Doublet-Lattice Method Correction by Means of Linearised Frequency Domain Solver Analysis

Valente, Carmine; Jones, Dorian P; Gaitonde, Ann L; Cooper, Jonathan E.; Lemmens, Yves

doi:10.2514/6.2016-1575

Cited by 5 publications

(5 citation statements)

References 9 publications

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“…Doublet lattice method 22 was effective for engineering flutter analysis, and the main code had been involved in the commercial software ZAERO. The related plane aerodynamic grid for the present system including a tail cabin and six all-movable rudders is shown in Figure 13.…”

Section: Flutter Analysismentioning

confidence: 99%

Experimental and numerical study of dynamic characteristic of a complex all-movable rudder system

Bai

Qian

Chen

et al. 2017

Journal of Low Frequency Noise, Vibration and Active Control

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Modal analysis and flutter computation of a complex tail cabin system including six all-movable rudders for hypersonic flight vehicle was studied in this paper. Recently, some complex all-movable rudder system has been applied to hypersonic flight vehicle. Many investigations were taken to analyse a single all-movable rudder, such as modal analysis, flutter analysis, aero-heating analysis, etc. But most of existing investigations emphasized on single rudder. In this paper, a complex tail cabin system including six all-movable rudders from the X-51A vehicle was investigated. Modal analysis was presented based on accurate finite element modelling and bending and twisting modes of the structure were computed. Ground vibration test was provided to confirm the accuracy of computation. Then flutter characteristic of this complex system was analysed based on doublet lattice method. With flight Mach number 3 and 4, flutter analysis relating to both symmetric mode and antisymmetric mode was presented. It can be found from the presented results of flutter analysis that there were obvious and non-negligible coupling vibration effects among rudders in such a complex rudder system. So flutter characteristic of hypersonic flight vehicle should be analysed based on the whole system modelling including all of rudders. This analysis process can play a significant role for the design and flight of hypersonic vehicle.

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Section: Flutter Analysismentioning

confidence: 99%

Experimental and numerical study of dynamic characteristic of a complex all-movable rudder system

Bai

Qian

Chen

et al. 2017

Journal of Low Frequency Noise, Vibration and Active Control

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“…The flutter of a flying wing is a phenomenon of aeroelastic dynamic instability triggered by the coupling of elastic structural dynamics and nonconstant aerodynamics. According to the theory of vibration [11][12][13][14], the equations of motion of the aeroelastic system under the discrete system can be derived:…”

Section: Flutter Analysismentioning

confidence: 99%

“…A P-K method based on the above equations is a commonly used method to solve the flutter problem [17], and this paper used this method to analyze flutter of the present model. The fundamental equation for modal flutter analysis by the PK-method is (11) where B is the modal damping matrix, and this term is not considered in this paper; and are the modal aerodynamic damping matrix and the modal aerodynamic stiffness matrix, respectively, both as a function of Mach number Ma and the reduced frequency k. The damping term is not considered in this paper; p denotes the eigenvalue;c, ρ and V are the reference length, fluid density and velocity, respectively; {u} is the modal amplitude vector.…”

Section: Flutter Analysismentioning

confidence: 99%

Flutter Modelling and Computation of a Flying Wing Aircraft

Bai

Zhang

2022

JERR

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Flying wing aircraft has many encouraging advantages, but there still were many unsteady aerodynamic uncertainty of the structures. Dynamic stability is a most significant analysis object. This paper wants to propose the flutter characteristic of a real flying wing aircraft. Firstly, an efficient finite element modelling method was taken to find basic dynamic features of the presented aircraft with effective mode analysis. Typical dynamic characteristics including bending and twisting modes of the structure were analyzed to propose possible dynamic stability of the aircraft. Secondly, a frequency domain fluid-structure interaction method was proposed to solve flutter analysis problem of the aircraft. With different heights and Ma number, flutter features of the aircraft were presented. It was seen from the computational results that dynamic stability analysis is necessary for the flying wing aircraft with proper flight velocity and height. The present dynamic modelling method and flutter computation process can give an effect reference for the design of flying wing aircraft. Also it can provide useful suggestions for existing flying wing aircraft structures.

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“…For low subsonic flight, panel codes based on unsteady vortex lattice methods [31] provide a means of rapid assessment of highaltitude long-endurance aircraft. On the other hand, tools designed for high Mach number cases range from corrected doublet lattice method [39] (typically used in the loads estimations process in industry) to computationally expensive unsteady computational fluid dynamics (CFD) simulations of the whole aircraft [20]. When deployed in areas of the flight envelope where these tools are valid, designers and engineers have gained significant insight on aircraft aerodynamic performance.…”

Section: Introductionmentioning

confidence: 99%

Verification of a low fidelity fast simulation framework through RANS simulations

et al. 2019

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Verification and validation of simulation models are critical steps in engineering. This paper aims at verifying the suitability of reduced order aerodynamic models used in an aeroservoelastic framework designed to analyze the flight dynamics of flexible aircraft, known as the Cranfield Accelerated Aircraft Loads Model. This framework is designed for rapid assessment of aircraft configurations at the conceptual design stage. Therefore, it utilizes or relies on methods that are of relatively low fidelity for high computational speeds, such as modified strip theory coupled with Leishmann-Beddoes unsteady aerodynamic model. Hence, verification against higher order methods is required. Although low fidelity models are widely used for conceptual design and loads assessments, the open literature still lacks a comparison against higher fidelity models. This work focuses on steady-trimmed flight conditions and investigates the effect of aerodynamic wing deformation under such loads on aerodynamic performance. Key limitations of the reduced order models used, namely fuselage and interference effects, are discussed. The reasons for the overall agreement between the two approaches are also outlined.

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Doublet-Lattice Method Correction by Means of Linearised Frequency Domain Solver Analysis

Cited by 5 publications

References 9 publications

Experimental and numerical study of dynamic characteristic of a complex all-movable rudder system

Experimental and numerical study of dynamic characteristic of a complex all-movable rudder system

Flutter Modelling and Computation of a Flying Wing Aircraft

Verification of a low fidelity fast simulation framework through RANS simulations

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