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A flight mechanics-based justification of the unique range of Strouhal numbers for avian cruising flight Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-22 Diganta Bhattacharjee; Kamesh Subbarao
In this paper, analytical expressions for cycle-averaged aerodynamic forces generated by flapping wings are derived using a force model and flapping kinematics suitable for the forward flight of avian creatures. A strip theory-based formulation is proposed and the analytical expressions are found as functions of the amplitude of twist profile, mean twist angle, the flow separation point on the upper
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Neural network adaptive backstepping fault tolerant control for unmanned airships with multi-vectored thrusters Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-22 Shiqian Liu; James F Whidborne
This paper presents the fault tolerant control (FTC) of an unmanned airship with multiple vectored thrusters in the presence of model parameter uncertainties and unknown wind disturbances. A fault tolerant control based on constrained adaptive backstepping (CAB) approach, combined with a radial basis function neural network (RBFNN) approximation, is proposed for the airship with thruster faults. A
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Investigation of infrared dim and small target detection algorithm based on the visual saliency feature Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-22 Shaoyi Li; Xiaotian Wang; Xi Yang; Kai Zhang; Saisai Niu
Infrared dim and small target detection has an important role in the infrared thermal imaging seeker, infrared search and tracking system, space-based infrared system and other applications. Inspired by human visual system (HVS), based on the fusion of significant features of targets, the present study proposes an infrared dim and small target detection algorithm for complex backgrounds. Firstly, in
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Experimental study on soft PSD material of dual pulse solid rocket motor Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-21 Chunguang Wang; Weiping Tian; Liwu Wang; Guiyang Xu
In order to study the failure reason of the soft PSD in the dual pulse solid rocket motor (SRM), the deformation process of the intermediate section of the second pulse combustion chamber was simplified to the two-dimensional plane strain state, and the calculation method of the circumferential strain of the soft PSD was obtained. The influencing factors of the circumferential strain of the soft PSD
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Corrigendum to Optimality considerations for propulsive fuselage power savings Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-21
Optimality considerations for propulsive fuselage power savings, by Arne Seitz, Anaïs Luisa Habermann and Martijn van Sluis. First Published April 8, 2020 DOI: 10.1177/0954410020916319
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Moving-horizon-estimator-integrated adaptive hierarchical sliding mode control for flexible hypersonic vehicles considering aeroservoelastic effect Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-17 Erkang Chen; Wuxing Jing; Changsheng Gao
In order to solve the attitude control problem of flexible hypersonic vehicles with consideration of aeroservoelastic effect, uncertainty and external disturbance, a novel moving-horizon-estimator-integrated adaptive hierarchical sliding mode control scheme is presented in this paper. First, the measurement model considering flexibility is established and the influence of aeroservoelastic effect on
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Comprehensive design of an oleo-pneumatic nose landing gear strut Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-13 Muhammad Ayaz Ahmad; Syed Irtiza Ali Shah; Taimur Ali Shams; Ali Javed; Syed Tauqeer ul Islam Rizvi
A comprehensive design cycle of a nose landing gear strut having an oleo-pneumatic shock absorber for a lightweight aircraft is proposed. Design and analysis of a retractable nose landing gear according to Airworthiness Standards FAA FAR Part 23 have been carried out. This research is focused on mathematical modeling of an oleo-pneumatic strut with an analytical solution of design variables at static
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CFD-CSD method for coupled rotor-fuselage vibration analysis with free wake-panel coupled model Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-11 Siwen Wang; Jinglong Han; Haiwei Yun; Xiaomao Chen
An efficient comprehensive vibration analysis method for a helicopter rotor–fuselage coupling system is presented. This loose computational fluid dynamics (CFD)/computational structural dynamics (CSD) coupling approach with a free wake–panel coupled model is used for system vibration response analysis. The CSD model of the helicopter consists of a fuselage model using a refined three dimensional (3 D)
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Experimental and numerical analysis of fluid-solid-thermal coupling on electric fuel pump Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-09 Renfeng Wei; Zhifeng Ye
This paper designs an axial partition fuel cooling shell to solve the problem of temperature rise in the motor of the electric fuel pump (EFP). And describes a simplified method in conjunction with the computational fluid dynamics(CFD) to analyze heat generations and fuel cooling effects in integrated EFPs. Furthermore, CFD is used to numerically simulate the coupling effects among the fluid-solid-thermal
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Time-marching solution of transonic flows at axial turbomachinery meanline Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-09 Simone Rosa Taddei
A new blade force model is coupled to quasi-one dimensional Euler equations for a variable geometry flowpath. After analytical inclusion of the blade force, the flow equations take a strictly one-dimensional form with specific expressions of the convective flux and blade load source terms. Regardless of the flow turning, that is simply achieved by the load source term as an explicit function of the
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Numerical study of the flow over the modified simple frigate shape Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-09 Tong Li; Yibin Wang; Ning Zhao
The simple frigate shape (SFS) as defined by The Technical Co-operative Program (TTCP), is a simplified model of the frigate, which helps to investigate the basic flow fields of a frigate. In this paper, the flow fields of the different modified SFS models, consisting of a bluff body superstructure and the deck, were numerically studied. A parametric study was conducted by varying both the superstructure
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Evaluation on the performance fluctuation after water ingestion for a turbofan engine compressor during flight descent Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-09 Lu Yang; Qun Zheng; Aqiang Lin
Turbofan engine compressor is most severely threatened by the entry of liquid water during flight descent. This study aims to deeply understand the fluctuations of compressor performance parameters caused by water ingestion through frequency spectrum analysis. The water content and droplet diameter distribution are determined based on the real heavy rain environment. Results reveal that most of the
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Far-field drag decomposition using hybrid formulas and vorticity based area sensors Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-08 L Qiao; XL He; Y Sun; JQ Bai; L Li
Numerical simulation of flow-field has become an indispensable tool for aerodynamic design. Usually, wall surface integration is a tool used to calculate values of pressure drag and skin friction drag, but the aerodynamic mechanism of drag production is still confusing. In present work, in order to decompose the total drag into viscous drag, wave drag, induced drag, and spurious drag, a far-field drag
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An experimental study of rotor-stator wake unsteadiness in a multistage axial compressor Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-08 Jun Li; Jun Hu; Chenkai Zhang
The flow in a multistage axial compressor is highly unsteady, three-dimensional and turbulent. The interaction between compressor blade rows results in rotor/stator wake unsteadiness, which is not typically considered in the computational fluid dynamics (CFD) models. To gain depth and insight into the inner flow mechanism in multistage compressors, specifically the wake variability driven by the rotor/stator
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A novel system identification algorithm for quad tilt-rotor based on neural network with foraging strategy Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-08 Zhigang Wang; Zhichao Lyu; Dengyan Duan; Jianbo Li
Quad tilt-rotor(QTR) UAV is a nonlinear time-varying system in full flight mode. It is difficult and inaccurate to model the nonlinear time-varying system, which cannot fully reflect the problem of controlling input and system response output in the full flight mode. In order to solve the above problems, a novel neural network model was adopt to identify the nonlinear time-varying system of quad tilt-rotor
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Numerical transient responses of cut-out borne composite panel and experimental validity Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-08 Hukum Chand Dewangan; Subrata Kumar Panda
The effect of cut-out parameters (shapes: square and circular; position: concentric/eccentric) on the dynamic deflection values of the curved/flat layered composite panel are verified experimentally with the higher-order finite element solutions first-time. The solutions are obtained using the linear finite element model in the framework of cubic-order displacement filed functions. The necessity of
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An improved dynamic load-strength interference model for the reliability analysis of aero-engine rotor blade system Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-06 Bingfeng Zhao; Liyang Xie; Yu Zhang; Jungang Ren; Xin Bai; Bo Qin
As the power source of an aircraft, aero-engine tends to meet many rigorous requirements for high thrust-weight ratio and reliability with the continuous improvement of aero-engine performance. In this paper, based on the order statistics and stochastic process theory, an improved dynamic load-strength interference (LSI) model was proposed for the reliability analysis of aero-engine rotor blade system
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Thermal and structural response of aerospike mounted on blunt-nose body Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-12-06 Zhang ZhunHyok; Won CholJin; Ri CholUk; Kim CholJin; Kim RyongSop
The inclusion of aerospike on blunt nose body of hypersonic vehicle has been considered to be the simplest and most efficient technique for a concurrent reduction of both aeroheating and wave drag due to hypersonic speed. However, the thermal and mechanical behavior of aerospike structure under the coupling effect of aerodynamic force and aeroheating remains unclear. In this study, the thermal and
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Enhancement of air entrainment in ejector-diffuser using plate guidance at slots to reduce infrared emission Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-30 L Singh; SN Singh; SS Sinha
Ejector-diffuser reduces infrared emissions and are installed in combat aircraft to counter the threat of heat-seeking missile. The specific role of an ejector-diffuser is to reduce the heat emissions without substantially affecting the engine performance. The present study investigates a new design of ejector-diffuser wherein straight-plates and hybrid-straight-plates are installed at each slot for
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Multi-physics simulation of an insect with flapping wings Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-30 Kabir Bakhshaei; Hoomaan MoradiMaryamnegari; Sadjad SalavatiDezfouli; Abdol Majid Khoshnood; Mani Fathali
In this paper, the unsteady aerodynamic of an insect’s forward flight has been carried out with a novel approach. In order to fully utilize the available powerful solvers, an innovative intermediary MATLAB code has been written for the high-fidelity time-resolved multi-physics problems involving fluid flow and multi-body simulations. For simulating the insect’s flight, the FLUENT solver has been utilized
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Preliminary parameters design for a long endurance unmanned helicopter with low rotor-disc loading Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-30 Hong Zhao; Jian-Bo Li; Yuan Wang; Zhi-Gang Wang
This paper investigates the design of a long-endurance unmanned helicopter (LEUH) with low rotor disc loading (LRDL) and low rotor speed (LRS). Due to the flaws in flying qualities caused by the LRDL and the LRS, this paper establishes a flying quality evaluation model in which handling qualities (FQs) and flight control (FC) are introduced into the distributed multi-objective collaborative optimization
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A numerical study on the single pulsed energy addition based unsteady wave drag reduction at varied hypersonic flow regimes Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-27 Dathi SNV Rajasekhar Rao; Bibin John
In this study, unsteady wave drag reduction in hypersonic flowfield using pulsed energy addition is numerically investigated. A single energy pulse is considered to analyze the time-averaged drag reduction/pulse. The blast wave creation, translation and its interaction with shock layer are studied. As the wave drag depends only on the inviscid aspects of the flowfield, Euler part of a well-established
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Fixed-time three-dimensional guidance law with input constraint and actuator faults Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-23 Peng Li; Qi Liu; Chen-Yu He; Xiao-Qing Liu
This paper investigates the three-dimensional guidance with the impact angle constraint, actuator faults and input constraint. Firstly, an adaptive three-dimensional guidance law with impact angle constraint is designed by using the terminal sliding mode control and nonhomogeneous disturbance observer. Then, in order to solve the problem of the input saturation and actuator faults, an adaptive anti-saturation
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An experimental investigation on the use of a rectangular strut in a scramjet thruster for thrust vector control Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-23 DR Biju Ben Rose; BTN Sridhar
An experimental investigation was carried out to find the effect of a strut spanning across the width of a single expansion ramp of a laboratory model scramjet thruster as a thrust vector control device. Cold flow tests were conducted with operating total pressures ranging from 4 bar to 10 bar and the thruster exhaust was to ambient atmosphere. The mass flow rate varied from 0.105 kg/s to 0.263 kg/s
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A numerical study on the blow-off limit of premixed hydrogen/air flames in a cylindrical micro-combustor Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-19 Saeed Naeemi; Seyed Abdolmehdi Hashemi
In the current work, a numerical study on combustion of premixed H2–air in a micro-cylindrical combustor was carried out and the critical velocity of inlet flow that causes the blow-off was obtained. Furthermore, the effects the equivalence ratio, wall thickness, geometry of combustor and thermal properties of walls on the critical blow-off velocity were studied. The numerical results showed that,
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Effects of skin heat conduction on aircraft icing process Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-11 Xiaobin Shen; Yu Zeng; Guiping Lin; Zuodong Mu; Dongsheng Wen
During the aircraft icing process caused by super-cooled droplet impingement, the surface temperature and heat flux distributions of the skin would vary due to the solid substrate heat conduction. An unsteady thermodynamic model of the phase transition was established with a time-implicit solution algorithm, in which the solid heat conduction and the water freezing were analyzed simultaneously. The
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Virtual guidance-based finite-time path-following control of underactuated autonomous airship with error constraints and uncertainties Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-05 Yan Wei; Pingfang Zhou; Yueying Wang; Dengping Duan; Zheng Chen
This paper addresses the finite-time three-dimensional path-following control problem for underactuated autonomous airship with error constraints and uncertainties. First, a five degrees-of-freedom path-following error model in the Serret-Frenet coordinate frame is established. By applying the finite-time stability theory, a virtual guidance-based finite-time adaptive neural backstepping path-following
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Leading edge redesign of dual-peak type variable inlet guide vane and its effect on aerodynamic performance Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-04 Hengtao Shi; Lucheng Ji
Recently, a new type airfoil for variable inlet guide vane (VIGV), featuring “dual-peak” surface velocity pattern at high incidence, is proposed and shows wide low-loss operation range. To further improve its performance, this paper researches the influence of leading edge (LE) thickness and shape on the loss level and surface velocity features of the “dual-peak” type airfoil. Firstly, a polynomial-based
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Attitude trajectory tracking of quadrotor UAV using super-twisting observer-based adaptive controller Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-11-04 Ai-Jun Chen; Ming-Jian Sun; Zhen-Hua Wang; Nai-Zhang Feng; Yi Shen
The successful implementation of high-level decision algorithm on quadrotor depends on the accurate trajectory tracking performance. In this paper attitude estimation and trajectory tracking control problem of quadrotor unmanned aerial vehicle (UAV) with endogenous and exogenous disturbance are considered, where the lumped disturbance characteristic does not have a probabilistic illustration but instead
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Characteristics of open cavity flow with floor inclinations at M = 2.0 Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-27 VS Saranyamol; Priyank Kumar; Sudip Das
Experimental studies on open cavity flows at supersonic speed of M = 2.0 were carried out. Oil flow visualization tests were made to understand the steady features of the surface flow field. Unsteady pressure measurements were done at five locations inside the cavity and pressure spectrum of these measurements were obtained. Cavity floor was made inclined to influence the flow directing towards the
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Entrance length effects on the flow features of rectangular liquid jets Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-27 MH Aliyoldashi; M Tadjfar; A Jaberi
An experimental study was carried out to investigate the effects of entrance length on the main characteristics of rectangular liquid jets discharged into the stagnant atmosphere. Six rectangular nozzles, all with the same aspect ratio of 3 but with different entrance length ratios ranging from 3.3 to 60 were constructed. The physics of the fluid flows was visualized by the aid of backlight shadowgraph
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Fast fixed-time convergent smooth adaptive guidance law with terminal angle constraint for interception of maneuvering targets Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-26 Peng Zhang; Xiaoyu Zhang
This paper introduces a fast fixed-time guidance law with terminal angle constraint for interception of maneuvering targets, which is based on the structure of singularity-free fast terminal sliding mode and the fixed-time stability theory. Different from the finite-time stability, the fixed-time stability can predefine the maximum stabilization time of system states which is independent on the initial
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On the reductions of aerofoil-turbulence interaction noise through multi-wavelength leading edge serrations Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-26 S Narayanan; Sushil Kumar Singh
This paper provides an experimental study into the use of multi-wavelength sinusoidal leading edge (LE) serrations for enhancing the aerofoil-broadband noise reductions. The noise reduction performances of multi-wavelength serration profiles introduced on a flat plate are compared against those generated by single-wavelength profiles when applied separately. The multi-wavelength leading edge serration
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Analysis of influencing parameters in ion thruster plume simulation Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-26 Baiyi Zhang; Guobiao Cai; Hongru Zheng; Bijiao He; Huiyan Weng
Effects from ion thruster plume have long raised concerns. However, little work has systematically analyzed the influencing parameters in the ion thruster plume simulation. This paper analyzes LIPS 200 ion thruster plume simulations about the influencing parameters. The numerical simulations are carried out by a hybrid particle-in-cell (PIC) method and the direct simulation Monte Carlo (DSMC) method
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Free vibration analysis of rotating thin-walled cylindrical shells with hard coating based on Rayleigh-Ritz method Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-26 Dongxu Du; Wei Sun; Xianfei Yan; Kunpeng Xu
This paper focuses on the free vibration analyses of the rotating hard-coating cylindrical shells with various boundary conditions and the effects of hard coating on the vibration behaviors of the rotating shells. To accurately predict more natural characteristics, the characteristic orthogonal polynomials are taken as the admissible displacement functions. Considering the influences of Coriolis force
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Compressible large eddy simulation of the unsteady evolution process in a LPT Cascade with incoming wakes Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-26 Yunfei Wang; Huanlong Chen; Huaping Liu; Yanping Song; Fu Chen
An in-house large eddy simulation (LES) code based on three-dimensional compressible N-S equations is used to research the impact of incoming wakes on unsteady evolution characteristic in a low-pressure turbine (LPT) cascade. The Mach number is 0.4 and Reynolds number is 0.6 × 105 (based on the axial chord and outlet velocity). The reduced frequency of incoming wakes is Fred = 0 (without wakes), 0
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Shock train control by boundary layer suction in a scramjet isolator Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-26 Vignesh Ram Petha Sethuraman; Tae Ho Kim; Heuy Dong Kim
The isolator plays a critical role in the scramjet engine situated between the inlet and the combustion chamber. The flow field is more complex with shock–shock interaction and shock boundary layer interaction result in a series of compression waves reffered to as “shock train”. The presence of such flow inside the isolator can degrade the performance of the scramjet engine. The present study focus
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Structure and aerodynamic characteristics of a coaxial quad-wing flapper Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-26 Huan Shen; Qian Li; Kun Hu; Zhuoqun Feng; Aihong Ji
As a special type of micro ornithopter, the coaxial quad-wing flapper (CQWF) enables greater flight speed and higher stability than the paired-wing flapper. These characteristics are closely related to the unique pneumatic mechanism of the CQWF. Therefore, the aerodynamic generation mechanism of the CQWFs has been actively researched in recent years. This study verifies the reliability of flow-field
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Numerical study on aerodynamic performance of waverider with a new bluntness method Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-26 Zhipeng Qu; Houdi Xiao; Mingyun Lv; Guangli Li; Cui Kai
Abastrct The waverider is deemed the most promising configuration for hypersonic vehicle with its high lift-to-drag ratio at design conditions. However, considering the serious aero-heating protection, the sharp leading edge must be blunted. The existing traditional bluntness methods including the following two types: “reducing material method” and “adding material method”. Compared to the initial
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Aircraft flat-spin recovery using sliding-mode based attitude and altitude control Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-22 Salahudden; Vijay S Dwivedi; Prasiddha N Dwivedi; Dipak K Giri; Ajoy K Ghosh
In the present paper, a control command to recover steady-straight-level flight from flat-oscillatory-stable-left-spin is developed using a sliding-mode based attitude and altitude control. Direct spin recovery, using a spin solution by bifurcation results, to low angle-of-attack is achieved in finite-time without any separation in dynamics. The exponential convergence of errors is discussed by invoking
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Cooperative guidance law for active aircraft defense with intercept angle constraint Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-22 Min He; Xiaofang Wang; Hai Lin; Nianyuan Xiao; Zonglin Du
In this paper, the three-body engagement scenario is considered where a target aircraft fires a defender missile to intercept the attacker missile. A cooperative guidance law with the intercept angle constraint for both of the defender missile and target has been presented. With the assumption that the attacker missile uses augmented proportional navigation guidance law, the nonlinear relative motion
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Investigation of rotating detonation fueled by pre-combustion cracked kerosene under different channel widths Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-22 Xingkui Yang; Yun Wu; Yepan Zhong; Feilong Song; Shida Xu; Di Jin; Xin Chen; Shunli Wang; Jianping Zhou
In this study, the effects of channel widths on the characteristics of the rotating detonation wave (RDW) were investigated. Pre-combustion cracked kerosene and 50% oxygen-enriched air were taken as the propellant. Keeping the outer diameter (D = 150mm) constant, the channel widths (W) of the combustor range from 15 mm to 50 mm in the experiments. The results indicate that the time for the formation
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Effects of propeller flow on the longitudinal and lateral dynamics and model couplings of a fixed-wing micro air vehicle Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-22 K Harikumar; Jinraj V Pushpangathan; Suresh Sundaram
This paper analyzes the effects of propeller flow on the linear coupled longitudinal and lateral dynamics of a 150 mm wingspan fixed wing micro air vehicle (MAV). The effects propeller flow on the lift, drag, pitching moment and side force is obtained through wind tunnel tests. The aerodynamic forces and moments are modeled as a function of angle of attack, sideslip angle, control surface deflection
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Characteristics of helicopter engine exhaust through scaled experiments using stereoscopic particle image velocimetry Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-22 Zhen Wei Teo; Wai Hou Wong; Zhi Wen Lee; Tze How New; Bing Feng Ng
Helicopter engines are often mounted atop the fuselage to keep the aircraft footprint small and optimal for operations. As a result, hot gases produced by the engines may inadvertently impinge upon the tail boom or dissipate inefficiently that compromises on operation safety. In this study, a scaled fuselage model with a hot air blower was used to simulate hot exhaust gases. The velocity field immediately
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Effect of air jet with injection pressure on the performance of mixed compression air intake Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-22 NK Gahlot; NK Singh
A computational study on the performance of mixed compression supersonic air intake has been carried out with and without air jet at various operating conditions. Commercially available software ANSYS was used and K-ω SST turbulence model was selected to capture the turbulent flow inside the air intake. All the simulations were simulated at a design Mach number of 2.2. Two Air jet of 1 mm diameter
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Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-22 Čedomir Kostić; Aleksandar Bengin; Boško Rašuo; Dijana Damljanović
The goal of this work is to build a unique numerical method to obtain the basic aerodynamic characteristics of the aircraft and to enable a wide application of the method in the analysis of some aerodynamic characteristics of the aircraft, without use of empirical methods. The Computational fluid dynamics (CFD) simulation method was being calibrated based on test results of the standard AGARD-B (Advisory
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Grid transformation and dynamic scattering for tail rotor radar cross section analysis Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-21 Zeyang Zhou; Jun Huang
With the promotion and enhancement of stealth technology of helicopter rotor components, the research on the dynamic radar cross section (RCS) of helicopter rotor is becoming more and more important and imminent. In order to facilitate the calculation and analysis of the electromagnetic scattering characteristics during rotor rotation, a dynamic scattering calculation (DSC) method based on quasi-static
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Influence of tip clearance and cavity depth on heat transfer in a cutback squealer tip Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-20 Weijie Wang; Shaopeng Lu; Hongmei Jiang; Qiusheng Deng; Jinfang Teng; and Wensheng Yu
Numerical simulations are conducted to present the aerothermal performance of a turbine blade tip with cutback squealer rim. Two different tip clearance heights (0.5%, 1.0% of the blade span) and three different cavity depths (2.0%, 3.0%, and 6.0% of the blade span) are investigated. The results show that a high heat transfer coefficient (HTC) strip on the cavity floor appears near the suction side
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Numerical study of the pseudo-boiling phenomenon in the transcritical liquid oxygen/gaseous hydrogen flame Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-20 Hamed Zeinivand; Mohammad Farshchi
The interactions and effects of turbulent mixing, pseudo-boiling phenomena, and chemical reaction heat release on the combustion of cryogenic liquid oxygen and gaseous hydrogen under supercritical pressure conditions are investigated using RANS simulations. Comparisons of the present numerical simulation results with available experimental data reveal a reasonably good prediction of a supercritical
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Analysis of rotor aerodynamic response during ramp collective pitch increase by CFD method Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-20 Kai Zhang; Qijun Zhao; Xiayang Zhang; Guohua Xu
In order to study the aerodynamic response characteristics of the helicopter rotor during ramp collective pitch increase, the moving-embedded grid technique is employed for numerical simulation. The governing equations are modeled via Navier-Stokes equations, as well as one equation S-A turbulence model. In order to improve the precision of unsteady simulation of the rotor flowfield, the three-order
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Towards a methodology for new technologies assessment in aircraft operating cost Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-12 Valeria Vercella; Marco Fioriti; Nicole Viola
The need for a greener and competitive aircraft is leading to the use of new technologies. A thorough assessment of these technologies is mandatory from the initial phases of aircraft design to understand their feasibility and to select the most promising one both in terms of performances and in terms of costs. This paper proposes a methodology to assess the operating cost of innovative technologies
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Adaptive compliant controller for space robot stabilization in post-capture phase Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-12 Pengcheng Xia; Jianjun Luo; Mingming Wang
Safety and reliability are the primary prerequisites of space robotic manipulation. Due to the inaccurate inertial parameters of the tumbling target, tracking the desired trajectory directly will lead to the build up of large contact force and torque and damage the grasping point. The measurement noise in the contact wrenches will disturb the application of compliant stabilization strategy, and lead
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Editorial Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-10-06 Lucas FM da Silva; Robert D Adams; Chiaki Sato; Klaus Dilger
This special issue of Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering contains selected papers presented at the 1st International Conference on Industrial Applications of Adhesives 2020 (IAA 2020), held in Funchal, Madeira (Portugal) during 5-6 March 2020. The goal of the conference was to provide a unique opportunity to exchange information, present
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Performance improvement of a high-speed aero-fuel centrifugal pump through active inlet injector Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-09-23 Jia Li; Xin Wang; Wancheng Wang; Yue Wang
This paper presents a high-speed aero-fuel centrifugal pump with an active inlet injector for an aero-engine aiming at regulating the internal flow field and improving overall hydraulic performance. Unlike most of the existing centrifugal pumps for aero-engines, an injector is designed and integrated with the pump to accomplish the active flow control. Firstly, by employing the energy equation in the
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DSMC simulation of rarefied gas flow over a 2D backward-facing step in the transitional flow regime: Effect of Mach number and wall temperature Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-09-23 Deepak Nabapure; Ram Chandra Murthy K
Rarefied gas flow over a backward-facing step (BFS) is often encountered in separating flows prevalent in aerodynamic flows, engine flows, condensers, space vehicles, heat transfer systems, and microflows. Direct Simulation Monte Carlo (DSMC) is a powerful tool to investigate such flows. The purpose of this research is to assess the impact of Mach number and wall temperature on the flow and surface
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Sparse identification of nonlinear unsteady aerodynamics of the oscillating airfoil Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-09-23 Chong Sun; Tian Tian; Xiaocheng Zhu; Zhaohui Du
Reduced-order models are widely used in aerospace engineering. A model for unsteady aerodynamics is desirable for designing the blades of wind turbines. Recently, sparse identification of nonlinear dynamics with control was introduced to identify the parameters of an input-output dynamical system. In this paper, two models for attached flows and one for separated flows are identified through this technique
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The influence of yaw on the unsteady surface pressures over a two-wheeled landing-gear model Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-09-21 WR Graham; A Gatto
Landing-gear noise is an increasing issue for transport aircraft. A key determinant of the phenomenon is the surface pressure field. Previous studies have described this field when the oncoming flow is perfectly aligned with the gear. In practice, there may be a cross-flow component; here its influence is investigated experimentally for a generic, two-wheel, landing-gear model. It is found that yaw
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Experimental evaluation and numerical simulation of performance of the bypass dual throat nozzle Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-09-21 Mohammad Hadi Hamedi-Estakhrsar; Hossein Mahdavy-Moghaddam
Bypass dual throat nozzle (BDTN) is a modern concept of fluidic thrust vector control. This method able to solve the problem of thrust loss without need the secondary mass flow from other part of engine. Internal nozzle performance and thrust vector angles have been measured in the BDTN experimentally and numerically. A new simple approach is proposed to detect the thrust deflection angle. Numerical
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Fuel efficiency optimization of high-aspect-ratio aircraft via variable camber technology considering aeroelasticity Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-09-21 Liqiang Guo; Jun Tao; Cong Wang; Miao Zhang; Gang Sun
In this study, variable camber technology is applied to improve the fuel efficiency of high-aspect-ratio aircraft with aeroelasticity considered. The nonlinear static aeroelastic analyses are conducted for CFD/CSD (computational fluid dynamics/computational structural dynamics) numerical simulations. The RBF (radial basis function) method is adopted for the transmission of aerodynamic loads and structural
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Attitude control of nanosatellite with single thruster using relative displacements of movable unit Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. (IF 1.244) Pub Date : 2020-09-20 Anton V Doroshin; Alexander V Eremenko
The attitude dynamics of a nanosatellite (NS) with one movable unit changing its angular position relative to a main body of the nanosatellite is considered. This relative movability of the unit can be implemented with the help of flexible rods of variable length connecting the unit with the main body. Change of the relative position of the movable unit shifts the center of mass of the entire mechanical