Analysis and optimization of the coupling effect for duct-rotor based on aerodynamic performance

Wei, Wei; Tu, Jinghan; Ke, Zhifang; Wang, Ruolin; Xu, Bin

doi:10.1016/j.ast.2024.109200

Cited by 2 publications

(3 citation statements)

References 15 publications

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“…Therefore, the SST k-ω turbulence model is adopted, and in the numerical solution process, the secondorder upwind scheme finite volume method suitable for polyhedral grids and compressible fluids is employed. The convergence of the solution is evaluated using RMS (Root Mean Square) residuals, with a defined convergence criterion of 10 −5 for each variable [44,45]. Specific data for the computational domain settings can be found in Table 2:…”

Section: Grid Partitioning and Sensitivity Analysismentioning

confidence: 99%

“…And the mesh division of the computational domain is shown in Figure 5. [44,45]. Specific data for the computational domain settings can be found in Table 2:…”

Section: Airfoil Type Clf5605mentioning

confidence: 99%

“…The aerodynamic performance of a rotor is generally explained by analyzing its lift coefficient C T , torque coefficient C Q , and lift-to-drag ratio C T /C Q . The expressions for these coefficients are shown as follows [45]:…”

Section: Aerodynamic Characteristics Analysismentioning

confidence: 99%

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Aerodynamic Hinge Moment Characteristics of Pitch-Regulated Mechanism for Mars Rotorcraft: Investigation and Experiments

Meng,

Hu,

Wei

et al. 2024

Drones

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The precise regulation of the hinge moment and pitch angle driven by the pitch-regulated mechanism is crucial for modulating thrust requirements and ensuring stable attitude control in Martian coaxial rotorcraft. Nonetheless, the aerodynamic hinge moment in rotorcraft presents time-dependent dynamic properties, posing significant challenges for accurate measurement and assessment for such characteristics. In this study, we delve into the detailed aerodynamic hinge moment characteristics associated with the pitch-regulated mechanism of Mars rotorcraft under a spectrum of control strategies. A robust computational fluid dynamics model was developed to simulate the rotor’s aerodynamic loads, accompanied by a quantitative hinge moment characterization that takes into account the effects of varying rotor speeds and pitch angles. Our investigation yielded a thorough understanding of the interplay between aerodynamic load behavior and rotor surface pressure distributions, leading to the creation of an empirical mapping model for hinge moments. To validate our findings, we engineered a specialized test apparatus capable of measuring the hinge moments of the pitch-regulated mechanism, facilitating empirical assessments under replicated atmospheric conditions of both Earth and Mars. The result indicates aerodynamic hinge moments depend nonlinearly on rotational speed, peaking at a 0° pitch angle and showing minimal sensitivity to pitch under 0°. Above 0°, hinge moments decrease, reaching a minimum at 15° before rising again. Simulation and experimental comparisons demonstrate that under Earth conditions, the aerodynamic performance and hinge moment errors are within 8.54% and 24.90%, respectively. For Mars conditions, errors remain below 11.62%, proving the CFD model’s reliability. This supports its application in the design and optimization of Mars rotorcraft systems, enhancing their flight control through the accurate prediction of aerodynamic hinge moments across various pitch angles and speeds.

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Section: Grid Partitioning and Sensitivity Analysismentioning

confidence: 99%

“…And the mesh division of the computational domain is shown in Figure 5. [44,45]. Specific data for the computational domain settings can be found in Table 2:…”

Section: Airfoil Type Clf5605mentioning

confidence: 99%