Research on transition corridor boundary of distributed propulsion VTOL fixed wing by Cheng Yuxuan, Zhou Zhou, Wang Kelei

“…The transition state is the most critical and dangerous state of the VTOL fixed wing aircraft in the whole flight process. In this paper, a transition corridor for a distributed propulsion VTOL fixed-wing aircraft is studied based on the lift characteristics of the wing and the power constraints of the power unit. …”
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Development and Trend Analysis of Vertical Takeoff and Landing Fixed Wing UAV by WANG Kelei, ZHOU Zhou, MA Yuewen, DU Wanshan, GUO Jiahao, LI Xu, ZHANG Yang, SUN Pengbo

Subjects: “…vtol fixed wing uav…”
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Modeling and Simulation for Multi-Rotor Fixed-Wing UAV Based on Multibody Dynamics

“…The dynamic model for the multi-rotor fixed-wing UAV was looked into and it was divided into fuselage, air-body, multi-rotors, vertical fin, vertical tail and control surfaces, based on the multibody dynamics. …”
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Aerodynamic Modeling and Path Optimization of Wing Docking Process for Fixed-Wing UAVs by Yiwei CHEN, Haojie LIU, Rui HUANG, Xiumin GAO

“…The problem of aerial docking of fixed-wing UAVs restricts the development of the chained-wing UAVs. …”
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Interference Analysis of Rotor and Wing of Compound Vertical Takeoff and Landing Fixed Wing UAV by Zhang Fei, Wang Yun, Tan Kun

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Study on longitudinal stability of ducted vertical take-off and landing fixed-wing UAV

“…The longitudinal flight stability of the ducted vertical take-off and landing fixed-wing UAV during the flight state of hovering and transition is studied. …”
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Research on Transition Corridor of Ducted Vertical Take-off and Landing Fixed-wing UAV by WANG Chunyang, ZHOU Zhou

Subjects: “…vertical take-off and landing fixed-wing…”
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Design Analysis of Wing Tip Vertical Tail of the Vertical Takeoff and Landing Fixed-wing UAV by Zhang Fei, Wang Yun, Sun Yifang, Tan Kun

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Online Fault Detection of Fixed-Wing UAV Based on DKPCA Algorithm with Multiple Operation Conditions Considered

Subjects: “…fixed-wing uav…”
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Aerodynamic optimization design of Z-shaped folding UAV by Bin MENG, Jinkang ZHANG, Lele XI, Zexia YANG, Ning ZHOU

Subjects: “…fixed wing aircraft; unmanned aerial vehicle; optimization design; genetic algorithm; airfoil parameterization; flow field modeling; aerodynamic performance…”
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A dense obstacle avoidance algorithm for UAVs based on safe flight corridor by FAN Liyuan, ZHANG Haozhe, XU Zhao, LYU Mingwei, HU Jinwen, ZHAO Chunhui, LIU Xiaobin

“…Aiming at the problem of autonomous obstacle avoidance of fixed-wing UAVs in a complex, dense and multi-obstacle environment, a path planning algorithm for fixed-wing UAVs based on a safe flight corridor is proposed. …”
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Design and analysis of takeoff and landing control algorithm for four-rocket boosting drone by TIAN Weili, YAN Zhaowu, LI Wen, JIA Dong

“…Fixed wing UAV takes off and lands on the ground with high requirements，which limits the application and development of fixed wing aircraft. …”
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High-performance Propeller Optimization Design by Wang Ce, Tang Zhengfei, Luo Jian

“…The propeller blades used in unmanned multi-rotor aircraft are mainly fixed-wing propellers, but their aerodynamic environments are not the same. …”
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Study on Aerodynamic Characteristics of Tilting Wing Aircraft Considering Propeller Interference by Wei Wei, Han Qing, Sang Xiaoqing, Liu Xing

“…Tilting wing aircraft not only has the ability of vertical take-off and landing like helicopter, but also be provided with high speed cruise capability as traditional fixed-wing aircraft.Tilting wing aircraft is one of the hot spots of research in both military and civilian unmanned aerial vehicles.A new layout, tilt-tandem wing and quadrotor of vertical take-off and landing(VTOL)aircraft, is proposed to avoid the defects of low aerodynamic efficiency and complicated tilting mechanism.Conceptual design and aerodynamics simulation are carried out to analyze the aerodynamic characteristics of aircraft with the interference of propellers.Further more, prototypes are made and experienced several flight tests validation.Results show that this layout can avoid the disadvantages of low efficiency propellers and complicated tilting mechanism, which is reliable and practical.…”
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Aerodynamic Optimization Design of the Rotor Blade of a Tilt-rotor Aircraft by Sun Kaijun, Zhang Lian, Fu Yiwei, Yu Yueyang

“…The aerodynamic design of tilt-rotor needs to synthetically consider the different requirements in helicopter mode and fixed-wing aircraft mode. The multi-objective genetic algorithm based on Kriging surrogate model is used to establish an optimization design methods for aerodynamic shape of tilt-rotor, the Latin hypercube sampling method is employed to generate the initial sample points, and the Kriging surrogate model is built to replace the numerical simulation of flow. …”
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Reliability Evaluation of a Certain Missile's Telescopic Wing Deployment by ZHU Xinghong, LI Weinan, GENG Xiaoliang, HUANG Yimin

“…Compared with fixed wing, the telescopic wing can effectively reduce the space of aircraft missile bay.The reliability reduction becomes a problem that cannot be ignored due to the existence of the mechanism of the telescopic wing.In order to explore the reliability of the new mechanism, the positioning reliability of a certain type of telescopic wing deployment mechanism is calculated from a theoretical perspective, Adams is used to simulate the deployment process of the telescopic wing, and the Adams/Insight module is combined to calculate the clamping reliability under the friction force.The reasons for the clamping failure of the telescopic wing are analyzed.The results show that the presence of foreign matter can significantly reduce the positioning reliability of the telescopic wing, the suitable increase of preload of upper and lower wing springs can effectively reduce the clamping failure of telescopic wing mechanism, and the additional torque generated by the upper and lower wing springs at the center of mass of the upper wing can reduce the clamping failure of telescopic wing.…”
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Flight Performance Estimation of Bionic Flapping-Wing Micro Air Vehicle

“…Bionic flapping-wing micro air vehicle(MAV) has received worldwide attention.The flight performance calculation is an important step in the conceptual design.The differences in performance estimation methods between the flapping-wing and conventional fixed-wing aircraft are analyzed.Based on the results of the aerodynamic estimation and wind tunnel experimental measurement, the flight performance estimation method of flapping-wing micro air vehicle is proposed, and the performance of level flight, climbing, and duration are calculated and analyzed.The frequency represents the accelerator in a certain extent, while the frequency is coupled with lift and thrust.The results show that there may be two stable cruising states at certain frequencies, one is the small angle of attack with high speed, the other is the small speed with big angle of attack, and the two states have different power consumption.According to the parameters of the vehicle, climbing performance and duration performance can be obtained.The speed versus power characteristic curve is a U shape, minimum slope of the U curve can be obtained through the mapping method to calculate the farthest flight speed, and the minimum velocity of U-shaped curve is the speed for longest duration.The proposed flight performance calculation method can be used to evaluate the flight capability of bionic micro flapping-wing air vehicle.…”
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Study on modular design method of tiltable rotor system for quad tilt-rotor unmanned aircraft by SUN Xiaobin, XU Jinfa

“…The results show that the rotor speed fluctuation error is less than 2.6%, the smooth and uniform transition from helicopter mode to fixed wing mode can be achieved within 7 s, and the system has good real-time data communication, which meet the application requirements of tiltable rotor system.…”
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Analysis of Reachable Set for Aircraft Perching Trajectory by DU Xin, HUANG Jiangtao, ZHANG Sheng

“…The landing maneuver of aircraft is considered to be a feasible way to solve the problem of ultra short distance,precise landing of carrier based fixed wing aircraft. The existing researches mainly focus on aerodynamic modeling,nominal landing trajectory optimization and trajectory tracking control in the process of landing,but few on the overall analysis of the landing mission. …”
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Study on the effect of transition process on rotor hovering simulation by PANG Chao, LI Meng, GAO Zhenghong

“…The transition process will evidently affect the results from the RANS-based numerical simulations in some steady cases for the fixed wing aircrafts, which should be taken into consideration in the design process. …”
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