Longitudinal Aerodynamic Coefficients of Hydra Technologies UAS-S4 from Geometrical Data

Segui, Marine; Kuitche, Maxime Alex Junior; Botez, Ruxandra

doi:10.2514/6.2017-0579

Cited by 6 publications

(4 citation statements)

References 8 publications

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“…For the purpose of investigating the increase of performance, the geometrical characteristic of a real aircraft was considered. The estimations were made using the characteristic of the UAS-S4 (43)(44)(45) . The UAS-S4 is an unmanned aerial system designed and manufactured by Hydra technologies for the military and civilian purpose (Fig.…”

Section: Improved Range and Endurance Estimationmentioning

confidence: 99%

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Comparison and analyses of a variable span-morphing of the tapered wing with a varying sweep angle

Elelwi¹,

Kuitche²,

Botez³

et al. 2020

Aeronaut. j.

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ABSTRACTThis work presents a comparative study of design and development, in addition, of analyses of variable span morphing of the tapered wing (VSMTW) for the unmanned aerial vehicle (UAV). The proposed concept consists in the sliding of the inner section into the fixed part along the wing with varying the angle of the inner section inside the fixed part (parallel with the leading edge and the moving-wing axis is coincident to the fixed-wing axis) within two configurations. The wing design is based on a NACA 4412 aerofoil with the root chord of 0.675m and the tip chord of 0.367m for the fixed segment and 0.320m for the moving segment. Morphing wing analysis occurs at three selected locations that have been specified for extending and modifying span length by (25%, 50%, and 75%) of its original length to fulfill various flight mission requirements. The main objective of this paper is to compare the aerodynamic characteristics for several span lengths and sweep angles and to find their most efficient combinations. The wing is optimised for different velocities during all phases of flight (min speed, loiter, cruise, and max speed) which are 17, 34, 51, and 68m/s, respectively. The analyses are performed by computing forces (drag and lift) and moments at various altitudes, such as at the sea level, at 5,000 and 10,000ft. Two-dimensional aerodynamic analyses are carried out using XFLR5 code, and the ANSYS Fluent solver is used for investigating the flow field on the three-dimensional wing structure. It has been observed that a variable span morphing of tapered wing technology with a variable sweep angle can deliver up to 32.93% improved aerodynamic efficiency. This concept design can also be used for the aircraft roll motion technique instead of conventional control devices. Furthermore, the range flight mission increases up to 46.89% when the wing is placed at its full length compared to an original position. Finally, it has been concluded from this study that the wing design is more sensitive to the changing angle of the inner section and more efficient in terms of aerodynamic characteristics.

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Section: Improved Range and Endurance Estimationmentioning

confidence: 99%

“…The estimations were made using the characteristic of the UAS-S4 (43–45) . The UAS-S4 is an unmanned aerial system designed and manufactured by Hydra technologies for the military and civilian purpose (Fig.…”

Section: Aerodynamic Analysismentioning

confidence: 99%

Comparison and analyses of a variable span-morphing of the tapered wing with a varying sweep angle

Elelwi¹,

Kuitche²,

Botez³

et al. 2020

Aeronaut. j.

View full text Add to dashboard Cite

show abstract

“…The angular rate stability derivatives were taken from values estimated from gathered flight data. The explicit values of aircraft stability (A lon and A lat ) and control (B lon and B lat ) parameters are shown in Equations (32) and (33). They were defined according to [23].…”

Section: Airplane Dynamic Modelmentioning

confidence: 99%

“…In addition, control surfaces were actuated by Hitec R electric servos providing a maximum ailerons deflection of 35 deg, maximum rudder deflection of 25 deg, and maximum elevator deflection of 20 deg. The properties of the airframe are shown in Table 2, and the moments of inertia were calculated using XFLR5, as shown in Figure 5 [32]. K2 aircraft was instrumented with a redundant IMU that measured angular rates and translational accelerations.…”

Section: Experimental Arrangementmentioning

confidence: 99%

Experimental Validation of Total Energy Control System for UAVs

et al. 2019

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This paper presents an analysis of a Total Energy Control System (TECS) introduced by Lambregts to control unmanned aerial vehicle (UAV) velocity and altitude by using the total energy distribution. Furthermore, an extended Kalman filter (EKF) approach was used to predict aircraft response in terms of angular rates and linear acceleration during a test flight campaign. From both approaches, state equations were obtained to model the aircraft using Matlab-Simulink. From an aerodynamic study, airplane characteristics were obtained in terms of non-dimensional derivatives and compared to those obtained from the experimental methods. It was determined that TECS approach was very accurate; however, disturbance errors could be decreased by adjusting some model parameters. On the other hand, it was difficult to obtain a real estimation from the EKF method due to the presence of turbulence during flight and the relatively low inertia of the scale model. Dynamic characteristics were validated using a low-cost inertial sensor that cab be easily integrated in UAV platforms. The gathered data can be used to predict model characteristics by integrating the information into flight simulators for future design development.

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Blade element momentum new methodology and wind tunnel test performance evaluation for the UAS-S45 Bàlaam propeller

Kuitche¹,

Botez²,

Viso³

et al. 2020

CEAS Aeronaut J

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Longitudinal Aerodynamic Coefficients of Hydra Technologies UAS-S4 from Geometrical Data

Cited by 6 publications

References 8 publications

Comparison and analyses of a variable span-morphing of the tapered wing with a varying sweep angle

Comparison and analyses of a variable span-morphing of the tapered wing with a varying sweep angle

Experimental Validation of Total Energy Control System for UAVs

Blade element momentum new methodology and wind tunnel test performance evaluation for the UAS-S45 Bàlaam propeller

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