Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering最新文献_第6页

Novel integrated guidance and control design for a three-stage satellite carrier using model-free adaptive control 利用无模型自适应控制为三级卫星运载器设计新颖的综合制导和控制装置

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-03-27 DOI: 10.1177/09544100221107507

Mohammadreza Yaseri, Alireza Basohbat Novinzadeh

引用次数: 0

Finite-time state-constrained adaptive fault-tolerant control for heavy launch vehicles with input quantization 输入量化重型运载火箭的有限时间状态约束自适应容错控制

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-03-20 DOI: 10.1177/09544100241240161

Ruitao Zhang, Zheng Wang, Yangwang Fang, Hang Guo, Wenxing Fu, Jie Yan, Lulu Rong

{"title":"Finite-time state-constrained adaptive fault-tolerant control for heavy launch vehicles with input quantization","authors":"Ruitao Zhang, Zheng Wang, Yangwang Fang, Hang Guo, Wenxing Fu, Jie Yan, Lulu Rong","doi":"10.1177/09544100241240161","DOIUrl":"https://doi.org/10.1177/09544100241240161","url":null,"abstract":"This paper proposes the finite-time state-constrained adaptive fault-tolerant control method for a class of heavy launch vehicles subject to quantized input signals and actuator faults. Firstly, the attitude dynamic model of the heavy launch vehicles suffering from the actuator faults and disturbances is formulated. Secondly, to deal with the completely unknown nonlinear functions, radial basis function neural networks (RBFNNs) are introduced for approximation and compensation. Meanwhile, the barrier Lyapunov function (BLF) is introduced to ensure that all the states in the closed-loop system are bounded and the constraints of the system states are satisfied. As a result, the finite-time state-constrained adaptive fault-tolerant control structure is constructed for the heavy launch vehicles and the semi-globally practical finite-time stability (SGPFS) of the closed-loop control system is proved. Finally, numerical simulation results show the effectiveness and the satisfactory performance of the proposed control algorithm.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2024-03-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140203907","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

Numerical simulations of a hydrogen-air pre-detonator for detonation engines 引爆发动机氢气空气预引爆器的数值模拟

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-03-06 DOI: 10.1177/09544100241233324

Amrutha Preethi Pathangae, Ramanujachari Varadachari

{"title":"Numerical simulations of a hydrogen-air pre-detonator for detonation engines","authors":"Amrutha Preethi Pathangae, Ramanujachari Varadachari","doi":"10.1177/09544100241233324","DOIUrl":"https://doi.org/10.1177/09544100241233324","url":null,"abstract":"In recent years, heat release associated with the detonation phenomenon is considered a very efficient process. Pressure gain combustors are being developed with detonation waves as the driving force. In this scenario, study of detonation waves has become very important. Deflagration-to-Detonation transition (DDT) is one of the ways used to initiate detonation in the combustors. An attempt has been made in this paper to study the DDT in a tube with obstacles using OPENFOAM. A 2-dimensional rectangular section of a tube containing obstacles filled with stoichiometric hydrogen-air mixtures at different initial conditions have been studied. The effect of changes in the length of the tube, number of obstacles, blockage ratios and initial pressure of the reactants on the detonation wave properties have been studied using numerical simulation based on ddtfoam software. The motivation for this study is to design a pre-detonator for a rotating detonation engine (RDE). In order to make it compatible with the RDE and the test facility, it has been proposed to carry out simulations using shorter lengths of the DDT tube. The number of obstacles has been selected appropriately to obtain detonation at shorter lengths of the tube of the order of 1.5 m, 1.0 m & 0.5 m. As the objective has been to obtain design data for the prototype, the finer details of DDT are not being discussed in this paper.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2024-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140055202","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

Nonlinear vibrations analysis of two-directional functionally graded porous cylindrical shells resting on elastic substrates in a thermal environment based on Donnell nonlinear shell theory 基于唐奈非线性壳理论的热环境下弹性基底上双向功能分级多孔圆柱壳的非线性振动分析

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-03-05 DOI: 10.1177/09544100241234376

Ahmad Ali Rahmani, Farhad Hosseinnejad, Yasser Rostamiyan

{"title":"Nonlinear vibrations analysis of two-directional functionally graded porous cylindrical shells resting on elastic substrates in a thermal environment based on Donnell nonlinear shell theory","authors":"Ahmad Ali Rahmani, Farhad Hosseinnejad, Yasser Rostamiyan","doi":"10.1177/09544100241234376","DOIUrl":"https://doi.org/10.1177/09544100241234376","url":null,"abstract":"The primary objective of this study is to investigate the nonlinear free vibrational characteristics of temperature-dependent two-directional functionally graded porous (TDFGP) cylindrical shells resting on elastic substrates in a thermal environment. To accomplish this, the thermomechanical equations are derived based on the Donnell nonlinear shell theory framework in conjunction with the von Kármán assumption. Two-directional functionally graded porous cylindrical shell models have mechanical properties that can change smoothly and continuously across the length and thickness of the shell. Additionally, it is assumed that the internal porosities in the matrix materials can be dispersed into two independent patterns, either even or uneven porosity distribution. The nonlinearity in free vibration assessed via the nonlinear-to-linear frequency ratio concerning the central deflection amplitude can be gained employing the Galerkin discretization approach and modified Poincare–Lindstedt (P-L) method. The accuracy and effectiveness of the present analytical model are indicated through comparison with existing solutions. Finally, some comprehensive parametric investigations are carried out to gain insight into the impacts of several factors on the nonlinear free vibration characteristics of structures under different conditions. The results of this article demonstrate that parameters such as gradient indices, volume fraction, distribution pattern of porosity, geometric parameters, and ambient temperature rise significantly influence the structure’s nonlinear frequency and free vibration response.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2024-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140045894","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 entry guidance with no-fly zone constraint using reinforcement learning and predictor-corrector technique 利用强化学习和预测校正器技术进行具有禁飞区约束的综合入境引导

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-03-01 DOI: 10.1177/09544100241236995

Yuan Gao, Rui Zhou, Jinyong Chen

{"title":"Integrated entry guidance with no-fly zone constraint using reinforcement learning and predictor-corrector technique","authors":"Yuan Gao, Rui Zhou, Jinyong Chen","doi":"10.1177/09544100241236995","DOIUrl":"https://doi.org/10.1177/09544100241236995","url":null,"abstract":"This paper presents an integrated entry guidance law for hypersonic glide vehicles with no-fly zone constraint. Existing methods that employ predictor-corrector technique and lateral guidance logic for both guidance and avoidance, may have limitations in response time and maneuverability when facing sudden threats, because the guidance cycle is limited by computational efficiency and the bank angle magnitude cannot be adjusted according to the urgency of the avoidance. To overcome these challenges, the proposed method divides the entry process into safe flight stages and no-fly zone avoidance stages, and introduces reinforcement learning to develop an intelligent avoidance strategy for the latter. This division reduces the complexity of the learning problem by restricting the state space and increases the applicability in the presence of multiple no-fly zones. The trained avoidance strategy can directly output continuous bank angle command through a single forward calculation, considering both guidance and avoidance requirements. This enables the full utilization of the vehicle’s maneuverability and supports a high command update frequency to effectively handle threats. Additionally, a network trained via supervised learning is employed to generate reference commands, accelerating the training convergence of reinforcement learning. Simulation results demonstrate the effectiveness of the proposed guidance law, highlighting its high computational efficiency, command stability, and robustness. Importantly, the approach offers convenience in extending to multiple no-fly zones and accommodating vast initial state spaces.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2024-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140019940","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

Single-lever control method design based on power management system and deep reinforcement learning for turboprop engines 基于涡轮螺旋桨发动机动力管理系统和深度强化学习的单杆控制方法设计

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-02-29 DOI: 10.1177/09544100241235824

Run-Min Ji, Xiang-Hua Huang, Xing-Long Zhang, Ling-Wei Li

{"title":"Single-lever control method design based on power management system and deep reinforcement learning for turboprop engines","authors":"Run-Min Ji, Xiang-Hua Huang, Xing-Long Zhang, Ling-Wei Li","doi":"10.1177/09544100241235824","DOIUrl":"https://doi.org/10.1177/09544100241235824","url":null,"abstract":"This paper presents a single-lever control method based on Power Management System (PMS) and improved Twin Delayed Deep Deterministic Policy Gradient (TD3) algorithm for turboprop engines. In this approach, power level angle command, which is the single-lever command, is decoupled into controlled variable commands by PMS, and the controller based on improved TD3 algorithm can ensure that controlled variables track their commands rapidly and accurately. To achieve the optimal conversion relationship between different commands, an offline optimization process is used to design PMS. By optimization, specific fuel consumption and propeller efficiency are both improved after conversion. To deal with strong interactions between different control loops of a turboprop engine, TD3 algorithm which is a deep reinforcement learning algorithm is adopted. Two improvements which are the design method of observation state and prioritized experience replay are made to enhance the tracking accuracy. Simulation results show that improved TD3 algorithm can learn an optimal control policy to guarantee good control effect with fast response and small overshoot. The maximum settling time is less than 0.25s and the maximum overshoot is less than 0.1%. It also has a good robustness performance when the plant exists model uncertainties. The maximum fluctuations are less than 0.05%.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2024-02-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140008169","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

Modal and response characteristics of rotor with angle misalignment fault based on cross-coordinate system substructure modeling method 基于十字坐标系子结构建模方法的角度不对中故障转子的模态和响应特性

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-02-28 DOI: 10.1177/09544100241234371

Yu Liu, Diwen Zhao, Zhi Wang, Yanting Ai

{"title":"Modal and response characteristics of rotor with angle misalignment fault based on cross-coordinate system substructure modeling method","authors":"Yu Liu, Diwen Zhao, Zhi Wang, Yanting Ai","doi":"10.1177/09544100241234371","DOIUrl":"https://doi.org/10.1177/09544100241234371","url":null,"abstract":"Finite element models are widely used in dynamic analysis of misalignment rotor, but present finite element rotor models cannot simulate the axis characteristics of angle misalignment rotor, which consistent with the one with no misalignment. For achieving the precisely modeling of angle misalignment rotor, a novel modeling method called cross-coordinate substructure modeling method is introduced to establish the model of misalignment rotor, in which different parts of rotor rotate around different axis. Based on this modeling method, the 3D solid models of angle misalignment rotor are established with the help of ANSYS, and the modal characteristics and critical speeds of the misalignment rotor are achieved through modal analysis and harmonic response analysis. The numerical simulation based on Newmark method and experiment tests is carried out to obtain the response characteristics of the rotor model under the combined action of unbalanced force and misalignment load. The results show that the modal “rotation of rotor” appears, and the more amounts of response peaks can be aroused in harmonic response analysis when the rotor occurs angle misalignment. The typical fault characteristics of angle misalignment rotor in the spectrums and orbit diagrams are generally consistent both in the numerical simulation and experiment test. The research results can provide a theoretical basis for simulation and identification of the misalignment fault in rotating machinery system.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2024-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140008181","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

Research on optimization method for flyby observation mission adapted to satellite on-board computation 适应卫星星载计算的飞越观测任务优化方法研究

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-02-27 DOI: 10.1177/09544100241235801

Jiyuan Wang, Yan Xiao, Dong Ye, Zijun Wang, Zhaowei Sun

{"title":"Research on optimization method for flyby observation mission adapted to satellite on-board computation","authors":"Jiyuan Wang, Yan Xiao, Dong Ye, Zijun Wang, Zhaowei Sun","doi":"10.1177/09544100241235801","DOIUrl":"https://doi.org/10.1177/09544100241235801","url":null,"abstract":"In this paper, the optimization problem of orbital transfer strategy for orbital flyby observation missions is studied. A hybrid optimization method is proposed, which is improved to make it more suitable for satellite on-board computing. This new algorithm is designed to solve the initial value sensitivity problem of the sequential quadratic programming algorithm (SQP). It is consisted of the depth-first search algorithm (DFS) and the SQP algorithm and thus has the characteristics of fast convergence, high reliability, and good robustness. With this method, the DFS with a large step size is calculated first, and then the optimal value in the calculation result is used as the initial value of the SQP algorithm for further optimization. This method can obtain the approximate optimal solution available in engineering. The numerical simulation of an orbital transfer optimization problem is set to verify the effectiveness of the new hybrid algorithm. The simulation results compared with the genetic algorithm (GA) show that the proposed hybrid algorithm can effectively reduce the on-board resource occupation when getting similar results and thus can meet the needs of satellite on-board computing.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2024-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140008182","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

Collaborative strategy research of target tracking based on natural intelligence by UAV swarm 基于自然智能的无人机群目标跟踪协同策略研究

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-02-26 DOI: 10.1177/09544100241233313

Shi Yin, Xiaofang Wang, Lianyong Luo, Nan Pan, Da Zhao, Xiayang Zhang

引用次数: 0

The effect of a tandem vane crossover diffuser configuration on the performance of a MGT mixed flow compressor 串联叶片交叉扩散器配置对 MGT 混流压缩机性能的影响

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-02-23 DOI: 10.1177/09544100241235602

Hano van Eck, Sybrand Johannes van der Spuy

{"title":"The effect of a tandem vane crossover diffuser configuration on the performance of a MGT mixed flow compressor","authors":"Hano van Eck, Sybrand Johannes van der Spuy","doi":"10.1177/09544100241235602","DOIUrl":"https://doi.org/10.1177/09544100241235602","url":null,"abstract":"Due to the inherent geometric restrictions of a micro gas turbine (MGT) mixed flow compressor design, diffuser design has a major impact on compressor performance and operating range. Vaned diffusers are often preferred to vaneless diffusers in MGT compressor designs due to better efficiency and pressure recovery, albeit at the expense of operating range. A numeric investigation of the effect of a tandem vane crossover diffuser configuration on the performance and operating range of a MGT mixed flow compressor stage is presented. Three baseline test compressors, covering a wide range of design speeds, mass flow rates and meridional exit angles, are designed with a single vane crossover diffuser. For each of the three baseline compressors, the crossover diffuser design is modified to feature various tandem vane configurations. The tangential shift of the second vane row relative to the first row is evaluated. Additionally, relative first and second vane row lengths are evaluated. The performance (efficiency and pressure ratio) and operating range of the modified diffuser configurations are compared to the baseline configurations. It is shown that a 75% second vane row tangential shift configuration displays the best overall performance, regardless of the relative vane length. It is further shown that an appropriate vane length depends on the design requirement.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2024-02-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139949722","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