Effect of elastic deformation on flight dynamics of projectiles with large slenderness ratio

Hua, Ruhao; Ye, Zhengyin; Wu, Jie

doi:10.1016/j.ast.2017.09.029

Cited by 29 publications

(9 citation statements)

References 20 publications

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“…The code has been verified by many aeroelastic problems [32,33]. Table 6 and Figure 8 illustrate that the computational results show a good agreement with those of the reference and experimental data.…”

Section: Computational Resultsmentioning

confidence: 57%

Static Aeroelastic Modeling and Rapid Analysis of Wings in Transonic Flow

Yang

Liu

Zhang

2018

International Journal of Aerospace Engineering

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A fast static aeroelastic analysis method, coupling with the modal method and Kriging surrogate model, is proposed in this paper. The deflection of the wing is described by the modal method, and the Kriging surrogate model is utilized to model the generalized forces under different deformations, angles of attack, and Mach numbers in order to replace the CFD solver. We analyzed the static aeroelasticity of HIRENASD wing in transonic flow field by coupling with the generalized force model by the static equilibrium equation. The results were compared with those of the experimental data and the references, and the comparison shows that the method is useful for the small deflections. After enough training cases are finished, the high-accuracy aerodynamic force coefficients and wing deflection will be obtained rapidly, which will only take several seconds. This method is more time saving than the CFD/CSD method, when it comes to a large quantity of the static aeroelastic analyses. Hence, it has good perspective for engineering applications during the aircraft design period.

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Section: Computational Resultsmentioning

confidence: 57%

Static Aeroelastic Modeling and Rapid Analysis of Wings in Transonic Flow

Yang

Liu

Zhang

2018

International Journal of Aerospace Engineering

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“…More details about the numerical methods of CFD, the chimera mesh technique, and the mesh deformation technique of the in-house code can be found in Hua and Ye 19 and Hua et al. 20…”

Section: Computational Algorithm Of Trimming Analysismentioning

confidence: 99%

“…Since the displacement due to the elastic deformation is much smaller than the characteristic length of the projectile, the centroid position and the moments of inertia are assumed to be constant during the flight process, which has been validated in Hua et al. 20…”

Section: Computational Modelmentioning

confidence: 99%

Trimming analysis of flexible aircrafts based on computational fluid dynamics/computational structural dynamics coupling methodology

Hua

Chen

Yuan

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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A numerical methodology based on the coupling of computational fluid dynamics (CFD) and computational structural dynamics is established to obtain the trimming characteristics of flexible aircrafts in this paper. Reynolds-averaged Navier–Stokes equations are solved through CFD technique. Based on the frame of unstructured mesh, techniques of dynamic chimera mesh and morphing mesh are adopted to treat the data transfer between different computational zones and structure deformation caused by aeroelasticity, respectively. When it is applied to a projectile model with large slenderness ratio constructed in this paper, convergence histories of various initial conditions demonstrate the efficiency and robustness of the algorithm. The influence of the structural rigidity and normal loads on the trimming condition of flexible projectiles is investigated, and the locations of the aerodynamic center with various rigidities present the explanation that elastic deformation can move the aerodynamic center forward and weaken the margin of the stability. Furthermore, the trimming condition of flexible projectiles with propulsion is researched, which indicates that thrust misalignment will increase the effect of elastic deformation on the trimming condition, and the stability margin will be further weakened because of thrust misalignment. The conclusion provided in this paper can provide guidance for the structural design, control system design, and stability analysis for modern aircrafts with small stability margin and low rigidity.

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“…Although the force due to the aerothermoelastic effect on the jet interference is much less than the engine thrust, its force arm is significantly greater than that of the engine thrust. The pitching moment generated by the jet interference can bring considerable moment compared with that generated by the engine thrust, even comparable to the control ability, which can bring additional challenges to the aircraft control system [5,6].…”

Section: Introductionmentioning

confidence: 99%

Study on the Aerothermoelastic Characteristics of a Body Flap Considering the Nozzle–Jet Interference

Hua,

Chen,

Wan

et al. 2023

Aerospace

Self Cite

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A body flap/RCS-integrated configuration is often used to achieve pitch trimming and controlled flight in near space for hypersonic vehicles. Under the high temperature and pressure load induced by the expansion wave at the nozzle exit, the body flap is prone to significant structural deformation, which leads to a change in the resulting moment, even comparable to the control ability, and bring additional challenges to the control system. Based on the CFD/CTD/CSD coupling method, the aerothermoelastic effect on the aerodynamic characteristics and structural deformation of the body flap under jet interaction is systematically studied. Numerical results indicate that the pitching moment coefficients show an increasing trend for all the models, rigid, elastic and thermoelastic, while the increment significantly decreases with the increase in trajectory altitudes. With the increase in deflection angle, the pitching moment coefficients of the three models decrease nonlinearly at high altitude, and the aerothermoelastic effect significantly decreases. At a middle-lower altitudes, the pitching moment coefficient is reversed at a lager deflection angle, and the trailing edge of the body flap presents the deformation characteristics of upward bending, which makes the aerothermoelastic phenomenon degenerate into an aeroelastic problem. From the station along the chord and spanwise direction, the change in displacement increment of the thermoelastic model reflects the competitive relationship between normal stress and thermal stress imposed by jet interaction.

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Effect of elastic deformation on flight dynamics of projectiles with large slenderness ratio

Cited by 29 publications

References 20 publications

Static Aeroelastic Modeling and Rapid Analysis of Wings in Transonic Flow

Static Aeroelastic Modeling and Rapid Analysis of Wings in Transonic Flow

Trimming analysis of flexible aircrafts based on computational fluid dynamics/computational structural dynamics coupling methodology

Study on the Aerothermoelastic Characteristics of a Body Flap Considering the Nozzle–Jet Interference

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