Investigation of the Three-Dimensional Hinge Moment Characteristics Generated by the ONERA-M6 Wing with an Aileron

Zhang, G. Q.; Yu, S. C. M.; Chien, Aichi

doi:10.1155/2013/714168

Cited by 5 publications

(6 citation statements)

References 15 publications

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“…Characteristics for the zero angle of attack were determined, but for other angles of attack, the change in hinge moment is similar for particular configurations. As the deflecting angle increases, the hinge moments decrease (Zhang et al , 2013). It can be noted that the change in the hinge moment of the system is not dependent on the presence of an aileron slat in a non-sealed configuration.…”

Section: Resultsmentioning

confidence: 99%

“…Therefore, with the increase of the aileron area and the airspeed, the respective hinge moment can grow up. To complete the deflecting motion of the aileron by means of the control stick, more operating force will be needed (Zhang et al , 2013). To determine the characteristics of the hinge moment, it is necessary to specify the pressure distributions on the control surfaces.…”

Section: Introductionmentioning

confidence: 99%

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Impact of the aileron gap sealing on the aileron effectiveness

Kowalska

Goetzendorf‐Grabowski

2022

AEAT

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Purpose The purpose of the presented aileron modification analysis is the improvement of the flight handling by eliminating adverse phenomena in the aileron area, such as aileron shaking movements, without the risk of deterioration of flow characteristics during manoeuvres. It was also crucial to reduce aileron forces acting on the control stick. Design/methodology/approach Numerical CFD analysis of the aileron system with modifications of sealing in the aileron gap area were performed. The effect of the caulking strip at the upper surface of the aileron gap was determined, as well as caulking at the entrance to the aileron gap on the bottom surface. A solution has also been proposed, consisting of completely closing the aileron gap by using a diaphragm. The three-dimensional flow analysis was carried out, allowing localization of the flow disturbances in the aileron gap at cruising speed. The result of the analysis are the aerodynamic and the hinge moment coefficients determining forces on the control stick, depending on the type of seals. Findings It has been shown that the use of subsequent sealing means has a direct impact on the hinge moment value. The results of the CFD analysis showed that the more closed aileron gap is, the higher aileron forces are generated on the control stick. Completely closing the flow in the aileron gap changes the character of the force generated on the control stick. Practical implications Through CFD analyses of the aileron gap sealing in the PZL-130 Orlik aircraft, the impact of successive aileron gap sealing on the aileron efficiency was determined. It has been shown that simple change of the aileron gap size by the slat sealing can significantly affect the value of the forces generated on the control stick. Originality/value The research using CFD methods allowed to verify the impact of the particular type of aileron gap sealing on the hinge moment value and thus to determine proper sealing configuration for the PZL-130 Orlik aircraft at low computational cost.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Impact of the aileron gap sealing on the aileron effectiveness

Kowalska

Goetzendorf‐Grabowski

2022

AEAT

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“…Gaya counter tersebut adalah hinge moment, yang berupa restoring tendency dan floating tendency pada komponen control [1]. Menurut penelitian yang dilakukan oleh yang dilakukan oleh Zhang diketahui jika perubahan pada geometri rudder dapat berpengaruh pada hasil Ch yang dihasilkan oleh rudder [2]. Perubahan geometri dapat berubah dengan cara merubah desain rudder dan memberikan sudut defleksi pada rudder.…”

Section: Pendahuluanunclassified

Analisa Nilai Hinge Moment Coefficient pada Pengaruh Bentuk Rudder Pesawat N-2xx dengan Variasi Defleksi Rudder 0o, 10 O, dan 25 O Berbasis Computational Fluid Dynamics

Amir¹,

Sarwono²

2018

JTITS

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N-2XX adalah pesawat yang dirancang oleh PT. Dirgantara Indonesia untuk penerbangan rute perintis dan dibuat dengan teknologi full mechanical dalam melakukan penerbangannya. Pengendalian rudder yang dilakukan oleh pilot tersebut akan menghasilkan sebuah gaya counter yang disebut dengan coefficient hinge moment. Nilai coefficient hinge moment dari rudder tergantung dari bentuk rudder yang dimiliki pesawat, sehingga dilakukan analisa mengenai variasi nilai hinge moment terhadap bentuk rudder yang berbeda. Penggunaan rudder dengan bentuk conic dengan defleksi 0° dan 10° memiliki nilai coefficient hinge moment yang lebih kecil dibanding rudder circle. Namun pada sudut defleksi 25° rudder conic memiliki nilai Ch sebesar 0.051166 pada angle of attack-5°, lalu sebesar 0.060217 pada angle of attack 0°, dan sebesar 0.069274 untuk angle of attack 5°. Kata Kunci-Rudder, Angle of Attack, dan Coefficient Hinge Moment.

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“…G.Q. Zhang et al studied the effect of wing angle of attack on aileron hinge moments, and the results showed that under small clearances, hinge moments decreased gradually with the increase of angle of attack [30].…”

Section: Introductionmentioning

confidence: 99%

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

Meng,

Hu,

Wei

et al. 2024

Preprint

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The precise regulation of 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 has been developed to simulate 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 has 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 non-linearly 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 accurate prediction of aerodynamic hinge moments across various pitch angles and speeds.

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Investigation of the Three-Dimensional Hinge Moment Characteristics Generated by the ONERA-M6 Wing with an Aileron

Cited by 5 publications

References 15 publications

Impact of the aileron gap sealing on the aileron effectiveness

Impact of the aileron gap sealing on the aileron effectiveness

Analisa Nilai Hinge Moment Coefficient pada Pengaruh Bentuk Rudder Pesawat N-2xx dengan Variasi Defleksi Rudder 0o, 10 O, dan 25 O Berbasis Computational Fluid Dynamics

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

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