Effect of elastic deformation on the aerodynamic characteristics of a high-speed spinning projectile

Yin, Jintao; Lei, Juanmian; Wu, Xinping; Liu, Tingting

doi:10.1016/j.ast.2015.05.019

Cited by 9 publications

(4 citation statements)

References 36 publications

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“…Four factors are selected for comparative analysis and there are three levels for each factor. So, 3 4 = 81 times CFD simulation should be calculated for an all-factors comparison. If the all-factors comparison is analyzed in subsonic, transonic, and supersonic conditions, there need to be 81 3 3 = 243 times CFD simulations at least, and that means a lot of time.…”

Section: Design Of Simulation Combination Schemementioning

confidence: 99%

“…Compared with the above methods, CFD is the kind of simulation method by which we can intuitively get the distribution of the flow field, and for the reasons that the process is simple and the results reliable and accurate, it is widely used for aerodynamic parameter calculations of guided projectiles, resulting in it becoming a hot area of aerodynamic research. For example, the CFD simulation has been used for the aerodynamic characteristic study of the spin-stabilized artillery shell by Hamel and Gagnon, 1 Je et al, 2 Fu et al, 3 and Yin et al, 4 used for the aerodynamic characteristic study of the fin-stabilized rocket by Afzal et al, 5 Sahu,6 Zhimin et al, 7 Sahu et al, 8 Zhang et al, 9 and López et al, 10 and used for the aerodynamic characteristic study of the mortar projectile by Su et al, 11 Li et al, 12 and Chengen et al 13 Most of the CFD simulations that are used for aerodynamic characteristic studies on projectiles, are focused on the effect of geometry on the aerodynamic parameter. The contrastive analysis of the CFD simulation method is relatively less.…”

Section: Introductionmentioning

confidence: 99%

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Investigation of the aerodynamic parameters simulation method of a guided rocket

Chen

Gao

2017

SIMULATION

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Orthogonal design method is adopted to investigate the aerodynamic parameters simulation method of a canard guided rocket, in order to obtain one simulation method which can calculate the aerodynamic parameters quickly, reliably, and accurately. The turbulence model, mesh size, y + value and flow field size, which are regarded as the main factors in computational fluid dynamics (CFD) simulation, are divided into three levels for comparative analysis. Nine simulation combination schemes, which are representative and comprehensive, are singled out based on orthogonal table. The axial force coefficient and normal force coefficient in subsonic, transonic, and supersonic conditions are respectively calculated with these nine simulation combination schemes. The best simulation combination schemes in subsonic, transonic, and supersonic conditions are respectively picked out by intuitive analysis and synthesis balance analysis. The aerodynamic parameters in different velocities and attack angles, which were obtained by corresponding best simulation combination schemes, prove that the best simulation combination schemes are accurate. The results provide basis for the aerodynamic characteristic study of the canard guided rocket, and this research method can be used for the investigation on aerodynamic parameters simulation method of projectiles with different configurations.

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Section: Design Of Simulation Combination Schemementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Investigation of the aerodynamic parameters simulation method of a guided rocket

Chen

Gao

2017

SIMULATION

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“…The aerodynamic and structural characteristics were respectively obtained by the Euler equation and the modal superposition method. Other numerical studies have predominantly explored the influence of aeroelasticity on the flight and control performance of projectiles [19][20][21][22][23][24][25][26]. In summary, previous investigations have encountered challenges in conducting two-way fluid-structure interaction calculations due to the intricate nature of the dynamic processes involved in spinning projectiles.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Response of Spinning Projectiles with Large Slenderness Ratio at Supersonic Speed

Liu

Lei

et al. 2023

Aerospace

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Obvious aeroelastic deformation occurs in spinning projectiles with large slenderness ratio, which seriously affects flight stability and maneuverability. This paper investigates the aeroelastic response of spinning projectiles with large slenderness ratio under supersonic speed. Based on a dynamic mesh method, an unsteady numerical simulation method is developed to study the aeroelasticity of spinning projectiles by coupling aerodynamics and structural dynamics. The numerical simulation method is well validated by the experimental results of AGARD 445.6 wing flutter. Then, the aeroelastic response of spinning projectiles with large slenderness ratio is numerically explored under different flight conditions. The aeroelastic response is obtained, revealing the presence of beat vibrations and variations in response frequency. Furthermore, the influence mechanism of flight conditions on the aeroelastic response is analyzed. The results suggest that the coupling of the first two modes of the projectile caused by the spinning motion leads to the occurrence of beat vibrations in the aeroelastic response; the coupling degree of the first two modes decreases as the angle of attack increases and it increases with the increase in spinning speed; and the time−averaged deformation caused by the time−averaged aerodynamic force is beneficial to the convergence of the aeroelastic response of spinning projectiles, while the rotation−induced Magnus effect is counterproductive.

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“…However, since the wind effects, spin effects [18] and time-varying aerodynamic coefficients [29] always exist in the ballistic process dynamics, the exact model of the process is always unavailable. Moreover, under the nonlinear air resistance, the analytic solution is unavailable and the solution can be only got by numerical calculation or approximate methods [5,19,22].…”

Section: Introductionmentioning

confidence: 99%

Initial states iterative learning for three-dimensional ballistic endpoint control

et al. 2016

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In this paper, an initial states iterative learning control algorithm is proposed for control of the ballistic endpoint displacement in three-dimensional space, where the target is moving and the projectile experiences system uncertainties. The characteristics of the three-dimensional ballistic process are formulated and explored, and the learning algorithm is proposed in the spatial domain. The algorithm consists of two parts. First, the initial speed and angles are iteratively learned to make the projectile attain a fixed position. Second, the shooting time is learned to tune the arrival time of the projectile. Since the dimensions of the solution space are larger than that of the task space, three control manners, including shooting speed, shooting angle and their combination, are researched respectively. Through rigorously analyzed, it is proved that the algorithm is convergent and the multiple initial states can be adjusted simultaneously. Finally, an example of practical cannonball projection is presented to verify the effectiveness of the proposed algorithms.

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Effect of elastic deformation on the aerodynamic characteristics of a high-speed spinning projectile

Cited by 9 publications

References 36 publications

Investigation of the aerodynamic parameters simulation method of a guided rocket

Investigation of the aerodynamic parameters simulation method of a guided rocket

Aeroelastic Response of Spinning Projectiles with Large Slenderness Ratio at Supersonic Speed

Initial states iterative learning for three-dimensional ballistic endpoint control

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