Journal of aeronautics, astronautics and aviation, Series A最新文献_第3页

A No-Subset Method for ARAIM of Tightly-Coupled GNSS/INS to Reduce Computational Load 一种减少计算量的GNSS/INS紧耦合ARAIM无子集方法

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2020-09-01 DOI: 10.6125/JOAAA.202009_52(3).03

W. Pan, X. Zhan, Xin Zhang, Rong Yang

{"title":"A No-Subset Method for ARAIM of Tightly-Coupled GNSS/INS to Reduce Computational Load","authors":"W. Pan, X. Zhan, Xin Zhang, Rong Yang","doi":"10.6125/JOAAA.202009_52(3).03","DOIUrl":"https://doi.org/10.6125/JOAAA.202009_52(3).03","url":null,"abstract":"Advanced Receiver Autonomous Integrity Monitoring (Advanced RAIM, ARAIM) is the next generation of RAIM which is widely used in air transport. Based on tight integration of Global Navigation Satellite System (GNSS) and Inertial Navigation System (INS), the GNSS/INS ARAIM attracts wide attention for its high performance with no additional cost. However, both of GNSS alone ARAIM and GNSS/INS ARAIM have to compute fault-tolerant position solutions of a large number of subsets, which results in a huge computational load. In this paper, a no-subset method for GNSS/INS ARAIM is proposed to conduct the fault detection test and to obtain the integrity and accuracy performances by computing a tight upper bound of the fault detection statistics and a tight bound of standard deviations of position errors, instead of the fault detection statistics and standard deviation of each subset. The computational load of the proposed algorithm is about 1% of that of the current GNSS/INS ARAIM, which facilitates its application in the airborne navigation system. Moreover, the simulation results show that the integrity and accuracy performances of the proposed GNSS/INS ARAIM are able to meet the corresponding requirements of CATI with global coverage.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126523056","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

Stable Inversion Based Fault-tolerant Trajectory Tracking Control of Civil Aircrafts Autolanding 基于稳定反演的民机自动着舰容错轨迹跟踪控制

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2020-09-01 DOI: 10.6125/JOAAA.202009_52(3).02

Xudong Wang, Shiqian Liu, Huihui Cheng, Y. Sang, Xinjian Ma

{"title":"Stable Inversion Based Fault-tolerant Trajectory Tracking Control of Civil Aircrafts Autolanding","authors":"Xudong Wang, Shiqian Liu, Huihui Cheng, Y. Sang, Xinjian Ma","doi":"10.6125/JOAAA.202009_52(3).02","DOIUrl":"https://doi.org/10.6125/JOAAA.202009_52(3).02","url":null,"abstract":"This paper deals with aircraft autoland control in the presence of wind disturbances and actuator faults. To solve this problem, a fault-tolerant trajectory tracking controller is presented to autoland a commercial aircraft. Firstly, the dynamics models of the aircraft with faults and winds are built. Secondly, the stable inversion based fault-tolerant autolanding control architecture is proposed. The stable inversion control is used to improve output tracking precision. The H_∞ control is applied for robust stability against uncertainties caused by wind disturbances and the faults. Compare with common fault-tolerant autolanding control, the stable inversion based fault-tolerant autolanding control has more robust capability including stabilizing the non-minimum phase system. Finally, two scenario simulations are carried out for automatic landing control of a large civil aircraft under winds and elevator failures. The results indicate that the proposed stable inversion based fault-tolerant autolanding controller has better tracking performances than those of the stable inversion control and fault-tolerant autolanding control, even in control surface faults and large winds.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"64 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131022842","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

Precise UAV Flight Management Based on Sensor Fusion with Integrity Monitoring 基于传感器融合和完整性监测的无人机精确飞行管理

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2020-09-01 DOI: 10.6125/JOAAA.202009_52(3).07

Rui Sun, Wenyu Zhang

{"title":"Precise UAV Flight Management Based on Sensor Fusion with Integrity Monitoring","authors":"Rui Sun, Wenyu Zhang","doi":"10.6125/JOAAA.202009_52(3).07","DOIUrl":"https://doi.org/10.6125/JOAAA.202009_52(3).07","url":null,"abstract":"The use of commercial Unmanned Aerial Vehicles (UAVs) has boomed in recent years. This increasing use has brought with significant challenges in respect to UAV flight management, however. As one of the liability-critical applications, UAV flight management requires precise knowledge of the real-time vehicle state in flight, as well as timely alerts to relevant users or entities before a risky event happens, such as intrusion into a no-fly zone. This paper, therefore, presents the user level, accuracy and integrity requirements for unmanned aerial vehicle flight management. We go on then to design a sensor fusion based positioning system to meet the aforementioned requirements. This uses a Kalman filter to integrate Global Positioning System (GPS) data with Inertial Navigation System (INS) data, based on the pseudorange measurements. In addition, an integrity monitoring algorithm is proposed based on a dual-mode fault detector and w test statistics, and real-time dynamic horizontal protection level computation. Onboard experimental results show that the proposed algorithm is capable of delivering the accuracy and integrity requirements for precise UAV flight management.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114363296","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

Artificial Neural Network Experimental Data Prediction of a Long-wave Excited Plane Jet Part I: Near Field Comparison 长波激发平面射流的人工神经网络实验数据预测第一部分:近场比较

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2020-06-01 DOI: 10.6125/JOAAA.202006_52(2).02

Yung-Lan Yeh, Yu-cheng Wang

引用次数: 0

Composite wing flutter analysis with variations of ribs location 考虑肋位置变化的复合材料机翼颤振分析

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2020-03-01 DOI: 10.6125/JOAAA.202003_52(1).05

Nurul Zubaidah Zaki, A. Abdul-Latif, S. Mansor

引用次数: 0

Dynamics Modeling and Pitching Parameters Identification of a Novel Hybrid UAV 一种新型混合动力无人机动力学建模与俯仰参数辨识

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2020-03-01 DOI: 10.6125/JOAAA.202003_52(1).03

Tung Lam Ngo, D. Hoang, T. Le

{"title":"Dynamics Modeling and Pitching Parameters Identification of a Novel Hybrid UAV","authors":"Tung Lam Ngo, D. Hoang, T. Le","doi":"10.6125/JOAAA.202003_52(1).03","DOIUrl":"https://doi.org/10.6125/JOAAA.202003_52(1).03","url":null,"abstract":"Unmanned Aerial Vehicle (UAV) is an appealing topic for aeronautical researchers due to its tremendous application in the world. To make controller design possible for a novel UAV design, dynamics modeling-a process of deriving a set of differential equations governing the motion of the aircraft-is essential. In this paper, we present a conceptual approach to obtain the parameterized dynamics equation based on application of Newton's second law and approximations of aerodynamics effects on the UAV. From there, two identification methods are introduced, one bases on maximum likelihood while the other employs linear regression to estimate the aircraft's dynamic parameters such as aerodynamic and control and stability derivatives through an example involving our new hybrid UAV developed from fixed wing aircraft and a tricopter. Wind tunnel tests for a one-third scaled model are carried out to receive outputs of the model, such as Euler angles and rotation rates, from prescribed input signals, which are rotors' speeds, then pitching parameters are identified. Estimated model would then be validated to another set of experiment to show the fitness, hence remarks regarding the accuracy of the dynamics model and the parameters themselves can be made. The articles show that for the derived mathematical model, the estimation results were well fitted, and cross-validation also indicates that the model was fine enough. The methods have strong implications about its generality that is applicable to other novel vehicle designs.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"12 2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116929861","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

Magnetoreception-based Navigation Mechanism of Black-faced Spoonbill 黑脸琵鹭基于磁感受的导航机制

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2019-12-01 DOI: 10.6125/JOAAA.201912_51(4).08

C. Yang, Tsung Han Lu, W. Chen

引用次数: 0

Experiments on Air Extraction Performance of Rooftop Natural Ventilators 屋顶自然通风机排风性能试验研究

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2019-12-01 DOI: 10.6125/JOAAA.201912_51(4).07

T. Chen, W. Mao, Y. Kuo

引用次数: 0

Simulation of the Resin Infiltration in Fiber Bundles Using the Lattice Boltzmann Method 用晶格玻尔兹曼方法模拟树脂在纤维束中的渗透

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2019-09-01 DOI: 10.6125/JOAAA.201909_51(3).08

Wei Yang, S. Chang, W. Young

引用次数: 0

An Efficient Procedure for Designing Various Series of Centrifugal Compressor Impellers 各种系列离心压缩机叶轮的高效设计方法

Journal of aeronautics, astronautics and aviation, Series A Pub Date : 2019-09-01 DOI: 10.6125/JOAAA.201909_51(3).02

C. Kong, Yueh-Heng Li, Wenhei Chen

引用次数: 0