Unsteady aerodynamics investigation of deploying tandem-wing with different methods

Cheng, Hongtai; Wang, Hua; Shi, Qingli; Zhang, Mengying

doi:10.1177/0954410018804737

Cited by 3 publications

(5 citation statements)

References 42 publications

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“…Cheng et al investigated the unsteady aerodynamics in the morphing stage of a tandem-wing UAV by using the improved vortex lattice method. This research confirmed that the vortex-lattice method can accurately predict the unsteady aerodynamic performance [12]. Besides, the same team also proposed a method of predicting the lift coefficient of tandem-wing aircraft systems based on Prandtl's lifting-line theory [13].…”

Section: Introductionsupporting

confidence: 59%

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An Adaptive Sequential Sampling Strategy-Based Multi-Objective Optimization of Aerodynamic Configuration for a Tandem-Wing UAV via a Surrogate Model

et al. 2021

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Multi-objective optimization of aerodynamic configuration for a tandem-wing unmanned aerial vehicle (UAV) via a surrogate model is appropriate in the primary stages of aircraft design. This study presents an adaptive sequential sampling strategy, which takes into account the principle of entropy rank and selection pooling based on a sigmoid function (ESP), in order to save time and construct a surrogate model database with considerable approximation accuracy. The entire procedure of optimization is divided into four parts, involving problem formulation for design variables and objectives, database construction for the surrogate model, multi-objective optimization with the surrogate models, and ESP adaptive sequential sampling to update the database. Firstly, a comparative study of the different surrogate models is carried out to assess their approximation performance. This verifies that the radial basis function (RBF) surrogate model outperforms the other models across the board. Then, we conduct two tests with typical mathematical problems to validate the effectiveness and applicability of the proposed method. We also develop a multiobjective optimization of the aerodynamic configuration for a tandem-wing UAV, aiming to maximize the lifting coefficient at the ascent (C Lascent ) and the lift-drag ratio (K cruise ) during the cruise. In this case, the RBF surrogate model is proven more suitable than the other common methods to replace the real values calculated by the non-planar vortex-lattice method (VLM) during the process of optimization. Furthermore, a comparison with large minimal distance (LMD) sequential sampling and disposable Latin hypercube sampling (LHS) is carried out alongside the optimization. These results show that the approximation precision achieved using ESP strategy is greater, highlighting the superiority of the ESP adaptive sequential sampling strategy in reducing the number of samples and raising the approximation accuracy. Finally, after the refinement of the database, an optimal Pareto front set is obtained to guide the primary design of the aerodynamic configuration for the tandem-wing UAV. Then, it is verified that the selected trade-off optimal design point has a better aerodynamic performance than the initial reference point, improving C Lascent and K cruise by 6.44% and 10.85%, respectively.

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Section: Introductionsupporting

confidence: 59%

“…Xie data from the wind tunnel tests [37]. Our previous comparative work, which used CFD method, adequately validated the accuracy and capability of non-linear VLM when calculating aerodynamic characteristics for tandem-wing aircraft [11], [12]. The results are shown in Fig.…”

Section: ) Validation Of the Numerical Calculation Methodsmentioning

confidence: 58%

An Adaptive Sequential Sampling Strategy-Based Multi-Objective Optimization of Aerodynamic Configuration for a Tandem-Wing UAV via a Surrogate Model

et al. 2021

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“…Compared with results obtained by different methods proposed in the previous study, the VLM method is more accurate to calculate the unsteady aerodynamics during the deploying process. 48 In order to apply the boundary condition that the flow in the direction normal to the wing's surface is zero, on all the lifting surfaces, the wing's mean camber surfaces should be divided into trapezoidal elements on which the discrete vortex rings are placed. The leading-edge segment of each vortex ring coincides with the quarter chord line of the corresponding element, and the control point is set at the midpoint of the three-quarter chord line of the element.…”

Section: Aerodynamics Calculationmentioning

confidence: 99%

“…Besides, in our previous study, the VLM and the lifting-line method were proposed to calculate the unsteady aerodynamics of the tandem wing aircraft during its deploying process, and meanwhile, the effects of the layout parameters and the deformation rate were studied comprehensively. 48 After launching from the tube, the lifting surfaces deploy by rotating around a hinge axis perpendicular to the airframe axis. During the deploying process, swept angles of the fore and hind wing change until fully deployed.…”

Section: Introductionmentioning

confidence: 99%

Flight dynamics modeling and stability analysis of a tube-launched tandem wing aerial vehicle during the deploying process

Cheng

Shi

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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During the subsequent deploying process after the launch, the vehicle experiences dramatic changes in geometry as well as aerodynamics, which cannot be ignored for the flight stability of the aircraft. The investigation on the flight dynamics modeling and stability analysis during the unsteady deploying process is of great significance for the flight control system design and the launch system design. The nonlinear multibody dynamic model of the vehicle, which mainly consists of the airframe and four wings, is established through the Newton–Euler method. Meanwhile, the unsteady vortex lattice method (VLM), which is suitable for tandem wing aircraft and combined with the viscosity effect in light of the strip theory, is proposed to calculate the aerodynamic loads of the vehicle during the deploying process. A series of simulations about the motion of the vehicle after the launch are calculated to analyze the effects of various parameters, including the deploying forms, the start-up time of the power system along with the launching parameters, on the stability of the aerial vehicle in the deployment process. As results indicated, a small difference in the deploying rates of wings and larger deploying rates of wings on the same side are beneficial to the stability of the vehicle during the deploying process. Additionally, it is advantageous to the pitching stability but not the lateral stability of the vehicle when the power system is started earlier. Besides, the attitude control strategy of the vehicle can be formulated in advance by analyzing the attitude of the vehicle with different launch parameters at the launching moment.

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“…Figure 4(c) shows the mesh generated for the present study, and most region is filled with structured mesh for good converging speed. 33 The meshes are refined in the region where shock waves and fierce evaporation occur to capture the discontinuity through shocks and mass transfer, which is marked by red oval. Note that the ozx plane and the oyz plane are the most representative profiles inside a silo.…”

Section: Computational Modelmentioning

confidence: 99%

Transient influence of water injection on the flow field of a hot launch in a W-shaped silo

Shi

Jiang

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study attempts to determine the effect of and mechanisms for the suppression of the ignition pressure and back-flowing exhaust during a hot launch process in a W-shaped silo, considering the missile movement via dynamic mesh technology. The mixture model for the multiphase and the turbulent model employed were experimentally proved to be accurate and reliable. The numerical results show that the injection of water into a missile exhaust can effectively suppress the ignition overpressure, thereby reducing the time of oscillation and oscillation amplitude, and reducing the maximum pressure at missile bottom from 3.68 × 105 Pa to 2.39 × 105 Pa. In addition, water injection makes the back-flowing exhaust remain at the bottom of the launch duct instead of filling the duct, and it cools the missile bottom, thus leading to a reduction in the maximum temperature from 3000 K to approximately 500 K.

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Unsteady aerodynamics investigation of deploying tandem-wing with different methods

Cited by 3 publications

References 42 publications

An Adaptive Sequential Sampling Strategy-Based Multi-Objective Optimization of Aerodynamic Configuration for a Tandem-Wing UAV via a Surrogate Model

An Adaptive Sequential Sampling Strategy-Based Multi-Objective Optimization of Aerodynamic Configuration for a Tandem-Wing UAV via a Surrogate Model

Flight dynamics modeling and stability analysis of a tube-launched tandem wing aerial vehicle during the deploying process

Transient influence of water injection on the flow field of a hot launch in a W-shaped silo

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