2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)最新文献_第6页

Design Method of Meridional Contours Based on Velocity Distribution of Multi-stage Composite Impeller 基于速度分布的多级复合叶轮子午轮廓设计方法

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522385

Jiangfeng Fu, Lingsheng Tong, Huacong Li, Xianwei Liu

引用次数: 0

Experimental Study on Multi-method Synchronous Combustion Diagnosis of Aluminized Solid Propellants under 7.5-20 MPa 7.5 ~ 20mpa含铝固体推进剂多方法同步燃烧诊断实验研究

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522405

Yu Liao, Bingning Jin, Lu Liu, Jiang Yuan, Peijin Liu

{"title":"Experimental Study on Multi-method Synchronous Combustion Diagnosis of Aluminized Solid Propellants under 7.5-20 MPa","authors":"Yu Liao, Bingning Jin, Lu Liu, Jiang Yuan, Peijin Liu","doi":"10.1109/ICMAE52228.2021.9522405","DOIUrl":"https://doi.org/10.1109/ICMAE52228.2021.9522405","url":null,"abstract":"Improving the specific impulse of rocket motors has long been a challenge of great interest. One of the widely used methods is to increase the working pressure of combustion chamber. Despite their importance, the difficulty of capturing the combustion characteristics under high pressure has limited our knowledge of combustion stability and reliability of AP/HTPB aluminized propellants. To overcome these limitations, we developed a multi-method combustion diagnostic system built based on a window bomb combustor with 4 optical paths. The maximum working pressure is ~30 MPa. Utilizing high-speed photography, shadowgraph and emission spectroscopy simultaneously to diagnose the combustion of aluminized AP/HTPB composite propellants under high pressure (7.5-20 MPa). This system is suitable for obtaining multiple typical characteristic parameters at the same time, including burning rate, emission spectrum and pressure curve of propellants under different pressures. The results show that, with the increase of pressure, the burning rate and chemiluminescence of propellants increases significantly, and the soot generated by combustion become denser, increasing the difficulty of optical diagnosis. This study lays the groundwork for future research into synchronous combustion diagnostic of composite propellants under ultrahigh pressure (≥ 20 MPa).","PeriodicalId":161846,"journal":{"name":"2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-07-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131942529","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: 2

High Speed Aircraft/Combined Power Integration Analysis 高速飞机/组合动力集成分析

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522400

Q. Hu, Yu-chun Chen, Wenhui Ling, Yuan Gao

{"title":"High Speed Aircraft/Combined Power Integration Analysis","authors":"Q. Hu, Yu-chun Chen, Wenhui Ling, Yuan Gao","doi":"10.1109/ICMAE52228.2021.9522400","DOIUrl":"https://doi.org/10.1109/ICMAE52228.2021.9522400","url":null,"abstract":"Based on the typical mission requirement of near space aircraft and the former integrated analysis model, a new high speed aircraft/combined power integration analysis model which considered angle of attack and climb was developed. Aiming at the wide operation range characters of high speed aircraft, the paper predicted the lift and drag characteristics of high speed aircraf and classified the aircraft to different generations according to the highest lift-to-drag ratio. In the last part, the contraint analysis and mission assessment of intergration were accomplished and the ability of completing mission of the steamjet and tandem TBCC engines was contrasted by using the high speed intergration design and analysis program. According to the results of calculation, several conculsions were reached. The steamjet with better reliability and maneuverability but shorter range can be used to realize the scheudled target of high speed aircraft in a short time; otherwise, the tandem TBCC engine with worse reliability were suited for carrying out long range mission because of its high impluse in the whole flight Mach condition.","PeriodicalId":161846,"journal":{"name":"2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"139 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-07-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125680985","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

Optimization Design of Sliding Bearing of Fuel Pump Based on CFD Method 基于CFD方法的燃油泵滑动轴承优化设计

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522403

Jiangfeng Fu, Yajun Jiang, Huacong Li, Jiaxing Zhu

引用次数: 1

Investigation of Icing Effects on Aerodynamic Performance for the High-Lift Configuration of Civil Aircraft 结冰对民用飞机大升力结构气动性能影响的研究

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522494

Qiming Wang, Meihong Zhang, Jinling Luo, Longqian Zheng

{"title":"Investigation of Icing Effects on Aerodynamic Performance for the High-Lift Configuration of Civil Aircraft","authors":"Qiming Wang, Meihong Zhang, Jinling Luo, Longqian Zheng","doi":"10.1109/ICMAE52228.2021.9522494","DOIUrl":"https://doi.org/10.1109/ICMAE52228.2021.9522494","url":null,"abstract":"For flight safety reason, a better understanding of the effect of ice accretion on the aerodynamic performance is required. The ice shape used in this study is holding ice with one or two ice horns, which accretes on the unprotected surface of the aircraft. By using the verified numerical simulation method, it can be found that due to the effects of holding ice, the stall angle of the aircraft is significantly reduced and lift has a severe penalty. Besides, the pitching moment characteristics are deteriorated, which is a threat to flight safety. The main reason for the pitch up of aircraft with holding ice is the decreases in pitch-down moment of the horizontal tail affected by the iced wing and the increases in pitch-up moment provided by the wing. To avoid this, a method is proposed to improve the aerodynamic performance of iced high-lift configuration, which is shortened inner slat. It can be seen that the obvious improvement in pitching moment characteristics is at the expense of the slight decrease in lift for the iced high-lift configuration. Besides, this method has little effect on aerodynamic performance of the clean configuration.","PeriodicalId":161846,"journal":{"name":"2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-07-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128339183","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

Feasibility Analysis of Integration of Electric Propulsion Technology and Traditional Propulsion Technology 电力推进技术与传统推进技术集成的可行性分析

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522517

Shaowei Zhang, Wenzhang Wang

引用次数: 0

An Investigation of Different Composite on Performance of Pressure Vessel by Filament Winding 不同复合材料对灯丝缠绕压力容器性能的研究

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522551

Ola Abdul Hussain, Najim Abdul Ameer Saad

{"title":"An Investigation of Different Composite on Performance of Pressure Vessel by Filament Winding","authors":"Ola Abdul Hussain, Najim Abdul Ameer Saad","doi":"10.1109/ICMAE52228.2021.9522551","DOIUrl":"https://doi.org/10.1109/ICMAE52228.2021.9522551","url":null,"abstract":"Lightweight composite pressure vessels are very important in many applications such as aerospace, constructions, automotive , energy gas and liquid saving systems due to their high strength and stiffness weight ratios replacing metal alloys in alternative applications. In the present paper, different fibers are used to reinforce epoxy matrix (carbon fiber, Kevlar fiber and E- glass fiber) to fabricate composite pressure vessels with different winding angles orientations [±45°3], [±55°3], [±65°3] and [±75°3] to investigate different mechanical performances like burst pressure and hoop stress. The von-Mises stress of the composites pressure vessel is performed by building a model based on FEM- ACP workbench 17.The obtained results show a strong influence of type of reinforcing fibers and winding orientations on the vessel strength where the maximum pressure recorded up to 100 bar for carbon fiber reinforced laminates which show no failure. While the rest composite laminates exhibit failure. As well as the internal pressure and hoop stress performance show the best results are for composite laminates with [±55°3] angle orientation. The von-Mises stress studies show that best performance is for [±65°3] winding angle observed at Kevlar fiber composite laminate is 4924.8 MPa while the lowest stress value observed with glass fiber composite laminate with [±75°3] winding angle is 606.02 MPa.","PeriodicalId":161846,"journal":{"name":"2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-07-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116917574","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

Aerodynamic Performance of a Two-Dimensional Flapping Elliptic Airfoil in Ground Proximity 二维扑动椭圆翼型近地气动性能研究

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522507

Jit Sinha, S. M. Dash

{"title":"Aerodynamic Performance of a Two-Dimensional Flapping Elliptic Airfoil in Ground Proximity","authors":"Jit Sinha, S. M. Dash","doi":"10.1109/ICMAE52228.2021.9522507","DOIUrl":"https://doi.org/10.1109/ICMAE52228.2021.9522507","url":null,"abstract":"In this numerical study, we have investigated the transient and time-averaged thrust performance of a two-dimensional elliptic airfoil sinusoidally flapping near a flat ground surface. To characterize the ground effects on the aerodynamic performance of the flapping airfoil, we have varied the mean ground clearances of the airfoil, flapping frequency, and pivot location on the airfoil. However, the Reynolds number of the incoming flow and effective angle of attack of the flapping airfoil is fixed as 5000 and 15 degrees, respectively. It is observed that regardless of the mean ground clearance and pivot location, the time-averaged thrust performance of the flapping airfoil increases monotonically with flapping frequency until it reaches a peak value at some critical flapping frequency; beyond which the thrust performance deteriorates considerably. Additionally, we observed when the mean ground clearance is reduced; the time-averaged thrust of the flapping airfoil is augmented at all pivot locations and flapping frequencies. Furthermore, we found that for the considered parameters, the pivot location near the leading-edge side of the airfoil provides a better time-average thrust performance than any other pivot location when the flapping airfoil experiences ground effects. Besides, we noticed that the transient thrust profile in a flapping cycle gets modified with a change in the flapping frequency, pivot location and mean ground clearances. We have thoroughly identified the specific types of transient thrust profiles associated with the increasing and reducing regions of the time-averaged thrust of the flapping airfoil at different pivot locations and mean ground clearances.","PeriodicalId":161846,"journal":{"name":"2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"66 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-07-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121983582","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: 0

Control of Interconnected Drones 互联无人机的控制

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522523

E. Oland

引用次数: 0

Numerical Simulation of Ignition Transient for Solid Rocket Motors with Large Aspect Ratio 大展弦比固体火箭发动机点火瞬态数值模拟

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2021-07-16 DOI: 10.1109/ICMAE52228.2021.9522550

Yanjie Ma, Mingming Zhan, Futing Bao, Lin Sun, Ran Wei

{"title":"Numerical Simulation of Ignition Transient for Solid Rocket Motors with Large Aspect Ratio","authors":"Yanjie Ma, Mingming Zhan, Futing Bao, Lin Sun, Ran Wei","doi":"10.1109/ICMAE52228.2021.9522550","DOIUrl":"https://doi.org/10.1109/ICMAE52228.2021.9522550","url":null,"abstract":"Despite the short duration, ignition transient plays a very important role in the whole operation of a solid rocket motor. A two-dimensional model is proposed to simulate the ignition transient in solid rocket motors with large aspect ratio. Transient mass flow rate inlet is implemented at the inlet of the flow field to simulate the gas from igniter. The temperature of the propellant surface is computed by conduction heat calculation and then is used as a criterion of ignition. Erosive burning is evaluated with Mukunda model. The regression of the burning face is considered, guaranteeing the simulation of the evolvement of erosive burning as the ignition proceeds. The internal ballistics curve obtained from the model meets the experimental data well. The pressure history shows a different trend from that of the burning perimeter, indicating the remarkable influence of erosive burning on the ignition transient. The model proposed in this paper can be used as a reliable approach to simulation of ignition transient for solid rocket motors with large aspect ratio.","PeriodicalId":161846,"journal":{"name":"2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-07-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134451898","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: 0