ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Design of fully electric scheme for three⁃surface verification aircraft
Received date: 2023-09-20
Revised date: 2023-11-23
Accepted date: 2024-02-01
Online published: 2024-02-07
With the increasingly strict carbon emission policy， green air travel has become one of the new goals of civil aircraft design. The room of improvement of aerodynamic efficiency and structural efficiency of the civil aircraft with traditional layout is limited， so it is difficult to achieve greater drag reduction.The design scheme of new layout combined with new energy have become a research hotspot.This paper summarizes the research progress of new layout technologies of Blended Wing Body （BWB）， Truss-Braced Wing （TBW） and Three-Surface Aircraft （TSA）， as well as new energy technologies of electric vehicles. Based on the layout characteristics of the 200 kg UAV verification aircraft “Windrider 2.0”， the aerodynamic characteristics analysis and layout benefit evaluation of the three-surface layout are carried out by the Computational Fluid Dynamics （CFD） and engineering estimation method. The pitching moment characteristics of single deflection and combined deflection of canard and horizontal tail are analyzed. The canard has the ability to recover from high angle of attack and good high-a nose-down control capability. Compared with the non-canard wing layout， the complete three-surface layout of the verification aircraft can obtain about 7% trim lift increase at 4° of angle of attack. Considering the negative effects of zero-lift drag， downwash and weight increase of the canard， the drag can be reduced by about 19.7count， and the cruise lift-to-drag ratio is increased by 3%. The take-off weight gain caused by the canard + tail components is about 0.3%. The distributed electric propulsion architecture is designed， which can reduce the asymmetric thrust moment by 90%. The flight test of electric propulsion architecture and performance is carried out based on the UAV verification aircraft. When the cruise airspeed is 45 m/s， the power required by the verification aircraft is about 20 kW， and the cruise energy consumption is 0.126 kW·h/km. When the cruise airspeed is 35 m/s， the power required is 8 kW， and the cruise energy consumption is 0.065 kW·h/km. The maximum power is 45 kW in the take-off phase， which is twice the cruise power， and the take-off energy consumption accounts for about 2 % of the flight profile.
Chuihuan KONG , Dawei WU , Zhaoguang TAN , Lijun PAN , Rubing MA , Jiangtao SI . Design of fully electric scheme for three⁃surface verification aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(6) : 629618 -629618 . DOI: 10.7527/S1000-6893.2024.29618
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