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Integrated method of guidance,control and morphing for hypersonic morphing vehicle in glide phase 被引量:24
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作者 Cunyu BAO Peng WANG Guojian 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2021年第5期535-553,共19页
The morphing technology of hypersonic vehicle improved the flight performance by changing aerodynamic characteristics with shape deformations,but the design of guidance and control system with morphing laws remained t... The morphing technology of hypersonic vehicle improved the flight performance by changing aerodynamic characteristics with shape deformations,but the design of guidance and control system with morphing laws remained to be explored.An Integrated of Guidance,Control and Morphing(IGCM)method for Hypersonic Morphing Vehicle(HMV)was developed in this paper.The IGCM method contributed to an effective solution of morphing characteristic to improve flight performance and reject the disturbance for guidance and control system caused by the morphing system for HMV in gliding phase.The IGCM models were established based on the motion models and aerodynamic models of the variable span vehicle.Then the IGCM method was designed by adaptive block dynamic surface back-stepping method with stability proof.The parallel controlled simulations’results showed the effectiveness in accomplishing the flight mission of IGCM method in glide phase with smaller terminal errors.The velocity loss of HMV was reduced by 32.8%which inferred less flight time and larger terminal flight velocity than invariable span vehicle.Under the condition of large deviations of aerodynamic parameters and atmospheric density,the robustness of IGCM method with variable span was verified. 展开更多
关键词 Adaptive dynamic surface Glide phase Hypersonic morphing vehicle Integrated guidance control and morphing method Variable span
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Combined Size and Shape Optimization of Structures with DOE,RSM and GA 被引量:1
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作者 Jie Song Hongliang Hua +2 位作者 Zhenqiang Liao Tao Wang Ming Qiu 《Journal of Beijing Institute of Technology》 EI CAS 2018年第2期267-275,共9页
In this paper,size and shape optimization problem of a machine gun system is addressed with an efficient hybrid method,in which a novel and flexible mesh morphing technique is employed to achieve fast parameterization... In this paper,size and shape optimization problem of a machine gun system is addressed with an efficient hybrid method,in which a novel and flexible mesh morphing technique is employed to achieve fast parameterization and modification of complexity structure without going back to CAD for reconstruction of geometric models or to finite element analysis( FEA) for remodeling. Design of experiments( DOE) and response surface method( RSM) are applied to approximate the constitutive parameters of a machine gun system based on experimental tests. Further FEA,secondary development technique and genetic algorithm( GA) are introduced to find all the optimal solutions in one go and the optimal design of the demonstrated machine gun system is obtained. Results of the rigid-flexible coupling dynamic analysis and exterior ballistics calculation validate the proposed methodology,which is relatively time-saving,reliable and has the potential to solve similar problems. 展开更多
关键词 finite element method(FEA) shape optimization mesh morphing response surface method(RSM) design of experiments(DOE) rigid-flexible coupling machine gun system
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A new non-linear vortex lattice method:Applications to wing aerodynamic optimizations 被引量:7
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作者 Oliviu Sugar Gabor Andreea Koreanschi Ruxandra Mihaela Botez 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2016年第5期1178-1195,共18页
This paper presents a new non-linear formulation of the classical Vortex Lattice Method (VLM) approach for calculating the aerodynamic properties of lifting surfaces. The method accounts for the effects of viscosity... This paper presents a new non-linear formulation of the classical Vortex Lattice Method (VLM) approach for calculating the aerodynamic properties of lifting surfaces. The method accounts for the effects of viscosity, and due to its low computational cost, it represents a very good tool to perform rapid and accurate wing design and optimization procedures. The mathematical model is constructed by using two-dimensional viscous analyses of the wing span-wise sections, according to strip theory, and then coupling the strip viscous forces with the forces generated by the vortex rings distributed on the wing camber surface, calculated with a fully three-dimensional vortex lifting law. The numerical results obtained with the proposed method are validated with experimental data and show good agreement in predicting both the lift and pitching moment, as well as in predicting the wing drag. The method is applied to modifying the wing of an Unmanned Aerial System to increase its aerodynamic efficiency and to calculate the drag reductions obtained by an upper surface morphing technique for an adaptable regional aircraft wing. 展开更多
关键词 Aerodynamic design Aerodynamic optimization Enhanced potential method morphing wing Nonlinear vortex latticemethod Quasi-3D aerodynamic method UAS optimization
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Transient aeroelastic responses and flutter analysis of a variable-span wing during the morphing process 被引量:10
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作者 Huang Ren Qiu Zhiping 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2013年第6期1430-1438,共9页
To investigate the transient aeroelastic responses and flutter characteristics of a variablespan wing during the morphing process,a novel frst-order state-space aeroelastic model is proposed.The time-varying structura... To investigate the transient aeroelastic responses and flutter characteristics of a variablespan wing during the morphing process,a novel frst-order state-space aeroelastic model is proposed.The time-varying structural model of the morphing wing is established based on the Euler-Bernoulli beam theory with time-dependent boundary conditions.A nondimensionalization method is used to translate the time-dependent boundary conditions to be time-independent.The time-domain aerodynamic forces are calculated by the reduced-order unsteady vortex lattice method.The morphing parameters,i.e.,wing span length and morphing speed,are of particular interest for understanding the fundamental aeroelastic behavior of variable-span wings.A test case is proposed and numerical results indicate that the flutter characteristics are sensitive to both of the two morphing parameters.It could be noticed that the aeroelastic characteristics during the wing extracting process are more serious than those during the extending process at the same morphing speed by transient aeroelastic response analysis.In addition,a faster morphing process can get better aeroelastic performance while the mechanism comlexity will arise. 展开更多
关键词 Galerkin methods morphing aircraft Time-varying systems Transient aeroelastic Unsteady vortex lattice method Variable-span wing
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