International Journal of Micro Air Vehicles最新文献_第3页

Extended incremental non-linear control allocation (XINCA) for quadplanes 四平面的扩展增量非线性控制分配（XINCA）

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293211070825

H. J. Karssies, C. De Wagter

{"title":"Extended incremental non-linear control allocation (XINCA) for quadplanes","authors":"H. J. Karssies, C. De Wagter","doi":"10.1177/17568293211070825","DOIUrl":"https://doi.org/10.1177/17568293211070825","url":null,"abstract":"Hybrid UAVs have gained a lot of interest for their combined vertical take-off & landing (VTOL) and efficient forward flight capabilities. But their control is facing challenges in over-actuation and conflicting requirements depending on the flight phase which can easily lead to actuator saturation. Incremental Non-linear Control Allocation (INCA) has been proposed to solve the platform’s control allocation problem in the case of saturation or over-actuation by minimizing a set of objective functions. This work demonstrates INCA on quadplanes, an in-plane combination between a quadrotor and a conventional fixed-wing, and proposes an extension to control the outer loop. The novel controller is called Extended INCA (XINCA) and adds the wing orientation as a force-generating actuator in the outerloop control optimization. This leads to a single controller for all flight phases that avoids placing the wing at negative angles of attack and minimizes the load on hover motors. XINCA has low dependence on accurate vehicle models and requires only several optimization parameters. Flight simulations and experimental flights are performed to demonstrate the performance.","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":"47403059","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

Design optimization-under-uncertainty of a forward swept wing unmanned aerial vehicle using SAMURAI 基于SAMURAI的前掠翼无人机不确定设计优化

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221092139

J. Wauters

{"title":"Design optimization-under-uncertainty of a forward swept wing unmanned aerial vehicle using SAMURAI","authors":"J. Wauters","doi":"10.1177/17568293221092139","DOIUrl":"https://doi.org/10.1177/17568293221092139","url":null,"abstract":"In this paper the design optimization-under-uncertainty of a forward swept wing (FSW) blended wing body (BWB) unmanned aerial vehicle (UAV) is examined. Conventional BWBs are often tailless, which leads to a backward swept wing to ensure longitudinal static stability. This in turn can induce flow separation at the tip, leading to a loss of lift, controllability and the appearance of a nose-up pitching moment. A possible solution to this problem is a conceptual redesign by introducing a forward swept wing, which is inherently free of tip-stall, but needs a careful design in order to be controllable. However, fixed wing UAVs are often produced by means of direct injection expanded foam moulding, which is characterized by not negligible production tolerances. This lead to a reliability-based robust design optimization problem, for which a novel framework is employed: SAMURAI. Firstly, the method accounts for computational cost by means of surrogate modelling, an analytical treatment of the problem and an asynchronous updating scheme that balances design space exploration and objective exploitation. Secondly, the method treats the problem as a multi-objective problem, which leads to a Pareto front of robust and reliable designs. The result is a novel series of UAV designs that are inherently free of tip stall, perform robustly and meet the stability requirements with the target reliability obtained with a computationally feasible budget.","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":"49023515","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

Wind tunnel tests of a wing at all angles of attack 在风洞中对机翼进行各种迎角的测试

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221110931

Ziqing Ma, E. Smeur, G. C. de Croon

{"title":"Wind tunnel tests of a wing at all angles of attack","authors":"Ziqing Ma, E. Smeur, G. C. de Croon","doi":"10.1177/17568293221110931","DOIUrl":"https://doi.org/10.1177/17568293221110931","url":null,"abstract":"Tailsitters have complex aerodynamics that make them hard to control throughout the entire flight envelope, especially at very high angle of attack (AoA) and reverse flow conditions. The development of controllers for these vehicles is hampered by the absence of publicly available data on forces and moments experienced in such conditions. In this paper, wind tunnel experiments are performed under different flap deflections and throttle settings at all possible AoA. The dataset is made open access. Our analysis of the data shows for the tested wing, flap deflections greatly affect the lift coefficient and stall occurs at ± 15 ∘ AoA as well as ± 160 ∘ . Wing-propeller interaction is studied by analyzing the propeller induced force in the axis orthogonal to the thrust axis, which is dependent on AoA, airspeed, flap deflections and thrust in a nonlinear and coupled manner. The influence of inverse flow on the wing is also discussed: The data confirm that when the airflow over the wing is reversed, flap deflections will affect the pitch moment in an opposite way compared to the non-reversed case, but this opposite effect can be avoided by increasing the throttle setting. The data show the exact relationship between flap deflections and forces in this condition. Moreover, it is found that the flap control effectiveness for a wing with or without spinning propellers is usually higher around zero degrees AoA than at ± 180 ∘ and it is more effective to change the flaps from 0 ∘ to ± 18.91 ∘ than from ± 18.91 ∘ to the respective ± 37.82 ∘ .","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":"46649811","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

Nonlinear model predictive control for improving range-based relative localization by maximizing observability 通过最大化可观测性改进基于距离的相对定位的非线性模型预测控制

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293211073680

Shushuai Li, C. De Wagter, G. de Croon

引用次数: 1

Field report: Deployment of a fleet of drones for cloud exploration 现场报道:部署无人机编队进行云探测

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293211070830

G. Hattenberger, Titouan Verdu, N. Maury, P. Narvor, F. Couvreux, M. Bronz, S. Lacroix, G. Cayez, Gregory Charles Roberts

引用次数: 1

Design, development, and flight testing of a tube-launched coaxial-rotor based micro air vehicle 管射同轴旋翼微型飞行器的设计、研制和飞行试验

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221117189

H. Denton, Moble Benedict, Hao Kang

引用次数: 1

Aeroacoustic optimization of MAV rotors MAV旋翼的气动声学优化

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293211070827

Pietro Li Volsi, David Gómez-Ariza, R. Gojon, T. Jardin, J. Moschetta

引用次数: 6

Analyzing visual imagery for emergency drone landing on unknown environments 无人机紧急降落在未知环境中的视觉图像分析

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221106492

O. Bektash, J. Naundrup, A. la Cour-Harbo

引用次数: 3

Numerical study on aerodynamic characteristics of two-dimensional propulsive wing in cruise and hover 巡航和悬停时二维推进翼气动特性的数值研究

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221122170

Jiaxin Lu, Yang Lu, Junjie Wang, Mengxue Shao

{"title":"Numerical study on aerodynamic characteristics of two-dimensional propulsive wing in cruise and hover","authors":"Jiaxin Lu, Yang Lu, Junjie Wang, Mengxue Shao","doi":"10.1177/17568293221122170","DOIUrl":"https://doi.org/10.1177/17568293221122170","url":null,"abstract":"The propulsive wing vehicle is a new concept vehicle, which is driven by a cross-flow fan (CFF) embedded in the trailing edge of the wing. The propulsive wing vehicle is capable of cruising and hovering at high angles of attack with very high aerodynamic force coefficients, and has the potential to become a new type of vertical take-off and landing (VTOL) vehicle. The cruise and hover states of the propulsive wing vehicle are defined, and a numerical model of the two-dimensional propulsive wing is established. Based on the computational fluid dynamics (CFD) method, the rotation of the CFF is simulated by using the sliding mesh technique. The effects of cruise speed, angle of attack and CFF rotation speed on the aerodynamics of the two-dimensional propulsive wing are evaluated, and the mechanism of the propulsive wing flow field changes is revealed. The results show that the propulsive wing has a very high lift coefficient of up to 60 at low speed and high angle of attack cruise, and a high thrust coefficient of up to 40 at low speed and small angle of attack cruise. The aerodynamic force of the propulsive wing fluctuates periodically with the rotation of the CFF, and the amplitude of the fluctuation is related to the vorticity of the CFF blade shedding vortex. In hover, the flow field of the propulsive wing is affected by the geometry and wake deflection into an asymmetric distribution, forming a vortex on each side of the airfoil, and the vortex diameter varies with the CFF rotation speed, which in turn has an impact on the hovering performance of the propulsive wing.","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":"42520543","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: 3

Vortex particle method with iterative Brinkman penalization for simulation of flow past sharp-shape bodies 具有迭代Brinkman惩罚的涡质点法模拟尖形状物体的流动

IF 1.4 4区工程技术

International Journal of Micro Air Vehicles Pub Date : 2022-01-01 DOI: 10.1177/17568293221113927

V. D. Duong, L. Zuhal

引用次数: 1