Study on flight dynamics of flexible projectiles based on closed-loop feedback control

Hua, Ruhao; Yuan, Xianxu; Tang, Zhigong; Ye, Zhengyin

doi:10.1016/j.ast.2019.04.038

Cited by 15 publications

(4 citation statements)

References 13 publications

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“…It should be noted that there are slight differences in the definitions of nondimensional dynamic pressure and frequency between the two studies. The non-dimensional dynamic pressure and frequency are defined as λ ¼ 2ql 3 =D ffiffiffiffiffiffiffiffiffiffiffiffiffiffiffi M 2 À 1 p and K f ¼ ωðρ m hl 4 =DðÞ 1=2 Þ by Dowell, while the nondimensional dynamic pressure and frequency are defined as λ visbal ¼ 2ql 3 =D and St ¼ fl=u ∞ by Visbal. ω is the angular flutter frequency calculated by ω ¼ 2πf , where f is the flutter frequency.…”

Section: Verificationmentioning

confidence: 99%

“…The aeroelastic problems related to shock-induced panel flutter have raised increasing attention in the development of the next generation's supersonic/hypersonic aircraft. 1,2 The combination of lightweight thin-walled panels and severe aerothermodynamic conditions encountered in the hypersonic flow may lead to an unstable structural response, 3 which is known to cause fatigue damage to flight vehicles. Panel flutter is relatively well understood in its traditional form, whereas the mechanism of panel flutter induced by shock impingement remains ambiguous.…”

Section: Introductionmentioning

confidence: 99%

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Mechanism of characteristic change of panel flutter caused by oblique shock impingement

Meng,

Ye,

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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Compared to the shock-free condition, the weak shock impingement stabilizes the flexible panel, while the strong shock impingement leads to the early onset of panel flutter with a significant increase in flutter amplitude and frequency. However, the reason for this change by shock impingement remains unclear. The current research examines the mechanism of this change by an in-house code where the von Kármán’s large deflection plate theory is coupled with two-dimensional Euler equations. Compared to the shock-free condition, the oblique shock impingement leads to the change of local dynamic pressure on the panel as well as the static pressure differential across the panel. The analysis on the influence of these changes indicates that, on the one hand, the average dynamic pressure on the panel becomes larger than the shock-free condition, accelerating the onset of panel flutter. On the other hand, the change of the static pressure differential across the panel alters the coupling characteristic between different natural frequencies (modes) of the panel structure. The dynamic response of panel flutter under shock impingements is dominated by the coupling between the second and third modes instead of the first two modes for panel flutter under the shock-free condition. The combined effect of these two changes leads to the change of flutter characteristics of the panel under shock impingement. These findings provide valuable insights into the mechanism of shock-induced panel flutter.

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Section: Verificationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Mechanism of characteristic change of panel flutter caused by oblique shock impingement

Meng,

Ye,

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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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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“…Also, the study investigates the flying quality of the proposed design as well as gust response [26]. Additionally, there are plenty of studies that investigate the effects of the aeroelastic behavior of the control surfaces on the flight dynamics such as [27,28]. But these are prevalent for high-speed regime air vehicles, so they are not the case for the subsonic general aviation aircraft.…”

Section: Introductionmentioning

confidence: 99%

Stick-free Flight Stability Problem Revisited: A Modeling and Simulation Approach

Altunkaya¹,

OZKOL²

2022

Preprint

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The stick-free flight stability is an old-fashioned and non-progressive issue; nevertheless, it is still existent, and of significant importance to the design of aircraft whose control system is reversible. The problem’s existence necessitates a deep assessment of stick-free flight stability throughout the aircraft design. Up to now, this problem has been addressed using either analytical approaches, which are only related to the static stability evaluation, or performing flight tests. In this study, the problem is handled in its entirety, from static and dynamic flight stability assessment to design criteria with a comprehensive perspective. Moreover, it is also exhibited that contrary to what has been generally proposed in the literature, limiting the problem of stick-free flight stability through static stability assessment is far from the main challenge. As a brief scope, the derivation of the control surface dynamics, a stick-free trim algorithm, and assessment rationale of the stick-free static and dynamic flight stability using a simulation approach are proposed. As a consequence, the aim is to set a broad understanding for designers related to this phenomenon and add adjunct design criteria in the design optimization process by approaching it in terms of modeling, simulation, and flight test perspective.

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Study on flight dynamics of flexible projectiles based on closed-loop feedback control

Cited by 15 publications

References 13 publications

Mechanism of characteristic change of panel flutter caused by oblique shock impingement

Mechanism of characteristic change of panel flutter caused by oblique shock impingement

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

Stick-free Flight Stability Problem Revisited: A Modeling and Simulation Approach

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