International Journal of Micro Air Vehicles最新文献_第4页

Dynamic Modeling and Control Law Design of a Fuel-electric Hybrid Multi-rotor UAV 油电混合动力多旋翼无人机动力学建模与控制律设计

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221078925

Xice Xu, Yang Lu, Xufeng Wu

{"title":"Dynamic Modeling and Control Law Design of a Fuel-electric Hybrid Multi-rotor UAV","authors":"Xice Xu, Yang Lu, Xufeng Wu","doi":"10.1177/17568293221078925","DOIUrl":"https://doi.org/10.1177/17568293221078925","url":null,"abstract":"In this paper, the design of control law for a new concept fuel-electric hybrid multi-rotor UAV with lift/attitude control separation is investigated. The remarkable feature of the UAV is that it has a large proportion of fuel weight. Firstly, based on the quasi-coordinate Lagrangian equation and sloshing equivalent model using the multi-mass-spring analogy, the non-linear dynamic model of the UAV considering the fuel slosh dynamics is established. Compared with the existing multi-rotor modeling method, it is more intuitive and accurate to describe the non-linear coupling process of sloshing and UAV's motion degrees of freedom. Secondly, the attitude control law is designed based on the finite-time sliding mode observer and cascaded continuous sliding mode controller to eliminate the adverse effects of fuel sloshing and mass changing, and only using the measurable angles. Furthermore, aiming at the problem of power redundancy of the altitude channel, a memoryless non-linear altitude authority assignment controller based on vertical acceleration is proposed for improving the control performance. Finally, the simulation results of the waypoint flight illustrate the feasibility and effectiveness of the proposed control strategy.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45986266","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Co-simulation platform for geometric design, trajectory control and guidance of racing drones 赛车无人机几何设计、轨迹控制和制导协同仿真平台

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221143785

J.M. Castiblanco Quintero, S. García-Nieto, R. Simarro, J. Salcedo

引用次数: 0

Robust design of compact axial compressor 紧凑型轴流压缩机的稳健设计

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221125847

Cong Zeng, Shaowen Chen, Hongyan Liu

{"title":"Robust design of compact axial compressor","authors":"Cong Zeng, Shaowen Chen, Hongyan Liu","doi":"10.1177/17568293221125847","DOIUrl":"https://doi.org/10.1177/17568293221125847","url":null,"abstract":"The method of connection weights in neural networks was used to analyze the sensitivity of the compressor rotor, and the Back Propagation Neural Network (BPNN) was used to construct the analysis relationship between the compressor rotor's geometries and the performance based on the training and learning of the data base, and the prediction accuracy can reach more than 99.99%. Then the modified Grason Algorithm based on the neural network connect weights was used to quantify the contribution of the geometrical effects on its performance. The result shows that the tip clearance contributes 11.43% (efficiency sensitivity analysis) and 10.18% (pressure ratio sensitivity analysis) to compressor performance changes. This study focuses mainly on the robust optimization of tip clearance. Non-intrusive probability collection point method (NIPC) was adopted for the uncertainty propagation. The robust optimization method based on BPNN agent model coupled with multi-objective genetic algorithm Non-dominated sorting genetic algorithm-II (NSGA II) was used to perform the optimization. Compared to the design prototype, the variance of robust compressor rotor's efficiency could be reduced by 21.04%.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49619960","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Rapid extraction of propeller geometry using photogrammetry 利用摄影测量快速提取螺旋桨几何形状

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221132044

Ellande Tang, Soon-Jo Chung

{"title":"Rapid extraction of propeller geometry using photogrammetry","authors":"Ellande Tang, Soon-Jo Chung","doi":"10.1177/17568293221132044","DOIUrl":"https://doi.org/10.1177/17568293221132044","url":null,"abstract":"As small Uninhabited Aerial Vehicles (sUAS) increase in popularity, computational analysis is increasingly being used to model and improve their performance. However, although propeller performance is one of the primary elements in modelling an aircraft, most manufacturers of propellers for this size of vehicle do not publish geometric information for the propeller. The lack of available geometric data makes simulation of propeller aerodynamics challenging. While techniques exist to accurately extract the 3D geometry of a propeller, these methods are often very expensive, time-consuming, or labor intensive. Additionally, typical 3D scanning techniques produce a 3D mesh that is not useful for techniques such as Blade Element Theory (BET), which rely on knowledge of the 2D cross sections along the propeller span. This paper describes a novel workflow to produce point clouds using readily available photo equipment and software and subsequently extract airfoil and propeller blade parameters at specified stations along the propeller span. The described process can be done with little theoretical knowledge of photogrammetry and with minimal human input. The propeller geometry generated is compared against results of established methods of geometry extraction and good agreement is shown.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44039272","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

On association of lift generation, wake topology and kinematics of oscillating foils 振荡翼升力产生、尾流拓扑和运动学的关联

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293211073959

Suyash Verma, M. Khalid, A. Hemmati

{"title":"On association of lift generation, wake topology and kinematics of oscillating foils","authors":"Suyash Verma, M. Khalid, A. Hemmati","doi":"10.1177/17568293211073959","DOIUrl":"https://doi.org/10.1177/17568293211073959","url":null,"abstract":"The association of lift generation and evolution of wake topology behind an oscillating foil with combined heaving and pitching motion is investigated numerically at a range of bluereduced frequency (0.16 ≤ f * ≤ 0.48), phase offset (0 ∘ ≤ ϕ ≤ 315 ∘ ) and Reynolds number (1000 ≤ R e ≤ 4000). The pitch-dominated kinematics that coincide with the range of ϕ ≤ 120 ∘ and ϕ ≥ 225 ∘ suggests that leading edge vortices are suppressed while trailing edge vortices dominate the wake with increasing reduced frequency. This corresponds to a transition in wake topology from a 2 P to a reverse Von Kármán wake mode. Contrarily, heave dominated kinematics (120 ∘ < ϕ ≤ 225 ∘ ) did not exhibit any wake topology transition with increasing f * . The temporal lift variation associated with heave-dominated regime further revealed a symmetric feature in terms of the time taken to attain peak lift generation within an oscillation cycle. This temporal symmetry was, however, lost as kinematics transitioned from heave- to pitch-dominated regime. Analyzing the wake evolution and lift features at quarter phase of an oscillation cycle revealed the existence of a correspondence between the two processes during the heave- and pitch-dominated kinematics.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45950882","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 4

An implementation framework for vision-based bat-like inverted perching with bi-directionalthrust quadrotor 基于视觉的双向推力四旋翼类蝙蝠倒立栖息实现框架

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293211073672

Pengfei Yu, K. Wong

{"title":"An implementation framework for vision-based bat-like inverted perching with bi-directionalthrust quadrotor","authors":"Pengfei Yu, K. Wong","doi":"10.1177/17568293211073672","DOIUrl":"https://doi.org/10.1177/17568293211073672","url":null,"abstract":"This paper presents an implementation framework to perform a vision-guided, bat-like inverted perching maneuver with a bi-directional thrust quadrotor platform. The framework consists of several distinct modules (guidance, motion planning, control, state estimation) that can be easily be individually customized in the future to meet specific research requirements. The main contribution of this paper lies in the whole framework pipeline with a modular structure developed for implementing a generalized framework for an agile quadrotor to achieve inverted perching. A computationally-light guidance module has been developed as an example to demonstrate the capability while being independent of accurate pre-known target information, and does not require the state estimation of the quadrotor to be provided by an external motion capture system as in our previous work. A motion planning module based on an optimization method has been introduced to generate a two-stage inverted perching trajectory aiming at minimizing altitude loss during the half-flip maneuver. A control module has been developed to enable a bi-directional quadrotor to fly in both upright and inverted states and closely follow the intended trajectory. The compensation strategy used in the control module is key to minimizing the transition time between the upright and inverted states. Finally, an experimental flight platform has been developed to demonstrate the capabilities of the framework. During testing, the proposed framework has achieved an 80 % success rate. To the best of our knowledge, this paper presents the first time a quadrotor has achieved the inverted perching maneuver using onboard vision guidance.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48139098","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

Estimating wind using a quadrotor 使用四旋翼机估算风

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293211070824

G. Hattenberger, M. Bronz, Jean-Philippe Condomines

引用次数: 3

Simulation of the flapping wing aerial vehicle using flexible multibody dynamics 扑翼飞行器柔性多体动力学仿真

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2021-10-20 DOI: 10.1177/17568293211043305

JaeWon Choi, DuHyun Gong, Junhee Lee, Chongam Kim, SangJoon Shin

引用次数: 0

A new nonlinear lifting line method for aerodynamic analysis and deep learning modeling of small unmanned aerial vehicles 基于非线性升力线的小型无人机气动分析与深度学习建模新方法

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2021-01-01 DOI: 10.1177/17568293211016817

Hasan Karali, G. Inalhan, M. Umut Demirezen, M. Adil Yukselen

{"title":"A new nonlinear lifting line method for aerodynamic analysis and deep learning modeling of small unmanned aerial vehicles","authors":"Hasan Karali, G. Inalhan, M. Umut Demirezen, M. Adil Yukselen","doi":"10.1177/17568293211016817","DOIUrl":"https://doi.org/10.1177/17568293211016817","url":null,"abstract":"In this work, a computationally efficient and high-precision nonlinear aerodynamic configuration analysis method is presented for both design optimization and mathematical modeling of small unmanned aerial vehicles. First, we have developed a novel nonlinear lifting line method which (a) provides very good match for the pre- and post-stall aerodynamic behavior in comparison to experiments and computationally intensive tools, (b) generates these results in order of magnitudes less time in comparison to computationally intensive methods such as computational fluid dynamics. This method is further extended to a complete configuration analysis tool that incorporates the effects of basic fuselage geometries. Moreover, a deep learning based surrogate model is developed using data generated by the new aerodynamic tool that can characterize the nonlinear aerodynamic performance of unmanned aerial vehicles. The major novel feature of this model is that it can predict the aerodynamic properties of unmanned aerial vehicle configurations by using only geometric parameters without the need for any special input data or pre-process phase as needed by other computational aerodynamic analysis tools. The obtained black-box function can calculate the performance of an unmanned aerial vehicle over a wide angle of attack range on the order of milliseconds, whereas computational fluid dynamics solutions take several days/weeks in a similar computational environment. The aerodynamic model predictions show an almost 1-1 coincidence with the numerical data even for configurations with different airfoils that are not used in model training. The developed model provides a highly capable aerodynamic solver for design optimization studies as demonstrated through an illustrative profile design example.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2021-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1177/17568293211016817","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42571483","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 6

Experimental study on the dynamic behaviour of drones designed for racing competitions 竞赛用无人机动力特性试验研究

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2021-01-01 DOI: 10.1177/17568293211005757

Jose M Castiblanco, S. García-Nieto, R. Simarro, JV Salcedo

引用次数: 3