曹义华
长期从事飞行器空气动力学,旋涡动力学,飞行力学,计算流体力学,飞行器CFD和气动弹性力学等方面的研究工作。
个性化签名
- 姓名:曹义华
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学术头衔:
博士生导师
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学科领域:
林业工程
- 研究兴趣:长期从事飞行器空气动力学,旋涡动力学,飞行力学,计算流体力学,飞行器CFD和气动弹性力学等方面的研究工作。
曹义华:男,1962年11月出生,北京航空航天大学教授,博士生导师。1982年南京航空航天大学飞行器设计专业本科毕业,1982年-1984年在中国直升机设计研究所工作。1990年于南京航空航天大学获飞行器设计专业飞行器空气动力学博士学位,1992年南京理工大学气体动力学博士后出站。1993-1994年工作于北京航空航天大学流体力学研究所。1995年获德国王宽诚奖学金,联邦德国科学技术交流署客座研究员,德国布伦瑞克技术大学访问教授;1995-1997年赴德国布伦瑞克技术大学航空系从事飞行器动力学、空气动力学与飞行力学等方面的客座研究。
曹义华教授主讲过博士生、留学硕士生、硕士生的《高等飞行动力学与控制理论》;《Flight Dynamics》;《V/STOL Aerodynamics》;《Rotorcraft Theory》;《直升机飞行性能分析》;《交通运输工程学》《直升机空气动力学》等10余门课程;培养博士生、硕士生20余名。曾任北京航空航天大学飞行器设计与应用力学系研究生指导主任。
在科研方面长期从事飞行器空气动力学,旋涡动力学,飞行力学,计算流体力学,飞行器CFD和气动弹性力学等方面的研究工作,已有部分成果发表在《European Rotorcraft Forum》、ICAS等国际会议上;以及国际知名杂志等刊物。以第一作者身份,在国内外刊物发表学术论文100多篇,其中SCI、SCIE及国际知名刊物论文20余篇(发表在《Journal of the American Helicopter Society》,《AIAA Journal of Aircraft》,《Journal of Aerospace Engineering》,《Aircraft Engineering and Aerospace Technology: An International Journal》,《Canadian Aeronautics and Space Journal》 等刊物上) 。主要译著一部,编写教材专著一部,参加编写国家级军用直升机标准2部,参加编写简明华夏百科全书力学卷等。获部委级科技进步奖二等和三等共3项;1995年获德国王宽诚奖学金,联邦德国科学技术交流署客座研究员,德国布伦瑞克技术大学访问教授。曾多次出访德国、荷兰、法国和俄罗斯等国家进行学术交流,现为北京航空航天大学学科责任(二级)教授,航空科学与工程学院飞机设计研究所副所长,博士生导师,美国直升机学会( American Helicopter Society )国际会员,英国国际知名杂志《Journal of Aerospace Engineering》等刊物的审稿专家。
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主页访问
3461
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关注数
0
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成果阅读
175
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成果数
4
【期刊论文】A New Inverse Solution Technique for Studying Helicopter Maneuvering Flight
曹义华, Yihua Cao
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-1年11月30日
The inverse snlution problem of vehicle motion in maneuvering flight is discussed in which the control inputs can be determined su as to enable a vehicle to perform a specified maneuver. For a nonlinear dynamic system such as a helicopter, imprnviug the mathematical model of helicopter maneuvering flight and the corresponding solution technique is one of the most complex and challenging problems in applied mechanics. In this paper a set of nonlinear equations governing the helicopter in maneuvering flight is developed and solved by using a new iuverse solution technique. The inverse solution technique is improved to emphasize nonlineaedy and good stability and convergence of the sample calculations of level turn, lateral jink, and pup-up maneuvers for twn kinds of helicopters. Beginning with a set of prescribed flight conditions, this inverse solution calculates the flight path, velocity, and other kinematic parameters first, and then the control inputs, flight altitude, and the load factor for the specified maneuver.
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29浏览
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【期刊论文】Numerical analysis of the airfoil flow fields and transonic blade-vortex interaction noise
曹义华, Yihua Cao*, Pengbin Kang and Xiaoyong Li
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-1年11月30日
The flow fields around NACA0012, NACA23012 and OA207 airfoils can be calculated by solving the Euler Navier Stokes equations. The far-field noise generated by NACA0012 airfoilvortex interaction is predicted using the combined Euler-Kirchhoff method. The Kirchhoff surfice is selected as one of the grid surfaces. Firstly, the result of flow field under airfoil-vortex interaction can be obtained by solving the Euler equations. Then the result of far-field noise can be obtained by the Kirchhoff method. Finally, the combined Euler-Kirchhoff method developed here is proved to be good for studying blade-vortex interaction noise through sample calculations.
Euler-Navier-Slokes equations,, Kirchhoff method,, blade-vortex interaction,, rotor aeroacoustics
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52浏览
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133下载
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【期刊论文】Helicopter manoeuvre gaming simulation and mathematical inverse solution
曹义华, Y Cao and Y Su
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-1年11月30日
The helicopter has evolved into one of the most powerful flight vehicles for air domination at low level. There are many factors that influence the success of a helicopter in manoeuvre gaming. Among those factors, the helicopter must have the manoeuvrability and agility to gain a favourable firing position first, and then the whole system must be able to achieve first round hits for successful manoeuvre gaming. In an attempt to address these factors, a general analytical model of helicopter manoeuvring flight and the projectile path is established in this paper. Taking helicopter manoeuvre gaming (blue helicopter versus red helicopter) at short range as an example, the inverse solution technique can be described with the following three stages. Firstly, this medthod calculates the kinematic parameters of the blue helicopter and then the fight attitudes and control law of the blue helicopter. At the final stage, the red helicopter position, projectile path, hit time and the firing position of the turreted gun are calculated.
helicopter,, manoeuvre gaming,, mathematical inverse solution
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46浏览
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145下载
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【期刊论文】Mixed Jameson/Total-Variation-Diminishing Scheme Applied to Simulating Rotor Airfoil FIowfield
曹义华, Yihua Cao, * Jifei Wang, * and Yuan Su
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-1年11月30日
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48浏览
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127下载
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