International Journal of Aerospace Engineering最新文献_第8页

An Efficient Aircraft Conflict Detection and Resolution Method Based on an Improved Reinforcement Learning Framework 一种基于改进强化学习框架的飞机冲突检测与解决方法

4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-09-16 DOI: 10.1155/2023/6643903

Qiucheng Xu, Zhangqi Chen, Fangfang Li, Zhiyuan Shen, Wenbin Wei

{"title":"An Efficient Aircraft Conflict Detection and Resolution Method Based on an Improved Reinforcement Learning Framework","authors":"Qiucheng Xu, Zhangqi Chen, Fangfang Li, Zhiyuan Shen, Wenbin Wei","doi":"10.1155/2023/6643903","DOIUrl":"https://doi.org/10.1155/2023/6643903","url":null,"abstract":"With the steady increase of air traffic column, an auxiliary decision tool is required to compensate the operation redundancy deficiency of more sectors of air traffic control. To solve the problem of nonconflict high-density departure and arrival traffic flow, this method is expected to rapidly establish and maintain safe separation with more flexible changing strategies for aircraft heading and speed. This paper proposes an improved reinforcement learning framework to achieve conflict detection and resolution. The proposed framework includes the first development of an air traffic flow model based on a multiagent Markov decision process. The goal reward function was then maximized by improved Monte-Carlo tree search combined with an upper confidence bound tree. Three simulation scenarios were designed for illustrating the improvements of the proposed algorithm, with the results indicating that the algorithm could establish and maintain safe separation between 20 agents in the simplified hexagon-shaped airspace of Huadong, China. Furthermore, the proposed method was demonstrated to reduce the number of conflicts between aircraft agents by up to 26.32% compared to previous research.","PeriodicalId":13748,"journal":{"name":"International Journal of Aerospace Engineering","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135305822","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

Intercept Guidance of Maneuvering Targets with Deep Reinforcement Learning 基于深度强化学习的机动目标拦截制导

4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-09-13 DOI: 10.1155/2023/7924190

Zhe Hu, Liang Xiao, Jun Guan, Wenjun Yi, Hongqiao Yin

{"title":"Intercept Guidance of Maneuvering Targets with Deep Reinforcement Learning","authors":"Zhe Hu, Liang Xiao, Jun Guan, Wenjun Yi, Hongqiao Yin","doi":"10.1155/2023/7924190","DOIUrl":"https://doi.org/10.1155/2023/7924190","url":null,"abstract":"In this paper, a novel guidance law based on a reinforcement learning (RL) algorithm is presented to deal with the maneuvering target interception problem using a deep deterministic policy gradient descent neural network. We take the missile’s line-of-sight (LOS) rate as the observation of the RL algorithm and propose a novel reward function, which is constructed with the miss distance and LOS rate to train the neural network off-line. In the guidance process, the trained neural network has the capacity of mapping the missile’s LOS rate to the normal acceleration of the missile directly, so as to generate guidance commands in real time. Under the actor-critic (AC) framework, we adopt the twin-delayed deep deterministic policy gradient (TD3) algorithm by taking the minimum value between a pair of critics to reduce overestimation. Simulation results show that the proposed TD3-based RL guidance law outperforms the current state of the RL guidance law, has better performance to cope with continuous action and state space, and also has a faster convergence speed and higher reward. Furthermore, the proposed RL guidance law has better accuracy and robustness when intercepting a maneuvering target, and the LOS rate is converged.","PeriodicalId":13748,"journal":{"name":"International Journal of Aerospace Engineering","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135691530","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

Integrated Dynamics of Space Rigid-Flex Combination System with Time-Varying Configuration 时变构型空间刚柔组合系统的综合动力学

4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-09-13 DOI: 10.1155/2023/9980780

Yaen Xie, Xianliang Zhang, Xiangshuai Song, Xiaobin Lian, Jian Zhang

引用次数: 0

Automatic Landing System Design for Unmanned Fixed-Wing Vehicles via Multivariable Active Disturbance Rejection Control 基于多变量自抗扰控制的无人固定翼飞行器自动着陆系统设计

4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-09-09 DOI: 10.1155/2023/9395447

Zonghua Sun, Liaoni Wu, Yancheng You

{"title":"Automatic Landing System Design for Unmanned Fixed-Wing Vehicles via Multivariable Active Disturbance Rejection Control","authors":"Zonghua Sun, Liaoni Wu, Yancheng You","doi":"10.1155/2023/9395447","DOIUrl":"https://doi.org/10.1155/2023/9395447","url":null,"abstract":"Landing control of unmanned aerial vehicles (UAVs) is challenging because of the strong nonlinear dynamics, multivariable, model uncertainties, wind variations, and sensor noise. Motivated by this fact, this paper investigates an automatic landing system (ALS) that includes trajectory generation and guidance law for the first flight test of a turbine-based combined cycle technology demonstrator. Specifically, the control scheme increases the original model’s order to generate a reasonable monotone-decreasing throttle reference flare trajectory by the pseudospectral method. Subsequently, the guidance law based on innovative multivariable active disturbance rejection control is designed to robustly track the reference altitude and velocity simultaneously with high accuracy. The multivariable extended state observer (ESO) incorporated decoupling algorithm enhances the estimation capability and accuracy of potential problem in cross-coupling dynamics compared to the traditional ESO. It is proven that the closed-loop error dynamic has bounded-input bounded-output stability and an explicit upper bound is given. Numerical simulation verifies that the presented approach has better robustness and higher tracking accuracy for external disturbances and parametric uncertainties than the existing benchmark autolanding controller. Finally, flight tests show that the proposed ALS can land the vehicle effectively and safely under severe wind conditions.","PeriodicalId":13748,"journal":{"name":"International Journal of Aerospace Engineering","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136108293","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

Damage Identification of Rotating Blades Based on Fuzzy C-Means and Frequency Response Function Curvature Methods 基于模糊c均值和频响函数曲率法的旋转叶片损伤识别

4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-09-09 DOI: 10.1155/2023/6011397

Ruize Cui, Zefeng Wang, Zhiguang Song

{"title":"Damage Identification of Rotating Blades Based on Fuzzy C-Means and Frequency Response Function Curvature Methods","authors":"Ruize Cui, Zefeng Wang, Zhiguang Song","doi":"10.1155/2023/6011397","DOIUrl":"https://doi.org/10.1155/2023/6011397","url":null,"abstract":"Rotor blades are one of the key components of helicopter. If the blades are damaged, the safety and reliability of the helicopter will be seriously affected. Therefore, it is necessary to investigate the damage identification of the rotating blades. In this paper, a rotating cantilever beam is used to model the rotor blade. Based on the assumed mode method and Hamilton’s principle, the equation of motion is formulated, and the correctness of the model is verified by numerical and experimental studies. Altogether, two methods are used to identify the damages on the blade. The first one is the cluster analysis method based on the fuzzy C-mean theory. In order to reduce the dimension of the signal features, the singular value decomposition is introduced. The second method is the curvature of frequency response function method that can be used to determine the exact position of damages. Simulation results show that one can use fuzzy C-mean method to determine whether there is damage on the blade firstly and then determine the exact position of the damage through the curvature of frequency response function method.","PeriodicalId":13748,"journal":{"name":"International Journal of Aerospace Engineering","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136108706","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

Model-Free Robust Backstepping Adaptive Cruise Control 无模型鲁棒反演自适应巡航控制

IF 1.4 4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-09-08 DOI: 10.1155/2023/8839650

Yanan Zhang, Jiacheng Song

{"title":"Model-Free Robust Backstepping Adaptive Cruise Control","authors":"Yanan Zhang, Jiacheng Song","doi":"10.1155/2023/8839650","DOIUrl":"https://doi.org/10.1155/2023/8839650","url":null,"abstract":"This paper studies the model-free robust adaptive cruise control problem of a vehicle with unknown nonlinear dynamics and disturbances. First, under backstepping control framework, the position tracking errors with different spacing strategies are used to design a virtual control law, which provides a velocity reference. Then, a novel data-driven sliding surface whose parameters are updated by designing estimation algorithm is developed to handle the unknown uncertainties and disturbances. Finally, the model-free robust backstepping adaptive cruise control (MFRB-ACC) method including PI control, model-free control, and robust control is designed. The novelty of the proposed control technique lies in its strong robustness, which is not based on the precise vehicle model. The designed data-driven sliding surface releases the necessity for the accurate mathematical model of the vehicle and guarantees the inherent robustness of the controller, in particular to uncertainties, modelling error, or external disturbance. Moreover, the designed controller contains three terms such that it has an effective decoupling ability and strong robustness. The effectiveness and superiority of the designed MFRB-ACC method are validated on MATLAB, and the simulation results show that compared to the PID algorithm, the designed MFRB-ACC algorithm can track its preceding vehicle with lower tracking error under different spacing strategies, different operating conditions, and low sampling frequencies. Especially at a sampling frequency of 0.1 s, the error under the PID-ACC increases from 0.2 m at a sampling frequency of 0.01 s to 2 m, and the error under MFRB-ACC has little change compared to the error at a sampling frequency of 0.01 s.","PeriodicalId":13748,"journal":{"name":"International Journal of Aerospace Engineering","volume":" ","pages":""},"PeriodicalIF":1.4,"publicationDate":"2023-09-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43160077","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

Lift Augmentation on a Tiltrotor Wing Using the Combination of Vortex Generators and Gurney’s Flap 利用涡流发生器和格尼襟翼组合增强倾转旋翼的升力

IF 1.4 4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-09-07 DOI: 10.1155/2023/6646817

Hao Chen, Siliang Du, Zhong Chen

引用次数: 0

Multiobjective Mission Planning for Multiple Geosynchronous Spacecraft Refueling 多地球同步航天器换料的多目标任务规划

IF 1.4 4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-09-06 DOI: 10.1155/2023/6623461

Linjie Kong, Yang Zhou

{"title":"Multiobjective Mission Planning for Multiple Geosynchronous Spacecraft Refueling","authors":"Linjie Kong, Yang Zhou","doi":"10.1155/2023/6623461","DOIUrl":"https://doi.org/10.1155/2023/6623461","url":null,"abstract":"This paper studies the multiple geosynchronous spacecraft refueling problem (MGSRP) with multiple servicing spacecraft (Ssc) and fuel depots (FDs). In the mission scenario, multiple Ssc and FDs are parked in the geosynchronous Earth orbit (GEO) initially. Ssc start from FDs and maneuver to visit and refuel multiple GEO targets with known demands. These capacitated Ssc are expected to rendezvous with fuel-deficient GEO targets and FDs for the purpose of delivering the fuel stored in FDs to GEO targets. The objective is to find a set of Pareto-optimal solutions with minimum fuel cost and mission duration. The MGSRP is a much more complex variant of multidepot vehicle routing problems mixing discrete and continuous variables. A two-nested optimization model is built. We propose a new multiobjective hybrid particle swarm optimization to solve the outer-loop problem, and the design variables are the refueling sequence, task assignment, time distribution, and locations of FDs. In the inner-loop problem, branch and bound method is used to find the optimal decision variable for a given outer-loop solution. Finally, numerical simulations are presented to illustrate the effectiveness and validity of the proposed approach.","PeriodicalId":13748,"journal":{"name":"International Journal of Aerospace Engineering","volume":" ","pages":""},"PeriodicalIF":1.4,"publicationDate":"2023-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43385762","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

A Shear-Sliding Rigid-Flexible Coupled Skin Variable-Sweep Wing Design and Heat-Fluid-Structure Multifield Coupling Analysis 剪切-滑动刚柔耦合蒙皮变后掠翼设计及热流固多场耦合分析

IF 1.4 4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-08-31 DOI: 10.1155/2023/7078091

Hong Xiao, Hongwei Guo, Mingqi Li, Yu Zhang, Rongqiang Liu, Jianguo Tao

{"title":"A Shear-Sliding Rigid-Flexible Coupled Skin Variable-Sweep Wing Design and Heat-Fluid-Structure Multifield Coupling Analysis","authors":"Hong Xiao, Hongwei Guo, Mingqi Li, Yu Zhang, Rongqiang Liu, Jianguo Tao","doi":"10.1155/2023/7078091","DOIUrl":"https://doi.org/10.1155/2023/7078091","url":null,"abstract":"The variable-sweep wing is very attractive for cross-speed domain aircraft. The shear-sliding rigid-flexible coupled skin variable-sweep wing and its associated mechanism are designed and optimized. The variable-sweep wing has smooth continuous deformation and rigid-flexible coupling features. The calculation model of the sliding skin patch segmentation strategy is established, and the aerodynamic characteristics of the two-dimensional airfoil before and after the deformation of the wing skin are analyzed. According to the deformation characteristics of sliding skin, the configuration of the associated mechanism is determined, and the kinematic characteristics of the reference points of each skin are calculated. The kinematic simulation verifies the force of the mechanism model at the joint of skin surfaces during the deformation process. Considering the aerodynamic heat at supersonic speed, the heat transfer, heat distribution, and structural thermal modes between the flow field and the skin are calculated based on the finite element method. The dynamic characteristics of the swept wing with different flight speeds and different morphologies are analyzed. The natural frequencies are found to be reduced by about 30% to 50% compared to cold models at supersonic speeds. Based on the results of the thermal fluid-solid coupling calculation, the skeleton structure of the swept wing is optimized, and the skeleton structure with 25% mass reduction and better performance is obtained.","PeriodicalId":13748,"journal":{"name":"International Journal of Aerospace Engineering","volume":" ","pages":""},"PeriodicalIF":1.4,"publicationDate":"2023-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42932514","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

Velocity-Adaptive Prescribed Performance Control for Carrier-Based Aircraft Based on Guardian Maps 基于Guardian映射的舰载机速度自适应预定性能控制

IF 1.4 4区工程技术

International Journal of Aerospace Engineering Pub Date : 2023-08-31 DOI: 10.1155/2023/5541378

Chenliang Li, Jizhou Lai, Boyi Chen, Yanbin Liu

引用次数: 0