Unmanned coaxial rotor helicopter dynamics and system parameter estimation

Harun‐Or‐Rashid, Mohammad; Song, Jun-Beom; Chae, Sanghyun; Byun, Young-Seop; Kang, Beom-Soo

doi:10.1007/s12206-014-0842-7

Cited by 11 publications

(5 citation statements)

References 6 publications

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“…The estimation as well as validation results show small inconsistencies with the experimental data because of the system's vibration and external disturbances such as wind. Figures 13 and 14 show that there are uneven fluctuations in the experimental data and slight discrepancies between experimental and simulation data, which result from sensor data-acquisition error and wind gust [21]. The developed numerical plant model does not consider wind gust or load disturbances [16] and the controller has limitations.…”

Section: Resultsmentioning

confidence: 99%

Inflow Prediction and First Principles Modeling of a Coaxial Rotor Unmanned Aerial Vehicle in Forward Flight

Harun‐Or‐Rashid¹,

Song²,

Byun³

et al. 2015

International Journal of Aeronautical and Space Sciences

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When the speed of a coaxial rotor helicopter in forward flight increases, the wake skew angle of the rotor increases and consequently the position of the vena contracta of the upper rotor with respect to the lower rotor changes. Considering ambient air and the effect of the upper rotor, this study proposes a nonuniform inflow model for the lower rotor of a coaxial rotor helicopter in forward flight. The total required power of the coaxial rotor system was compared against Dingeldein's experimental data, and the results of the proposed model were well matched. A plant model was also developed from first principles for flight simulation, unknown parameter estimation and control analysis. The coaxial rotor helicopter used for this study was manufactured for surveillance and reconnaissance and does not have any stabilizer bar. Therefore, a feedback controller was included during flight test and parameter estimation to overcome unstable situations. Predicted responses of parameter estimation and validation show good agreement with experimental data. Therefore, the methodology described in this paper can be used to develop numerical plant model, study non-uniform inflow model, conduct performance analysis and parameter estimation of coaxial rotor as well as other rotorcrafts in forward flight.

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Section: Resultsmentioning

confidence: 99%

Inflow Prediction and First Principles Modeling of a Coaxial Rotor Unmanned Aerial Vehicle in Forward Flight

Harun‐Or‐Rashid¹,

Song²,

Byun³

et al. 2015

International Journal of Aeronautical and Space Sciences

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“…Figure 2 shows the aerodynamic forces caused by fixed wings and special empennages, which can be calculated by Eq. (11).…”

Section: Coaxial Rotors Aerodynamicsmentioning

confidence: 99%

“…The navigation velocity of fixed wing type can be satisfying, but the vertical taking-off and landing (VTOL) problems cannot be solved reasonably [6,7]. The most applied rotary rotor type performs perfectly in VTOL and hovering flight [8,9], and the coaxial rotor type has been proved to afford higher loading with dual rotors based on the study of coaxial helicopters [10,11]. However, the aerodynamic coupling interference and mechanical vibration caused by rotor rotation will seriously influence the flight stability of UAVs [12,13].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic characteristic analysis and layout optimization design for compound UAVs by using hybrid Fuzzy–PSO algorithm

Chen

Qin

Shang

et al. 2019

J Braz. Soc. Mech. Sci. Eng.

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In order to further improve the performance of compound UAVs at high and low speed with heavy loading, a type of compound coaxial UAV with fixed wings and tail ducted-rotor thrusters was proposed to meet technology requirement. The lift and thrust aerodynamic characteristics were analyzed to get some relative characteristic and the aerodynamic coupling relationships between the fixed wings and tail propulsion system. And an optimization method based on hybrid Fuzzy-PSO (HFPSO) algorithm was proposed to obtain the optimal configuration plan that can reach the best aerodynamic performance without considering the coaxial architecture. The optimal configuration plan was finally obtained by applying the HFPSO method which also proves the method is effective and reasonable through comparison.

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“…The navigation velocity of fixed wing type can be satisfying, but the vertical taking-off and landing (VTOL) problems cannot be solved reasonably (Beard et al , 2005; Johnson et al , 2015). The most applied rotary rotor type performs perfectly in VTOL and hovering fight (Panagiotou and Yakinthos, 2020; Poh and Poh, 2016), and the coaxial rotor type has been proved to afford higher loading with dual rotors based on the study of coaxial helicopters (Zhang et al , 2015; Harun-Or-Rashid et al , 2014). However, the aerodynamic coupling interference and mechanical vibration caused by rotor rotation will seriously influence the fight stability of UAVs (Chattopadhyay et al , 1991; Koehl et al , 2012).…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic analysis of a logistics UAV wing with compound ducted rotor

Guan

Zeng

2022

AEAT

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Purpose To solve the problems of short battery life and low transportation safety of logistics drones, this paper aims to propose a design of logistics unmanned aerial vehicles (UAV) wing with a composite ducted rotor, which combines fixed wing and rotary-wing. Design/methodology/approach This UAV adopts tiltable ducted rotor combined with fixed wing, which has the characteristics of fast flight speed, large carrying capacity and long endurance. At the same time, it has the hovering and vertical take-off and landing capabilities of the rotary-wing UAV. In addition, aerodynamic simulation analysis of the composite model with a fixed wing and a ducted rotor was carried out, and the aerodynamic influence of the composite model on the UAV was analyzed under different speeds, fixed wing angles of attack and ducted rotor speeds. Findings The results were as follows: when the speed of the ducted rotor is 2,500 rpm, CL and K both reach maximum values. But when the speed exceeds 3,000 rpm, the lift will decrease; when the angle of attack of the fixed wing is 10° and the rotational speed of the ducted rotor is about 3,000 rpm, the aerodynamic characteristics of the wing are better. Originality/value The novelty of this work comes from a composite wing design of a fixed wing combined with a tiltable ducted rotor applied to the logistics UAVs, and the aerodynamic characteristics of the design wing are analyzed.

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Unmanned coaxial rotor helicopter dynamics and system parameter estimation

Cited by 11 publications

References 6 publications

Inflow Prediction and First Principles Modeling of a Coaxial Rotor Unmanned Aerial Vehicle in Forward Flight

Inflow Prediction and First Principles Modeling of a Coaxial Rotor Unmanned Aerial Vehicle in Forward Flight

Aerodynamic characteristic analysis and layout optimization design for compound UAVs by using hybrid Fuzzy–PSO algorithm

Aerodynamic analysis of a logistics UAV wing with compound ducted rotor

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