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| 1 | Crashworthiness uncertainty analysis of typical civil aircraft based on Box–Behnken method显示文摘The crashworthiness is an important design factor of civil aircraft related with the safety of occupant during impact accident. It is a highly nonlinear transient dynamic problem and may be greatly influenced by the uncertainty factors. Crashworthiness uncertainty analysis is conducted to investigate the effects of initial conditions, structural dimensions and material properties. Simplified finite element model is built based on the geometrical model and basic physics phenomenon. Box–Behnken sampling and response surface methods are adopted to obtain gradient information.Results show that the proposed methods are effective for crashworthiness uncertainty analysis.Yield stress, frame thickness, impact velocity and angle have great influence on the failure behavior,and yield stress and frame thickness dominate the uncertainty of internal energy. Failure strain and tangent modulus have the smallest influence on the initial peak acceleration, and gradients of mean acceleration increase because the appearance of material plastic deformation and element failure. | Ren Yiru Xiang Jinwu | 2014 | Chinese Journal of Aeronautics2014，27，3： | 3 |
| 2 | A novel trajectory planning strategy for aircraft emergency landing using Gauss pseudospectral method显示文摘To improve the survivability during an emergency situation, an algorithm for aircraft forced landing trajectory planning is proposed. The method integrates damaged aircraft modelling and trajectory planning into an optimal control framework. In order to deal with the complex aircraft flight dynamics, a solving strategy based on Gauss pseudospetral method(GPM) is presented.A 3-DOF nonlinear mass-point model taking into account the wind is developed to approximate the aircraft flight dynamics after loss of thrust. The solution minimizes the forced landing duration, with respect to the constraints that translate the changed dynamics, flight envelope limitation and operational safety requirements. The GPM is used to convert the trajectory planning problem to a nonlinear programming problem(NLP), which is solved by sequential quadratic programming algorithm. Simulation results show that the proposed algorithm can generate the minimum-time forced landing trajectory in event of engine-out with high efficiency and precision. | Shaohua MENG Jinwu XIANG Zhangping LUO Yiru REN Nanjian ZHUANG | 2014 | Control Theory and Technology2014，12，4： | 2 |
| 3 | Topology optimization design of micro-mass sensors for maximizing detection sensitivity显示文摘Micro-mass sensors have attracted increasing attention in the fiel of biomolecular and chemical detection. It has been found that the size, shape, and geometry of the structure may affect the performance of the sensor. As a result, a topology optimization methodology is proposed in this paper for the design of micro-mass sensors. A phasefiel function controlled by nodal variables and finit element shape functions is used to describe the configuratio of a sensor in the constructed optimization problem. The design goal is to maximize the mass detection sensitivity. On the basis of these formulations, an optimization algorithm is constructed using the finit element method and the method of moving asymptotes. Numerical examples are presented to demonstrate the validity of the proposed problem formulation. The results suggest that the performance of the micro-mass sensor can be improved by using the proposed approach. | Zheqi Lin Xuansheng Wang Yiru Ren | 2015 | Acta Mechanica Sinica2015，31，4： | 1 |
| 4 | A comparative study of the crashworthiness of civil aircraft with different strut configurations 显示文摘 | REN YiRu XIANG JinWu | 2010 | International Journal of Crashworthiness2010，15，3： | 1 |
| 5 | Crashworthiness analysis of aircraft fuselage with sine-wave beam structure显示文摘An integrated design concept for crashworthy fuselage using sine-wave beam and strut is proposed and investigated. The finite element model of aircraft fuselage is built first. The structures above cabin floor, occupant and seat are simplified as two rigid blocks. The fuselage frame is redesigned, and the sine-wave beam is arranged under the frame. The impact dynamic performance of the aircraft with bottom sine-wave beam structure is studied and compared with that of conventional type. To obtain better crashworthiness performance, different rigidity of strut is combined with the sine-wave beam bottom structure. Numerical simulation result shows that the proposed sine-wave beam bottom structure could not only dissipate more proportion of impact kinetic energy but also reduce the initial peak acceleration. The structure and rigidity of strut have great influence on the crashworthiness performance. To give a better fuselage structure, both of the strut and bottom structure should be properly integrated and designed. | Ren Yiru Xiang Jinwu Zheng Jianqiang Luo Zhangping | 2016 | Chinese Journal of Aeronautics2016，29，2： | 1 |
| 6 | Core reinforcement design for improving flexural energy-absorption of corrugated sandwich composite structure显示文摘To strengthen Specific Energy-Absorption(SEA)behavior of Sandwich Composite Structure(SCS),a kind of light-weight vertical stiffener is proposed for the corrugated core.The vertical stiffener,embedded in the corrugated core,can not only absorb part of energy but also simultaneously enhance Energy-Absorption(EA)of other components.The Hashin damage model considering the shear stress and ductile damage model is adopted to predict the failure of carbon fiber face-sheets and aluminum-core,respectively.The perfect bonding is modeled for interfaces between the face-sheet and core due to little realistic debonding.The finite element model is verified by available data of conventional SCS.To obtain more design ideas,several stiffeners with different thicknesses,numbers,and positions are investigated.From the predicted results,both the flexural load and deformation of SCS correlate well with experimental results.It is highlighted that the SCSs with different vertical stiffeners exhibit 9.74%-58.48%higher SEA than the SCS without stiffener.The complex reinforcement mechanisms are extensively revealed by underlying coupling EA and deformation mechanisms.Structural parameter analysis shows that the thickness and number have significant effects on the flexural behavior and SEA of reinforced SCS. | Yiru REN Yabin DENG Hongyong JIANG | 2021 | Chinese Journal of Aeronautics2021，34，5： | 1 |
| 7 | Topology optimization of piezocomposite resonator for maximizing excitation strength and synthesizing desired eigenmodes显示文摘A topology optimization method is proposed for the design of piezocomposite resonator with the aim of maximizing excitation strength and synthesizing desired eigenmodes.The objective function consists of maximizing the electromechanical coupling strength at the mode of interest.The topology layout of a structure with desired eigenmodes is obtained by adding the modal assurance criterion as additional constraint in the topology optimization model.Numerical examples are presented and the results illustrate that aside from maximizing the electromechanical coupling strength,the existing eigenmode of the piezocomposite resonator can be modified to be the desired one at the mode of interest. | Xuansheng Wang Zheqi Lin Yiru Ren | 2017 | Acta Mechanica Solida Sinica2017，30，5： | 0 |
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