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Modern problems of aircraft aerodynamics

Advances in aerodynamics 2019年第1期1卷 145-159页

作者： Sergey L.Chernyshev Sergey V.Lyapunov Andrey V.Wolkov Department of aerodynamics Central Aerohydrodynamic Institute named after Prof.N.EZhukovsky(TsAGI)140180Zhukovsky str.1ZhukovskyRussia

The article represents the discussion of several separate directions of investigations,which are performed by TsAGI flight vehicles aerodynamics specialists at the time.There are some major trends of classical layout of route aircraft and also peculiarities of some prospective flight vehicles.Also there are some hypersonic vehicles aerodynamics questions examined along with problems of creation of civil supersonic transport aircraft.There is a description given for well-known and some newer methods of flow control for drag reduction.

关键词： aircraft aerodynamics Hypersonic vehicles aerodynamics Civil supersonic transport aircraft Sonic boom

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A practical filter error method for aerodynamic parameter estimation of aircraft in turbulence

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Chinese Journal of Aeronautics 2023年第2期36卷 17-28页

作者： Qing WANG Fengqi ZHENG Weiqi QIAN Di DING State Key Laboratory of aerodynamics China Aerodynamics Research and Development CenterMianyang 621000China Computational aerodynamics Institute China Aerodynamics Research and Development CenterMianyang 62100China

It is common for aircraft to encounter atmospheric turbulence in flight tests.Turbulence is usually modeled as stochastic process noise in the flight dynamics equations.In this paper,parameter estimation of nonlinear dynamic system with both process and measurement noise was studied,and a practical filter error method was proposed.The linearized Kalman filter of first-order approximation was used for state estimation,in which the filter gain,along with the system parameters and the initial states,constituted the parameter vector to be estimated.The unknown parameters and measurement noise covariance were estimated alternately by a relaxation iteration method,and the sensitivities of observations to unknown parameters were calculated by finite difference approximation.Some practical aspects of the method application were discussed.The proposed filter error method was validated by the flight simulation data of a research aircraft.Then,the method was applied to the flight tests of a subscale aircraft,and the aerodynamic stability and control derivatives were estimated.All the estimation results were compared with the results of the output error method to demonstrate the effectiveness of the approach.It is shown that the filter error method is superior to the output error method for flight tests in atmospheric turbulence.

关键词： aircraft aerodynamics Atmosphere turbulence Flight tests Kalman filter Maximum likelihood estimation Measurement noise Parameter estimation Stability and control derivatives

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A Knowledge-based and Extensible aircraft Conceptual Design Environment

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Chinese Journal of Aeronautics 2011年第6期24卷 709-719页

作者： FENG Haocheng LUO Mingqiang LIU Hu WU Zhe School of Aeronautic Science and Engineering Beihang University Beijing 100191 China

Design knowledge and experience are the bases to carry out aircraft conceptual design tasks due to the high complexity and integration of the tasks during this phase. When carrying out the same task, different designers may need individual strategies to fulfill their own demands. A knowledge-based and extensible method in building aircraft conceptual design systems is studied considering the above requirements. Based on the theory, a knowledge-based aircraft conceptual design environment, called knowledge-based and extensible aircraft conceptual design environment （KEACDE） with open architecture, is built as to enable designers to wrap add-on extensions and make their own aircraft conceptual design systems. The architecture, characteristics and other design and development aspects of KEACDE are discussed. A civil airplane conceptual design system （CACDS） is achieved using KEACDE. Finally, a civil airplane design case is presented to demonstrate the usability and effectiveness of this v environment.

关键词： conceptual design knowledge engineering aircraft aerodynamics structural design weight estimation multidisciplinary design optimization

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Theoretical fundamentals of airframe/ propulsion integration for high-speed aircraft

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Advances in aerodynamics 2019年第1期1卷 226-238页

作者： A.A.Gubanov Central Aerohydrodynamic Institute named after Professor N.E.Zhukovsky(TsAGI) ZhukovskyMoscow RegionRussian Federation

Fundamental features of aerodynamic interference and integration of airframes and air-breathing jet engines for high-speed flight vehicles are studied within the framework of supersonic small perturbation theory.Both the influence of airframe components on air intakes performance and influence of intakes on vehicle external aerodynamics are under consideration.Analytical relations and specific examples show that significant favorable interference between airframes and air intakes can be realized by using preliminary compression of the flow in front of intakes at flight Mach numbers exceeding approximately 3.

关键词： aircraft aerodynamics Supersonic flight vehicles Aerodynamic configurations Airframe/propulsion integration Analytical studies CFD Wind-tunnel tests

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