The Aeronautical Journal最新文献_第5页

Autonomous predictive maintenance of quadrotor UAV with multi-actuator degradation 多执行器退化的四旋翼无人机自主预测维护

The Aeronautical Journal Pub Date : 2024-02-08 DOI: 10.1017/aer.2024.8

F.-y. Shen, W. Li, D.-n. Jiang, H.-j. Mao

{"title":"Autonomous predictive maintenance of quadrotor UAV with multi-actuator degradation","authors":"F.-y. Shen, W. Li, D.-n. Jiang, H.-j. Mao","doi":"10.1017/aer.2024.8","DOIUrl":"https://doi.org/10.1017/aer.2024.8","url":null,"abstract":"\u0000 With the wide application of quadrotor unmanned aerial vehicles (UAVs), the requirements for their safety and reliability are becoming increasingly stringent. In this paper, based on the feedback of airframe performance health perception information and the predictive function control strategy, the autonomous maintenance of a quadrotor UAV with multi-actuator degradation is realised. Autonomous maintenance architecture is constructed by the predictive maintenance (PdM) idea and the Laguerre function model predictive pontrol (LF-MPC) strategy. Using the two-stage Kalman filter (TSKF) method, based on the established UAV degradation model, the aircraft state and actuator degradation state are predicted simultaneously. For the predictive perception of system health, on the one hand, the system health degree (HD) based on Mahalanobis distance is defined by the degree of airframe state deviation from the expected state, and then the failure threshold of the UAV is obtained. On the other hand, according to the degradation state of each actuator, a comprehensive degradation variable fused with different weight coefficients of multiple actuators degradation is used to obtain the probability density function (PDF) of remaining useful life (RUL) prediction. For the autonomous maintenance of system health, the LF-MPC weight matrixes are adjusted adaptively in real-time based on the HD evaluation, to achieve a compromise balance between UAV performance and control effect, and greatly extend the working time of UAV. Simulation results verified the effectiveness of the proposed method.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":" 28","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139791712","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

On the secondary stall of a wing in tandem configuration 关于串联配置中机翼的二次失速

The Aeronautical Journal Pub Date : 2024-02-08 DOI: 10.1017/aer.2024.7

S.H.R. Shah, A. Ahmed

引用次数: 0

Design and dynamic analysis of supporting mechanism for large scale space deployable membrane sunshield 大型空间可部署膜式遮阳板支撑机构的设计与动态分析

The Aeronautical Journal Pub Date : 2024-02-08 DOI: 10.1017/aer.2024.1

B.Y. Chang, X. Guan, D. Liang, S.J. Yan, G.G. Jin

{"title":"Design and dynamic analysis of supporting mechanism for large scale space deployable membrane sunshield","authors":"B.Y. Chang, X. Guan, D. Liang, S.J. Yan, G.G. Jin","doi":"10.1017/aer.2024.1","DOIUrl":"https://doi.org/10.1017/aer.2024.1","url":null,"abstract":"\u0000 Stray light from the sun is one of the most significant factors affecting image quality for the optical system of a spacecraft. This paper proposes a method to design a deployable supporting mechanism for the sunshield based on origami. Firstly, a new type of space mechanism with single-closed loop was proposed according to thick-panel origami, and its mobility was analysed by using the screw theory. In order to design a deployable structure with high controllability, the tetrahedral constraint was introduced to reduce the degree of freedom (DOF), and a corresponding deployable unit named tetrahedral deployable unit (TDU) was obtained. Secondly, the process to constructing a large space deployable mechanism with infinite number of units was explained based on the characteristics of motion and planar mosaic array, and kinematics analysis and folding ratio of supporting mechanism were conducted. A physical prototype was constructed to demonstrate the mobility and deployment of the supporting mechanism. Finally, based on the Lagrange method, a dynamic model of supporting mechanism was established, and the influence of the torsion spring parameters on the deployment process was analysed.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"89 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139854193","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

Use of VEGA data to analyse balloon options for possible subsequent long endurance Venus cloud layer missions 利用 VEGA 数据分析气球选项，以执行可能的后续长航时金星云层飞行任务

The Aeronautical Journal Pub Date : 2024-02-08 DOI: 10.1017/aer.2023.105

G. dorrington

引用次数: 0

Autonomous predictive maintenance of quadrotor UAV with multi-actuator degradation 多执行器退化的四旋翼无人机自主预测维护

The Aeronautical Journal Pub Date : 2024-02-08 DOI: 10.1017/aer.2024.8

F.-y. Shen, W. Li, D.-n. Jiang, H.-j. Mao

{"title":"Autonomous predictive maintenance of quadrotor UAV with multi-actuator degradation","authors":"F.-y. Shen, W. Li, D.-n. Jiang, H.-j. Mao","doi":"10.1017/aer.2024.8","DOIUrl":"https://doi.org/10.1017/aer.2024.8","url":null,"abstract":"\u0000 With the wide application of quadrotor unmanned aerial vehicles (UAVs), the requirements for their safety and reliability are becoming increasingly stringent. In this paper, based on the feedback of airframe performance health perception information and the predictive function control strategy, the autonomous maintenance of a quadrotor UAV with multi-actuator degradation is realised. Autonomous maintenance architecture is constructed by the predictive maintenance (PdM) idea and the Laguerre function model predictive pontrol (LF-MPC) strategy. Using the two-stage Kalman filter (TSKF) method, based on the established UAV degradation model, the aircraft state and actuator degradation state are predicted simultaneously. For the predictive perception of system health, on the one hand, the system health degree (HD) based on Mahalanobis distance is defined by the degree of airframe state deviation from the expected state, and then the failure threshold of the UAV is obtained. On the other hand, according to the degradation state of each actuator, a comprehensive degradation variable fused with different weight coefficients of multiple actuators degradation is used to obtain the probability density function (PDF) of remaining useful life (RUL) prediction. For the autonomous maintenance of system health, the LF-MPC weight matrixes are adjusted adaptively in real-time based on the HD evaluation, to achieve a compromise balance between UAV performance and control effect, and greatly extend the working time of UAV. Simulation results verified the effectiveness of the proposed method.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"8 9","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139851400","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

Use of VEGA data to analyse balloon options for possible subsequent long endurance Venus cloud layer missions 利用 VEGA 数据分析气球选项，以执行可能的后续长航时金星云层飞行任务

The Aeronautical Journal Pub Date : 2024-02-08 DOI: 10.1017/aer.2023.105

G. dorrington

引用次数: 0

Improving pilots’ tactical decisions in air combat training using the critical decision method 在空战训练中利用关键决策法改进飞行员的战术决策

The Aeronautical Journal Pub Date : 2024-02-01 DOI: 10.1017/aer.2024.3

H. Mansikka, K. Virtanen, T. Lipponen, D. Harris

{"title":"Improving pilots’ tactical decisions in air combat training using the critical decision method","authors":"H. Mansikka, K. Virtanen, T. Lipponen, D. Harris","doi":"10.1017/aer.2024.3","DOIUrl":"https://doi.org/10.1017/aer.2024.3","url":null,"abstract":"\u0000 In fighter pilot training, much of upgrade pilots’ (UPs’) learning takes place during mission debriefs. A debrief provides instructor pilots (IPs) the opportunity to correct situation awareness (SA) upon which the UPs base their tactical decisions. Unless the debrief is conducted with proper depth and breadth, the IPs’ feedback on UPs’ SA and tactical decision-making may be incomplete or false, resulting in poor, or even negative learning. In this study, a new debrief protocol based on the Critical Decision Method (CDM) is introduced. The protocol specifically addresses the SA of UPs. An evaluation was conducted to examine if a short CDM training programme to IPs would enhance their ability to provide performance feedback to UPs regarding their SA and tactical decision-making. The IPs were qualified flying instructors and the UPs were air force cadets completing their air combat training with BAe Hawk jet trainer aircraft. The impact of the training intervention was evaluated using Kirkpatrick’s four-level model. The first three levels of evaluation (Reactions, Learning and Behaviour) focused on the IPs, whereas the fourth level (Results) focused on the UPs. The training intervention had a positive impact on the Reactions, Learning and debrief Behaviour of the IPs. In air combat training missions, the UPs whose debriefs were based on the CDM protocol, had superior SA and overall performance compared to a control group.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"57 44","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139685931","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

Aerodynamic design of a high-efficiency two-stage axial turbine, using streamline curvature method and performance optimisation by clocking of stator blades 利用流线曲率法和定子叶片时钟优化性能的高效两级轴流式涡轮机空气动力学设计

The Aeronautical Journal Pub Date : 2024-02-01 DOI: 10.1017/aer.2024.5

R. Taghavi Zenouz, S. Abiri

{"title":"Aerodynamic design of a high-efficiency two-stage axial turbine, using streamline curvature method and performance optimisation by clocking of stator blades","authors":"R. Taghavi Zenouz, S. Abiri","doi":"10.1017/aer.2024.5","DOIUrl":"https://doi.org/10.1017/aer.2024.5","url":null,"abstract":"\u0000 Aerodynamic design of a high-efficiency two-stage axial turbine is carried out using a hybrid method through implantation of a two-step design procedure. In the first step, the well-known streamline curvature (SLC) and free vortex (FV) methods are properly combined to establish three-dimensional geometries of the blades at each row and to obtain the flow field properties. The second step is provided to obtain the highest aerodynamic efficiency by optimum clocking of the second stator blades relative to the first ones through executing steady and unsteady computational fluid dynamics (CFD) of three-dimensional viscous flow. Slight discrepancies were observed between gas dynamics results of the SLC and those of CFD. Total pressure and temperature at the turbine outlet, obtained from SLC method, differed from those obtained by 3D-CFD technique by 13.06% and 1.88% respectively. Aerodynamic efficiency of the turbine is obtained about 91.83%, based on 3D-CFD. Time-averaged results showed that under the optimum clocking of the second row stator blades, inlet total pressure and output power of the second rotor increase by 0.23%, and 0.93%, respectively, in comparison to the worst clocking case. These augmentations resulted in increased total to total efficiency of the second stage by 0.444%. Additionally, the total output power of the two stages increased by 0.71% through the optimum clocking. Modeling the unsteady wake flow trajectory within the blades passages confirmed that all of these beneficial effects happen if the upstream wake impinges on the leading edge region of the second stator blades.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"29 9","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139885838","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

Aerodynamic design of a high-efficiency two-stage axial turbine, using streamline curvature method and performance optimisation by clocking of stator blades 利用流线曲率法和定子叶片时钟优化性能的高效两级轴流式涡轮机空气动力学设计

The Aeronautical Journal Pub Date : 2024-02-01 DOI: 10.1017/aer.2024.5

R. Taghavi Zenouz, S. Abiri

{"title":"Aerodynamic design of a high-efficiency two-stage axial turbine, using streamline curvature method and performance optimisation by clocking of stator blades","authors":"R. Taghavi Zenouz, S. Abiri","doi":"10.1017/aer.2024.5","DOIUrl":"https://doi.org/10.1017/aer.2024.5","url":null,"abstract":"\u0000 Aerodynamic design of a high-efficiency two-stage axial turbine is carried out using a hybrid method through implantation of a two-step design procedure. In the first step, the well-known streamline curvature (SLC) and free vortex (FV) methods are properly combined to establish three-dimensional geometries of the blades at each row and to obtain the flow field properties. The second step is provided to obtain the highest aerodynamic efficiency by optimum clocking of the second stator blades relative to the first ones through executing steady and unsteady computational fluid dynamics (CFD) of three-dimensional viscous flow. Slight discrepancies were observed between gas dynamics results of the SLC and those of CFD. Total pressure and temperature at the turbine outlet, obtained from SLC method, differed from those obtained by 3D-CFD technique by 13.06% and 1.88% respectively. Aerodynamic efficiency of the turbine is obtained about 91.83%, based on 3D-CFD. Time-averaged results showed that under the optimum clocking of the second row stator blades, inlet total pressure and output power of the second rotor increase by 0.23%, and 0.93%, respectively, in comparison to the worst clocking case. These augmentations resulted in increased total to total efficiency of the second stage by 0.444%. Additionally, the total output power of the two stages increased by 0.71% through the optimum clocking. Modeling the unsteady wake flow trajectory within the blades passages confirmed that all of these beneficial effects happen if the upstream wake impinges on the leading edge region of the second stator blades.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"35 5","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139825900","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

Finite-time attitude tracking control of stratospheric airship in the presence of multiple disturbances 存在多重干扰时平流层飞艇的有限时间姿态跟踪控制

The Aeronautical Journal Pub Date : 2024-02-01 DOI: 10.1017/aer.2024.4

Z.B. Li, D. He, J.Q. Zhang, X.R. Meng

{"title":"Finite-time attitude tracking control of stratospheric airship in the presence of multiple disturbances","authors":"Z.B. Li, D. He, J.Q. Zhang, X.R. Meng","doi":"10.1017/aer.2024.4","DOIUrl":"https://doi.org/10.1017/aer.2024.4","url":null,"abstract":"\u0000 This paper proposes a composite non-singular fast terminal sliding mode attitude control scheme based on a reduced-order extended state observer for the stratospheric airship’s attitude system affected by multiple disturbances. First, the feedback linearisation method is applied to address the nonlinearity of the attitude motion model and achieve decoupling of the model in three channels. Second, the overall disturbances, encompassing airship parameter perturbations and external disturbances, are treated as an aggregate. A reduced-order extended state observer is designed for each channel to formulate a composite non-singular fast terminal sliding mode surface. In the control design phase, the hyperbolic sine function is adopted as replacement for the sign function to ensure the continuity of the control signal. The estimated disturbances are incorporated in the control law design to directly offset the effects of multiple disturbances on the attitude motion of the airship. Third, based on Lyapunov theory, it has been proven that the control law can drive the attitude tracking error to converge to zero within a finite time. Simulation results demonstrate that the proposed control scheme exhibits favorable disturbance rejection capability, as well as higher tracking accuracy and faster response speed.","PeriodicalId":508971,"journal":{"name":"The Aeronautical Journal","volume":"19 5","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139889599","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