Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

Fujita, Koji; Oyama, Akira; Kubo, Daisuke; Kanazaki, Masahiro; Nagai, Hiroki

doi:10.4236/jfcmv.2019.72007

Cited by 7 publications

(6 citation statements)

References 3 publications

(3 reference statements)

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“…Therefore, the effect of the twist on the lift coefficient is considered negligible. Table 2 presents a summary of the wingtip deformation obtained from the wind tunnel test, the static load test of the main wing, and the wind tunnel test of the MABE1 [23].…”

Section: Deformation Of the Main Wingmentioning

confidence: 99%

“…However, since the replica has different structural characteristics from the actual aircraft, it is obvious that the wind tunnel tests for measuring the aeroelastic deformation using an actual airplane are the most accurate. Fujita et al conducted a wind tunnel test to measure the aeroelastic deformation of the actual MABE1 using a motion capture system of VICON [23]. Ball-type markers with a diameter of 14 mm used can interfere with the flow around the wing.…”

Section: Introductionmentioning

confidence: 99%

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Aeroelastic deformation measurement of Martian airplane for high-altitude flight experiment using stereophotogrammetry

Hiramatsu¹,

Anyoji²,

Fujita³

et al. 2021

Eng. Res. Express

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A fixed-wing aircraft called Mars Airplane Balloon Experiment −2 (MABE2) developed by the authors was the subject of high-altitude flight demonstration test in this paper, which can simulate the near-actual environment of a Martian atmospheric flight. Although the flight condition is in the low-Reynolds-number region due to low density at high altitude, the wing suffers from aeroelastic deformation given the relatively high dynamic pressure load in the pull-up phase. Stereophotogrammetry was applied in the 6.5 m × 5.5 m low-speed wind tunnel at the Japan Aerospace Exploration Agency (JAXA), aiming to optically measure MABE2’s aeroelastic deformation under dynamic pressure loads equivalent to high-altitude flight test, with the MABE2’s reinforced structural strength. The results of the accuracy test indicated that stereophotogrammetry measures aeroelastic deformation at high accuracy of ±0.1 mm around the image center and ±0.3 mm around the edge. A slight deflection of up to 4 mm was observed on the main wing, whereas both the main and tail wings were hardly twisted. Compared with flight-simulation-assumed errors, these deformations are extremely small and have a negligible effect on the high-altitude flight test. The study results confirmed the practicality and efficiency of this optical measurement technique in aeroelastic deformation measurement for a real light aircraft.

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Section: Deformation Of the Main Wingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aeroelastic deformation measurement of Martian airplane for high-altitude flight experiment using stereophotogrammetry

Hiramatsu¹,

Anyoji²,

Fujita³

et al. 2021

Eng. Res. Express

Self Cite

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show abstract

“…Currently, the types of Mars spacecraft being developed mainly include five categories: scientific balloons [4], fixed-wing aircraft [5,6], gliders [7], rotorcraft [8][9][10], and flapping-wing aircraft [11]. Compared with other types of spacecraft, rotorcraft have the characteristics of strong maneuverability, wide environmental adaptability, and vertical takeoff and landing capabilities [12,13].…”

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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“…Currently, the types of Mars spacecraft being developed mainly include five categories: scientific balloons [3], fixed-wing aircraft [4,5], gliders [6], rotorcraft [7][8][9], and flapping-wing aircraft [10]. Compared with other types of spacecraft, rotorcraft have the characteristics of strong maneuverability, wide environmental adaptability, and vertical takeoff and landing capabilities [11,12].…”

Section: Introductionmentioning

confidence: 99%

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

Meng,

Hu,

Wei

et al. 2024

Drones

View full text Add to dashboard Cite

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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Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

Cited by 7 publications

References 3 publications

Aeroelastic deformation measurement of Martian airplane for high-altitude flight experiment using stereophotogrammetry

Aeroelastic deformation measurement of Martian airplane for high-altitude flight experiment using stereophotogrammetry

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

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

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