外光谱数据与最大伸长率的相关性。结果表明:红外吸收光谱特征峰波数与最大伸长率高度相关,并在波数1785cm-l处建立了红外吸收光谱特征峰与最大伸长率的拟合公式;研究发现,HTPB推进剂的最大伸长率在老化过程中先下降,然后经过一个平台期或上升期,最后保持下降趋势。
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引用次数: 0
Research on Vacuum Fire Absorption Technology for Manned Spacecraft 载人航天器真空吸火技术研究
Zhanbin Fan, Jiang Luo, Yuan Zhang, Q. Bian, Z. Liang, Wubo Huang, Bingtian Jie
At present, the fire extinguisher used in manned spacecraft has some problems that are difficult to solve. For example, the use of carbon dioxide in a narrow and closed environment has a great impact on the air quality of small space, and the medium after combustion in microgravity environment is scattered everywhere. The above problems can be solved by a kind of suction technology for negative pressure. In this paper, a vacuum lire suction experimental device is designed to meet the requirements of spacecraft lire suppression. The typical fire suppression process of spacecraft by vacuum lire suction technology is studied, which provides data support for the practical application of vacuum fire suction technology in manned spacecraft.
目前,载人航天器上使用的灭火器存在一些难以解决的问题。例如,在狭窄封闭的环境中使用二氧化碳对小空间的空气质量影响很大,微重力环境中燃烧后的介质散落各处。采用一种负压吸力技术可以解决上述问题。本文设计了一种满足航天器生命抑制要求的真空活吸实验装置。研究了真空吸火技术在航天器上的典型灭火过程,为真空吸火技术在载人航天器上的实际应用提供了数据支持。
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引用次数: 0
Analysis Of The Wings And Powerplant Changes At The Time Of Civil Aircraft Variant Development 民机改型发展时期机翼和动力装置变化分析
D. Tiniakov, L. Makarova, O. Dveirin
For the transport category aircraft variants creation there are some ways. They are: keeping constant area and other geometric parameters of a wing and solve this task by the serious modification of a powerplant; modifying area and geometric parameters of a wing for an existing powerplant. Both of these ways have their own advantages, but in time for their realization there are some problems: excessive growth of new variant airplanes’ takeoff weight; possible derating of the takeoff and landing performance for a new airplane’s variant; derating of the fuel efficiency and other integral airplane’s performances that are reasons for the decreasing of the new variant’s competitive. The best performance of the new variant airplane can be obtained only at one condition: these changes are created synchronously and consistently. In the article the way of such changes coordination for increasing cargo capacity, flight range and fuel efficiency of new aircraft variant was created. The main specific of the proposed way is modification changes of a wing geometric parameters are providing of the decreasing its inductive drag for given lift. The model of design changes influence of wing geometric parameters such as taper ratio and local chords twist angle that are depending on elliptical factor of taper wing, to wings polar graph and its lift-to-drag ratio are proposed. Step-by-step evaluation for aerodynamic quality dependence on required values of lift coefficient CL and specific lift coefficient $overline{C}_{L}$ are given. CL and $overline{C}_{L}$ depend on coordination of modification changes for a wing and powerplant performance. The scope of lift-to-drag ratio $K(C_{L})$ for possible applying of required cargo capacity increasing was determined. Obtained results that relate to simulation of geometric wing changes are inherent part of the deep modification changes coordination for a wing and powerplant, which are needed for new aircraft variant creation with higher productivity.
对于运输类飞机变体的创建有一些方法。它们是:保持机翼的面积和其他几何参数不变,并通过对动力装置进行重大改造来解决这一任务;修改现有动力装置机翼的面积和几何参数。这两种方式各有优点,但在实现这两种方式的同时也存在一些问题:新型飞机起飞重量增长过快;一种新型飞机的起降性能可能出现的降额;燃油效率和其他整体飞机性能的下降是新机型竞争力下降的原因。新改型飞机的最佳性能只有在一个条件下才能获得:这些变化是同步和一致的。本文提出了为提高新机型的载货能力、航程和燃油效率而进行这种变化协调的方法。该方法的主要特点是在给定升力的情况下,通过改变机翼几何参数来减小其感应阻力。建立了锥度比、局部弦扭角等几何参数对设计变化的影响模型,这些参数取决于锥度翼的椭圆因子、翼的极坐标图及其升阻比。给出了气动质量依赖于升力系数CL和比升力系数$overline{C}_{L}$所需值的逐步评价。CL和$overline{C}_{L}$取决于机翼和动力装置性能的修改变化的协调。确定了可能应用所需载货能力增加的升阻比$K(C_{L})$的范围。与机翼几何变化仿真相关的所得结果是机翼与动力装置深度改型协调的内在组成部分,是提高飞机生产效率的新机型所需要的。
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引用次数: 0
The Impact and Mechanism Analysis of Effect of Incoming Flow Velocity on Aerodynamic of Flying Wing Model with Low Aspect Ratio 来流速度对低展弦比飞翼模型气动性能的影响及机理分析
Zeng Wei-yi, Zhao Zhong-liang, Yang Hai-yong, Wang Xiao-bin
With the development of modern air combat and the intensification of military confrontation, modern battlefields have put forward higher demands for the lift and drag characteristics and stealth characteristics of fighters. Because the configuration of flying wing with low aspect ratio removes the tail wing and adopts the wing body fusion design, its lift and drag characteristics and stealth are significantly better than the traditional configuration of wing body separation body. The configuration of flying wing with low aspect ratio has been widely concerned by aviation scientists from various countries and has been determined as the development direction of the future fighter configuration. Aircraft often fly at different speeds on the battlefield. Therefore, it is important to investigate the influence of different incoming flow speeds on the aerodynamic force of flying wing with low aspect ratio and to conduct mechanism analysis. In order to explore the influence of different incoming velocity on the aerodynamic coefficients of the configuration of flying wing with low aspect ratio and the underlying mechanism, the FL-24 wind tunnel of the China Aerodynamics Research and Development Center High Speed Institute conducted a test of the standard model of the flying wing with low aspect ratio. The test with flow Mach number of 0.4, 0.6, 0.8 obtained the normal force coefficient curve and found that the normal force coefficient decreases with the increase of Mach number at high angles of attack. The IDDES turbulence model is used to numerically calculate the standard mode, and the specific flow field details are obtained to explain the flow mechanism behind the phenomenon.
随着现代空战的发展和军事对抗的加剧,现代战场对战斗机的升阻特性和隐身特性提出了更高的要求。由于低展弦比飞翼构型去除了尾翼,采用翼身融合设计,其升力、阻力特性和隐身性能明显优于传统的翼身分离体构型。低展弦比飞翼构型受到各国航空科学家的广泛关注,并被确定为未来战斗机构型的发展方向。飞机在战场上经常以不同的速度飞行。因此,研究不同来流速度对低展弦比飞翼气动力的影响并进行机理分析具有重要意义。为探索不同来流速度对低展弦比飞翼构型气动系数的影响及其机理,中国空气动力研究与发展中心高速研究所FL-24风洞对低展弦比飞翼标准模型进行了试验。在流动马赫数为0.4、0.6、0.8时进行试验,得到了法向力系数曲线,发现在大攻角下,法向力系数随马赫数的增加而减小。采用IDDES湍流模型对标准模态进行数值计算,得到具体的流场细节来解释现象背后的流动机理。
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引用次数: 1
Mechanical Design of a Novel 4DOF Serial Manipulator 一种新型四自由度串联机械手的机械设计
Bahador Beigomi, Dan Zhang
In this paper, a strategy to accomplish small stone carving operations using a four-degree-of-freedom (DOF) robotic arm is presented. This research work tries to design a novel robotic arm that is small enough that can be mounted on the table and create artwork by carving and shaping stones. In the past two decades, there were many different designs for the robotic arm from simple 3DoF serial manipulator to advanced hybrid one, but the main thing in those designs was that they have been designed in order to use on an industrial scale. In this design what we have considered as a priority is to create a manipulator that can be mounted on a small table and also could be used by nonprofessionals. The designed robot, CarveARM, has a unique End Effector (EE) which is rotating around itself so fast to carve a stone precisely. At first, by gathering the link transformation matrices between each joint and also using the Denavit-Hartenberg (DH) notations the CarveARM manipulator coordinate transformation is completely described. We have also used some robotics methods to achieve some particular tasks such as solving the forward kinematics description, inverse kinematics problem, workspace evaluation, and dexterity analysis. Besides the position control of EE, we also control the final angle of EE to handle the stone carving procedure more accurately.
提出了一种利用四自由度机械臂完成小型石雕作业的策略。这项研究工作试图设计一种新颖的机械臂,它足够小,可以安装在桌子上,通过雕刻和塑造石头来创作艺术品。在过去的二十年里,有许多不同的机械臂设计,从简单的三维连续机械臂到先进的混合机械臂,但这些设计的主要目的是为了在工业规模上使用。在这个设计中,我们优先考虑的是创造一个可以安装在小桌子上的机械手,也可以被非专业人士使用。这款名为CarveARM的机器人有一个独特的末端执行器(EE),它可以围绕自身快速旋转,从而精确地雕刻石头。首先,通过收集每个关节之间的连杆变换矩阵,并使用Denavit-Hartenberg (DH)符号,完整地描述了CarveARM机械手的坐标变换。我们还使用一些机器人方法来实现一些特定的任务,如求解正运动学描述、逆运动学问题、工作空间评估和灵巧性分析。除了EE的位置控制,我们还控制EE的最终角度,以更准确地处理石雕过程。
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引用次数: 0
Performance Analysis of Pre-launch Attitude Compound Control Method Based on Grid Rudder and RCS 基于栅格舵和RCS的发射前姿态复合控制方法性能分析
Weiqi Xie, Long Cheng, Yan Li, Jingwei Jingwei-An
Based on the feasibility of the pre-launch attitude composite control method based on grid rudder+RCS (Reaction Control System), the anti-interference ability of the single channel and three channel pre-launch attitude composite control methods is analyse by adding interference torque. The results show that the pre-launch attitude composite control method has strong anti-interference ability and can complete the attitude control task of the launch vehicle. The robustness of the composite control method is analysed by introducing the environmental error and aerodynamic coefficient error to simulate the atmospheric environment change of the rocket in the real environment. The results show that the composite control method has good robustness to the atmospheric density change and aerodynamic coefficient error within the control capability range, which further verifies the feasibility and effectiveness of the method. At the same time, the pre-launch attitude composite control method based on grid rudder+RCS is compared with the more mature stable parachute control method and “stable parachute+control platform” control method. The results show that the designed composite scheme has obvious advantages in control accuracy and control speed, and not only realizes three channel closed-loop active control; It can also reduce the height and speed loss of the arrow body, and clarify the advantages of the composite control method.
基于栅格舵+RCS(反应控制系统)预发射姿态复合控制方法的可行性,通过增加干扰力矩,分析了单通道和三通道预发射姿态复合控制方法的抗干扰能力。结果表明,该发射前姿态复合控制方法具有较强的抗干扰能力,能够完成运载火箭的姿态控制任务。通过引入环境误差和气动系数误差来模拟火箭在真实环境中的大气环境变化,分析了复合控制方法的鲁棒性。结果表明,复合控制方法在控制能力范围内对大气密度变化和气动系数误差具有良好的鲁棒性,进一步验证了该方法的可行性和有效性。同时,将基于栅格舵+RCS的发射前姿态复合控制方法与较为成熟的稳定降落伞控制方法和“稳定降落伞+控制平台”控制方法进行了比较。结果表明,所设计的组合方案在控制精度和控制速度上具有明显的优势,不仅实现了三通道闭环主动控制;还可以减少箭身的高度和速度损失,阐明复合控制方法的优点。
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引用次数: 0
Transient numerical investigation of a thermal-driving water pipe cooling system 热驱动水管冷却系统的瞬态数值研究
Yun Luan, Junhang Luo, Beibei Wu, F. He, Jian-hua Wang
For a simple water cooling system, which consists of a U-shaped round pipe and a reservoir, how to discharge the vapor generated in the heated pipe during the cooling process is an interesting topic, especially when pumps or other driving units are hard to install and maintain in the device. In this paper, a thermal-driving method is proposed. By adding different heat fluxes on different parts of the U-shaped pipe, the fluid density difference between those parts can drive a natural circulation of fluid in the loop, and then the vapor bubbles can be discharged with the flow. Numerical simulations are carried out to study the transient performances of the thermal-driving water pipe cooling system under different heat flux distributions. The aim is to obtain the mechanism and evolution law of fluid movement, phase change and heat dissipation. The numerical results indicate that, when the heat flux is uniformly added on the whole pipe, slugs appear in the vertical pipe and where local heat transfer deterioration occurs. When the heat fluxes are different on the left and right vertical parts of the pipe, an overall circulating flow generates. In this process, small vapor bubbles can be discharged, which avoids the formation of the vapor slugs, and the system works stably at boiling point thereby. In addition, with an increase in the heat flux difference between the two vertical parts of the pipe, the initial time of the overall circulating flow shortens.
对于一个简单的水冷却系统,它由一个u型圆管和一个储水箱组成,如何排出在冷却过程中加热管中产生的蒸汽是一个有趣的话题,特别是当泵或其他驱动装置在设备中难以安装和维护时。本文提出了一种热驱动方法。通过在u型管的不同部位加入不同的热流密度,使各部位之间的流体密度差驱动回路中流体的自然循环,从而使汽泡随流排出。通过数值模拟研究了不同热流密度分布下热驱动水管冷却系统的瞬态性能。目的是获得流体运动、相变和散热的机理和演化规律。数值结果表明,当全管均匀加热流密度时,垂直管内出现弹塞,局部传热恶化。当管道左右垂直部位的热流密度不同时,产生整体循环流。在此过程中,可以排出小的蒸汽泡,避免了蒸汽塞状物的形成,从而使系统在沸点下稳定工作。此外,随着管道两垂直部分热流密度差的增大,整体循环流动的起始时间缩短。
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引用次数: 0
Attitude Control of the Low Earth Orbit Satellite with Moving Masses under Strong Aerodynamic Disturbance 强气动扰动下低地球轨道运动质量卫星的姿态控制
Yuandong Hu, Zhen Lu, W. Liao, X. Zhang
This study investigates an attitude control scheme for the satellite with moving masses and reaction wheels to solve the problem of the strong aerodynamic disturbance in low Earth orbit. The moving mass actuator is introduced to minimize the influence of the aerodynamic torque, so as to avoid the frequent saturation of the reaction wheel speed. The rotational dynamic equations of the attitude and the translational dynamic equations of the masses are derived by Newtonian mechanics. The dynamic effects of the mass movement are analyzed. A nonlinear observer is used for the precise estimation of the system disturbance to minimize the effects of the disturbance on attitude control through feedforward compensation. An incremental discrete PID control algorithm is used to slow down the mass movement and reduce the dynamic effects. The aerodynamic torque can be used to actively compensate the system disturbance in y and z axes of the body system without knowing structural parameters of the satellite. The numerical simulation indicates that the satellite is capable of maintaining the attitude convergence accuracy within ±0.1° all the time despite strong and uncertain aerodynamic torque. The results verify the feasibility and effectiveness of the proposed control scheme for the satellite with moving masses and reaction wheels.
为解决近地轨道强气动扰动问题,研究了一种动质量反作用轮卫星姿态控制方案。引入动质量作动器,最大限度地减少气动力矩的影响,避免反力轮转速频繁饱和。利用牛顿力学推导了姿态的旋转动力学方程和质量的平移动力学方程。分析了质量运动的动力效应。采用非线性观测器对系统扰动进行精确估计,通过前馈补偿使扰动对姿态控制的影响最小化。采用增量式离散PID控制算法,减缓质量运动,减小动态影响。在不知道卫星结构参数的情况下,利用气动力矩主动补偿体系y轴和z轴的系统扰动。数值模拟结果表明,在较大且不确定的气动力矩作用下,卫星始终能保持姿态收敛精度在±0.1°以内。仿真结果验证了所提控制方案对具有运动质量和反作用轮的卫星的可行性和有效性。
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引用次数: 0
Modelling the Deformation Characteristics of Titanium Diaphragm for a Spacecraft Propellant Tank 航天器推进剂储罐钛合金膜片的变形特性建模
W. Yang, S. Gu, Ji-peng Zhao, T. Ma, Bin Yu, Yu Jiang
In order to investigate the deformation characteristics of titanium diaphragm for a spacecraft propellant tank during its reversal process, Based on FE software MSC. Marc, a FE model of the reversal process of the titanium diaphragm is established. In this model, the nonlinear thickness distributions of the diaphragm are coupled by a MSC. Marc subprogram. With the aid of the model, the paper analyses the characteristics of different field variables during the whole reversal process, such as pressure drop, equivalent von mises stress, equivalent plastic strain and apex displacement. The results show that the deformation of the diaphragm is relatively stable during the reversal process. Simulated values of pressure differential show good agreement with measured ones.
为了研究航天器推进剂储罐钛合金膜片在翻转过程中的变形特性,基于有限元软件MSC。建立了钛合金膜片翻转过程的有限元模型。在该模型中,膜片的非线性厚度分布通过MSC进行耦合。马克·子程序。借助该模型,分析了整个逆转过程中不同场变量的特征,如压降、等效冯米塞斯应力、等效塑性应变和顶点位移。结果表明,在反转过程中,膜片的变形是相对稳定的。压差模拟值与实测值吻合较好。
{"title":"Modelling the Deformation Characteristics of Titanium Diaphragm for a Spacecraft Propellant Tank","authors":"W. Yang, S. Gu, Ji-peng Zhao, T. Ma, Bin Yu, Yu Jiang","doi":"10.1109/icmeas54189.2021.00024","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00024","url":null,"abstract":"In order to investigate the deformation characteristics of titanium diaphragm for a spacecraft propellant tank during its reversal process, Based on FE software MSC. Marc, a FE model of the reversal process of the titanium diaphragm is established. In this model, the nonlinear thickness distributions of the diaphragm are coupled by a MSC. Marc subprogram. With the aid of the model, the paper analyses the characteristics of different field variables during the whole reversal process, such as pressure drop, equivalent von mises stress, equivalent plastic strain and apex displacement. The results show that the deformation of the diaphragm is relatively stable during the reversal process. Simulated values of pressure differential show good agreement with measured ones.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131096803","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 1
期刊
2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)
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