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Coupling optimization design of configuration and swept-bowed effects in highly loaded subsonic compressor tandem cascades with tip clearance Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-04-20 Xiaochen Mao, Yingchen Jiao, Hao Cheng, Botao Zhang, Bo Liu
The coupling optimization design for swept-bowed effects and configuration of tandem cascade is conducted in a highly loaded subsonic compressor tandem cascade, in which the novelty lies in considering the spanwise distribution of configuration parameters and exploring the coupling relationship between them and swept-bowed design. Research results show that, compared with the original one, the loss
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Inverse dynamics based aerodynamic, gyroscopic, and rotor effects’ compensation in constrained trajectory synthesis for multi-copters Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-04-03 Tsung-Liang Liu, Kamesh Subbarao
The performance of an uncrewed aerial system (UAS) operating nominally in an indoor/outdoor environment depends upon the available power, and how well the system reacts to disturbances and nonlinear dynamic effects. This paper focuses on development of approaches to compensate for nonlinear dynamic effects due to aerodynamics, gyroscopic coupling, and rotor induced rolling effects in deriving aggressive
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Moment-independent sensitivity analysis of a fold mechanism based on an active learning kriging method Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-03-28 Yebao Hu, Yongshou Liu, Qing Guo, Jiayin Dai, Jing Wang
The present article shows the reliability and sensitivity of a missile folding rudder calculated by MSC.ADAMS and MATLAB. For folding rudder, mass of the counterweight, maximum of the motive force, preloading force, and stiffness coefficients of the spring 1 and spring 2 are considered when calculating the reliability. Two methods, active learning kriging (ALK) and Monte Carlo simulation (MCS), are
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Novel integrated guidance and control design for a three-stage satellite carrier using model-free adaptive control Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-03-27 Mohammadreza Yaseri, Alireza Basohbat Novinzadeh
A model-free adaptive control is proposed for suboptimal guidance correction and control of a prototypical three-stage satellite carrier. For this sake, we consider a nominal guidance for the model of the system and design the adaptive control for a single-input multi-output system exposed to wind disturbance and measurement noise in the rates of inputs and outputs. Then, subsequent to the guidance
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Finite-time state-constrained adaptive fault-tolerant control for heavy launch vehicles with input quantization Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-03-20 Ruitao Zhang, Zheng Wang, Yangwang Fang, Hang Guo, Wenxing Fu, Jie Yan, Lulu Rong
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
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Numerical simulations of a hydrogen-air pre-detonator for detonation engines Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-03-06 Amrutha Preethi Pathangae, Ramanujachari Varadachari
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
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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 Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-03-05 Ahmad Ali Rahmani, Farhad Hosseinnejad, Yasser Rostamiyan
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
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Integrated entry guidance with no-fly zone constraint using reinforcement learning and predictor-corrector technique Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-03-01 Yuan Gao, Rui Zhou, Jinyong Chen
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
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Single-lever control method design based on power management system and deep reinforcement learning for turboprop engines Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-29 Run-Min Ji, Xiang-Hua Huang, Xing-Long Zhang, Ling-Wei Li
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
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Modal and response characteristics of rotor with angle misalignment fault based on cross-coordinate system substructure modeling method Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-28 Yu Liu, Diwen Zhao, Zhi Wang, Yanting Ai
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
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Research on optimization method for flyby observation mission adapted to satellite on-board computation Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-27 Jiyuan Wang, Yan Xiao, Dong Ye, Zijun Wang, Zhaowei Sun
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
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Collaborative strategy research of target tracking based on natural intelligence by UAV swarm Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-26 Shi Yin, Xiaofang Wang, Lianyong Luo, Nan Pan, Da Zhao, Xiayang Zhang
Regarding the regional area target collaborative tracking problem widely existing in intelligent scenarios, this paper built a distributed UAV swarm framework inspired by natural intelligence to heighten intricate missions’ efficiency. Also, a standoff collaboratively continuous tracking strategy was proposed based on a lateral guidance law with an improved Reference Point Guidance (RPG) and a longitudinal
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The effect of a tandem vane crossover diffuser configuration on the performance of a MGT mixed flow compressor Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-23 Hano van Eck, Sybrand Johannes van der Spuy
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
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Investigation of inlet flow influenced on the first rotor flow instability at blade non-synchronous vibration state Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-20 Hongwei Ma, Zengzeng Wang, Xiang He, Yafei Zhong
Multistage axial compressor first stage rotor blades have occurred non-synchronous vibration (NSV). An experiment, including fluid and structure measurements, is adopted at the NSV occurred conditions to conduct a detailed investigation about NSV and rotating instability. The blade vibration stress was obtained from the strain gauges. High-frequency response two-hole pressure probes captured the flow
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Cooperative target estimation of strap-down missiles considering random measurement delay Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-20 Bin Zhao, Jie Chen, Ruimin Jiang, Min Zhou
Aiming at the problem of cooperative target estimation for multiple strap-down missiles, this paper is concerned with developing a distributed cooperative estimation fusion algorithm considering the random transmission delay of observation data. As a stepping stone, the random measurement delay system with multiple strap-down missiles is transformed into a delay-free system with correlation noise in
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Development of a steady-state computational fluid dynamics solver for transonic rotorcraft flows Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-19 Saleh Abuhanieh
The capability for solving compressible fluid flows in the rotating frame of reference is added to an existed open-source CFD solver, namely, HiSA solver. The new implementation is explained and validated using the experimental data of the Sikorsky S-76 rotor. A comparison is presented between the moving mesh results obtained from the original HiSA code and the single rotating frame results achieved
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Development and flight test of a manned electric propulsion lightweight airplane Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-13 Hyun-gi Kim, Sungchan Kim
Electrically powered airplanes can cope with global warming by reducing the use of fossil fuels and reduce airplane costs in the long run through the efficient use of energy. For this reason, advanced aviation countries such as the United States and several countries in the European Union are leading the development of innovative technologies to realize a fully electric airplane in the future. Currently
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Optimal sliding mode guidance law against maneuvering target with impact angle constraint Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-13 Mian Gong, Siteng Zhou, Di Zhou
In this paper, an optimal sliding mode guidance law with impact angle constraint is proposed against maneuvering targets. Firstly, the impact angle frame for a static target is extended to a maneuvering target. Then, in this impact angle frame, the optimal reaching law of sliding mode is proposed to design an optimal sliding mode guidance law which is robust to target maneuvers and satisfies an impact
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Rapid trajectory generation for quadrotor with limited motor speed Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-12 Shikai Shao, Yi Guo, Yuanjie Zhao
Planning a safe and dynamic flyable trajectory for unmanned aerial vehicle (UAV) is the precondition for autonomous flight. Considering environmental complexity and flight safety under limited motor speed, we proposed a new time-segmented trajectory planning method, which can ensure motor speed within the allowable range and achieve safe flight. Firstly, the candidate trajectory for quadrotor UAV is
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Calculate the ignition height of the vertical landing phase online for the reusable rocket Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-12 Guanghui Cheng, Wuxing Jing, Changsheng Gao
For the vertical landing phase of the reusable rocket, in order to improve the landing accuracy with consideration of multiple uncertainties, a novel strategy to calculate the ignition height online is proposed based on polynomial guidance law (PGL), particle swarm optimization (PSO), and deep reinforcement learning (DRL). Firstly, a deep neural network (DNN) is designed to describe the relationship
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Asymmetry of oblique shock train and flow control Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-09 Zhigang Zhang, Chuan Cheng, Lantian Zhang, Yuhang Li, Longsheng Xue, Chengpeng Wang, Keming Cheng
An oblique shock train generally forms an asymmetric structure in a Mach-2.7 flow field within a duct. To study the flow structure and interaction between oblique shock trains and upstream shocks, a ramp with equal width was installed inside a Mach-2.7 straight duct to generate an incident shock and an oblique shock train interaction. A Schlieren system, transient pressure measurements and particle
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Characterization modeling of wake vortex circulation decay under reasonable worst case conditions with cuckoo search algorithm Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-09 Ridvan Oruc, Tolga Baklacioglu, Ozlem Sahin
Wake vortex (WV) produced by a large aircraft has the potential to cause serious damage to smaller aircraft following it. In this context, characterization of WV circulation decay under the reasonable worst case (RWC) conditions allows the separation minima to be found safely. In this study, modeling of dimensionless decay curves, which were developed using three experimental LIDAR (Light Detection
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Thermal buckling in multi-directional porous plates: The effects of material grading and aspect ratio Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-08 Lazreg Hadji, Royal Madan, Fabrice Bernard
In the present study, a trigonometric shear deformation plate theory was employed to perform a thermal buckling analysis of multi-directional functionally graded (FG) plates. During the manufacturing of the multi-directional graded plate, the formation of pores is abounded. Hence, the effect of porosity on the buckling performance was investigated by considering the variation of porosity in the plate
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Segmented guidance method for multi-UAVs cooperative attack with spatio-temporal constraints Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-08 Yujie Wang, Zhongnan Tang, Hongbo Xin, Qingyang Chen, Xianzhong Gao, Xiaolong Deng
This paper presents a segmented guidance method for multi-UAVs (unmanned aerial vehicles) cooperative attack with spatio-temporal constraints, and successfully implemented in the flight tests. First, the uniform distribution of UAVs around the target is completed through cooperative path planning and tracking in the mid-course phase. The path planning method for cooperative arrival is proposed based
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A general parametric finite element modeling and stress response analysis methods for pipeline system using the nonconforming solid element Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-07 Wenhao Ji, Wei Sun, Hongwei Ma, Yu Zhang, Xin Wang
In the dynamic topology optimization design of pipeline system, parametric finite element modeling (PFEM) is needed to improve the model reconstruction efficiency. Taking a typical spatial single pipeline as the research object, this paper innovatively presents a PFEM method of pipeline system based on the newly constructed nonconforming solid (Solid-NC) element. The stiffness and mass matrices of
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Adaptive control law based integrated guidance and control design for missile with the radome error compensation Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-06 Jianguo Guo, Yinghe Zhou, Min Zhou
This paper presents an integrated guidance and control design for the homing missiles with the radome error compensation to address the guidance problems caused by radome. Firstly, a mathematics model of the integrated guidance and control system with the compensation for the radome error is built by integrating the missile dynamics and the engagement kinematics between the missile and ground target
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Non-uniform flow characteristics and rotating instability of a transonic high-pressure compressor rotor with cavity bleed Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2024-02-06 Chen Xu, Shaowen Chen, Yun Gong
The presence of bleed in an aero engine’s compressor can significantly impact its flow characteristics and contribute to rotating instability. This study focuses on the impact of a typical cavity bleed structure on the internal flow characteristics of a compressor, specifically its circumferential non-uniformity and aerodynamic stability. A numerical simulation involving multiple flow passages was
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Acoustic velocity analogy formulation for sources in quiescent medium Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-05-11 Jiahua He, Sidan Xue, Qiuhong Liu, Dangguo Yang, Liangquan Wang
The prediction of near field acoustic velocity is necessary when using equivalent source method and evaluating multi acoustic fields problem. According to the idea of acoustic analogy, this paper i...
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In-motion initial alignment method using Cayley–Kalman filter on special orthogonal group Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-20 Fujun Pei, Hengming Zhang, Siyuan Li
Aiming at the in-motion initial alignment problem of strapdown inertial navigation system (SINS), this paper proposed a precise direct in-motion alignment method based on attitude matrix representa...
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Adaptive diagnosis and non-fragile predictive control for HFV engine with non-Gaussian uncertain output Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-17 Kai-Yu Hu, Zian Cheng, Jingxiu Gong
This study presents an adaptive fault estimation and model predictive fault-tolerant control (FTC) for the hypersonic vehicle engine with non-Gaussian uncertain output jet plume. The non-Gaussian p...
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Optimization of novel flat serial single-phase radiators for spacecraft thermal control Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-17 Phanidra B. Chiranjeevi, Venkateswaran Ashok, K. Srinivasan, T. Sundararajan
Space thermal radiators play a significant role in the thermal management of spacecraft. With the increase in heat dissipation requirement, the heat pipe radiators are being replaced by mechanicall...
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A review on insects flight aerodynamics, noise sources, and flow control mechanisms Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-14 Foad Moslem, Zahra Babaie, Mehran Masdari, Kirchu Fedir
Wildlife always acts as an inspiration source for humans to help them study and mimic flight methods. Insects are one of the most important sources of biological systems’ inspiration to control flo...
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High-altitude airship variable-pitch propeller performance analysis at multiple altitudes Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-13 Wang Dongchen, Song Bifeng, Jiao Jun, Xue Dong
To achieve better propulsion performance for high-altitude airships, this paper proposes a variable-pitch propeller design and performance analysis. Propeller surrogate models were constructed base...
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Variable-horizon predictive tracking control for air-breathing hypersonic vehicle based on composite disturbance observer Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-09 Jin Zhao, Mou Chen
In this paper, a variable-horizon predictive tracking control (VHPTC) scheme based on composite disturbance observer (CDO) is proposed to investigate the attitude tracking problem for an air-breath...
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Research on selection method of aero-engine health parameters based on correlation and condition number Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-07 Cheng Chen, Qiangang Zheng, Haibo Zhang
Aiming at the problem of how to select aero-engine health parameters when the number of sensors is limited, a method of selecting aero-engine health parameters based on correlation and condition nu...
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Adaptive second order sliding mode guidance law for missile-target interception with fuzzy logic system Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-07 Handan Gürsoy-Demir, Mehmet Önder Efe
This paper presents the design of a 3D missile guidance law based on a second order sliding mode control technique employing an adaptive tuning law and a fuzzy gain scheduling. At the outset, the s...
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The cubic pitching moment coefficient of spin-stabilized projectiles Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-06 Sijiang Chang, Jingwen Zhang, Wei Wei
This technical note presents a feasible method to effectively predict the cubic pitching moment coefficient for spin-stabilized projectiles. First, a surrogate model for predicting the cubic moment...
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Contact stress analysis of external non-variable multi-modulus spur gear pairs Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-05 Zengbao Zhu, Hongbo Cui, Mingzhen Gong, Heyun Bao, Rupeng Zhu
The conditions of correct gear engagement of a pair of involute gears and the principle of geometric relationship of involute tooth profile are derived to determine the pitch point of externally me...
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Dynamics-based deep learning and fractional-order fixed-time sliding mode control for space robot impedance system Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-04-05 Tongyu Zhao, Guanghui Sun, Weihong Zhu
To complete complex tasks with space robots in the impedance environment, sliding mode control (SMC) has been proposed and plays an important role in the past decades. Learning-based control has al...
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Civil aviation safety risk intelligent early warning model based on text mining and multi-model fusion Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-31 Zhaoguo Hou, Minglan Xiong, Huawei Wang, Shaolan Lv, Lingzi Chen
Aviation unsafe events often lead to major casualties and property losses. Aviation safety risk intelligent early warning is an important means to ensure the safe and reliable operation of aircraft...
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An innovative integrated path planning and trajectory tracking framework for a quadrotor slung load system in an urban environment Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-31 Peyman Abeshtan, Fariborz Saghafi
In this paper, a hybrid path planning and trajectory tracking controller for a quadrotor slung load system is presented. This controller has benefited from the fuzzy inference system in its trackin...
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Nonlinear aeroelastic stability analysis of a folding wing by using geometrically exact fully intrinsic beam equations Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-31 Sayed Hossein Moravej Barzani, Hossein Shahverdi
In this paper, the aeroelastic instability of folding wings by using the geometrically exact fully intrinsic beam equations is investigated. The important advantages of these equations in compariso...
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A modified dual time integration technique for aerodynamic quasi-static and dynamic stall hysteresis Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-29 Mohamed Sereez, Nikolay Abramov, Mikhail Goman
Simulation of the aerodynamic stall phenomenon in both quasi-static and dynamic conditions requires expensive computational resources. The computations become even more costly for static stall hyst...
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Numerical solution of spacecraft pursuit-Evasion-Capture game based on progressive shooting method Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-23 Tian Liao, Shunli Li, Xinlong Chen, Mengping Zhu
The time optimal pursuit-evasion-capture (PEC) game problem for two spacecraft with continuous constant thrust is studied, which is a typical and considerable game scenario in practice. Progressive...
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Optimal hybrid Coulomb control for on-track rendezvous and docking of spacecraft Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-22 Gaurav Kumar, Dipak Kumar Giri, Shashi Ranjan Kumar
This paper investigates the dynamics of on-track rendezvous and docking of two spacecraft, and stabilization using hybrid Coulomb control. Modeling electrostatic forces and torques for control of c...
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Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-16 Hyun-gi Kim, Sungchan Kim, Su-hong An, Byoung-geun Ha, Young-shin Kim
An external fuel tank, one of the main components of an aircraft, is a component that extends the range of the aircraft and that should be separable from the aircraft in emergency situations. Durin...
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Aerostructural performance improvement in an unmanned long endurance aircraft using adaptive wing concept Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-14 Ashok K Sampath, Madhusudan A Padmanabhan, Subhaschandra Kattimani
This paper presents an analytical research study to improve the aerostructural performance of an unmanned medium altitude long endurance aircraft using the adaptive wing concept. Aerodynamic drag a...
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Implementation of a finite element modelling strategy for the prediction of aircraft tyre response Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-11 Amit Ramji, Marzio Grasso, James Chase, Hasher Maqbool, Michal Krypciak, Veronica Merchante, James Brighton
This paper presents the finite element modelling (FEM) strategy to identify the structural response of aircraft tyres under quasi-static and taxiing load conditions. The tyre FEM was developed to s...
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Experimental and numerical research on flow characteristics of inlet particle separator for aero-engine under the influence of water film Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-10 Mingcong Luo, Qionglei Hu, Aocheng Liu, Kim Tiow Ooi, Qun Zheng, Shilin Yan
An aero-engine must be able to operate in all-weather conditions, which requires the aircraft to be safe throughout the flight even in bad weather. Excessive intake of rainwater can induce stall an...
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Comparison between two computational fluid dynamics methods for gust response predictions Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-09 Zhenlong Wu, Yuan Gao, Xiaoming He, Weizhe Fu, Jianqiang Shi, Zhibo Zhang, Ruitao Zhou
Based on the open-source computational fluid dynamics (CFD) platform, OpenFOAM, two numerical simulation methods for gusty inflow characterization and gust response prediction are implemented by so...
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A novel method to identify the multiple faults of intermediate bearing based on multiscale Lempel–Ziv complexity enhancement Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-09 Mingyue Yu, Guihong Guo, Haonan Cong, Minghe Fang
In order to solve the difficulty to correctly identify a compound failure in intermediate bearing of aircraft engine, the paper has brought forward the method of strengthening fault feature informa...
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Research on afterburning control of more electric engine with a nonlinear fuel supply system Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-03-08 Zhihua Xi, Yong Wang, Haibo Zhang, Fengyong Sun, Qiangang Zheng, Zhemin Zhu
More electric engine (MEE) with electric pump metering fuel has the problem of unstable engine control due to the dead-zone characteristics of afterburner fuel actuator. On the basis of conventiona...
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Design studies for a light aircraft wing with highly integrated load-bearing hydrogen tanks using multi-objective optimization methods Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-02-24 Felix Friedmann, Hannes Rienecker, Florian Dexl, Andreas Hauffe, Klaus Wolf
To enable emission-free flight, the use of hydrogen as an energy carrier in aircraft is one possible solution. However, hydrogen storage is a challenging task. The current paper presents a design s...
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Real-time robust tracking control for a quadrotor using monocular vision Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-02-24 JR Montoya-Morales, ME Guerrero-Sánchez, G Valencia-Palomo, O Hernández-González, FR López-Estrada, JA Hoyo-Montaño
In this paper, the autonomous trajectory-tracking problem for an Unmanned Aerial Vehicle (UAV) based on Sliding Mode Control (SMC) algorithms is treated. The control system is implemented in real-t...
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Pipeline fault simulation and control of a liquid rocket engine Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-02-23 Yuqiang Cheng, Runsheng Hu, Jianjun Wu
The feedback control system was designed to control the pipeline blockage and leakage fault. Based on the open-loop engine system, different degrees of faults were simulated, and the changes in sys...
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A fault diagnosis method based on improved parallel convolutional neural network for rolling bearing Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-02-20 Tao Xu, Huan Lv, Shoujin Lin, Haihui Tan, Qing Zhang
There are many disadvantages for traditional Convolutional Neural Network (CNN) in rolling bearing fault diagnosis, such as low efficiency, weak noise immunity, and poor generalization with changin...
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Method of aeroengine fault diagnosis based on a Fingerprint map Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-02-20 Yao-hua Li, Ying-qi Gou, Cheng Pan, Kaige Song
The electrification and intelligentization trends of aeroengine systems present new challenges for the diagnostics of traditionally centralized control architectures. Scientific and practical fault...
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A novel UAV-integrated deep network detection and relative position estimation approach for weeds Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-02-20 Mahmoud Abdulsalam, Kenan Ahiska, Nabil Aouf
This paper aims at presenting a novel monocular vision–based approach for drones to detect multiple type of weeds and estimate their positions autonomously for precision agriculture applications. T...
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Advanced fault detection and diagnosis in spacecraft attitude control systems: Current state and challenges Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-02-17 Seid H Pourtakdoust, Mohamad Fakhari Mehrjardi, Mohammad Hossein Hajkarim, Forough Nasihati Gourabi
A review of advanced fault detection and diagnosis (FDD) techniques in attitude control systems (ACSs) of spacecraft is presented. In the first part of the paper, several types of ACS failure scena...
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A review of aircraft environmental control system simulation and diagnostics Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.1) Pub Date : 2023-02-16 Shafayat H Chowdhury, Fakhre Ali, Ian K Jennions
The aircraft Environmental Control System (ECS) enables the aircraft to maintain a comfortable and safe environment for its passengers throughout its operating envelope. The Pressurised Air Conditi...