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Aeroelastic stability of full-span tiltrotor aircraft model in forward flight

Chinese Journal of Aeronautics 2017年第6期30卷 1885-1894页

作者： Zhiquan LI Pinqi XIA College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics Nanjing 210016 China

The existing full-span models of the tiltrotor aircraft adopted the rigid blade model without considering the coupling relationship among the elastic blade, wing and fuselage. To overcome the limitations of the existing full-span models and improve the precision of aeroelastic analysis of tiltrotor aircraft in forward flight, the aeroelastic stability analysis model of full-span tiltrotor aircraft in forward flight has been presented in this paper by considering the coupling among elastic blade, wing, fuselage and various components. The analytical model is validated by comparing with the calculation results and experimental data in the existing references. The influence of some structural parameters, such as the fuselage degrees of freedom, relative displacement between the hub center and the gravity center, and nacelle length, on the system stability is also investigated. The results show that the fuselage degrees of freedom decrease the critical stability velocity of tiltrotor aircraft, and the variation of the structural parameters has great influence on the system stability,and the instability form of system can change between the anti-symmetric and symmetric wing motions of vertical and chordwise bending.

关键词： Aeroelastic stability Forward flight Full-span model Modal analysis tiltrotor aircraft

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Time-varying linear control for tiltrotor aircraft

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Chinese Journal of Aeronautics 2018年第4期31卷 632-642页

作者： Jing ZHANG Liguo SUN Xiangju QU Liuping WANG School of Aeronautic Science and Engineering Beihang University School of Electrical and Computer Engineering RMIT University

tiltrotor aircraft have three flight modes： helicopter mode, airplane mode, and transition mode. A tiltrotor has characteristics of highly nonlinear, time-varying flight dynamics and inertial/-control couplings in its transition mode. It can transit from the helicopter mode to the airplane mode by tilting its nacelles, and an effective controller is crucial to accomplish tilting transition missions. Longitudinal dynamic characteristics of the tiltrotor are described by a nonlinear Lagrangeform model, which takes into account inertial/control couplings and aerodynamic interferences.Reference commands for airspeed velocity and attitude in the transition mode are calculated dynamically by visiting a command library which is founded in advance by analyzing the flight envelope of the tiltrotor. A Time-Varying Linear（TVL） model is obtained using a Taylorexpansion based online linearization technique from the nonlinear model. Subsequently, based on an optimal control concept, an online optimization based control method with input constraints considered is proposed. To validate the proposed control method, three typical tilting transition missions are simulated using the nonlinear model of XV-15 tiltrotor aircraft. Simulation results show that the controller can be used to control the tiltrotor throughout its operating envelop which includes a transition flight, and can also deal with vertical gust disturbances.

关键词： Constrained optimal control Inertia/control couplings tiltrotor aircraft Time-varying control Transition mode

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维普期刊数据库

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Nonlinear Attitude Control of tiltrotor aircraft in Helicopter Mode based on ADRSM Theory

Nonlinear Attitude Control of Tiltrotor Aircraft in Helicopt...

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第37届中国控制会议

作者： Zhen Pan Chengzhi Chi Jingkai Zhang National Key Laboratory of Avionics System Integration China Aeronautical Radio Electronic Research Institute

tiltrotor aircraft is a kind of aircraft which can fly as a fixed wing aircraft or a helicopter. However, it is difficult to control especially in helicopter mode. To control it well, a nonlinear mathematical model based on Pitt-Peters dynamic inflow theory is established. A novel control method named active disturbance rejection sliding mode theory（ADRSM） based on active disturbance rejection controller（ADRC） and sliding mode controller（SMC） is designed. First of all, a tracking differentiator（TD） is utilized to get the command of attitude and angular rate. Because the disturbance of the novel model includes the model error and coupling between different channels, a novel sliding mode extended state observer（SMESO） base on sliding mode theory is developed to estimate the disturbance of model. After that, a novel control law based on dynamic surface control theory is developed. And the stability of ADRSM is proved. The parameters of ADRSM are not changed during the whole process of simulation. Simulation results in various flight conditions show that ADRSM is feasible and parameters are available in a wide range.

关键词： tiltrotor aircraft helicopter mode ADRSM ADRC tracking differentiator

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