民用飞机气动伺服弹性试飞激励响应仿真研究
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摘要
为提高民用飞机气动伺服弹性试飞仿真预测能力,实现高效安全的民用飞机气动伺服弹性试飞。在民用飞机气动伺服弹性试飞方法的基础上,提出民用飞机气动伺服弹性试飞激励响应仿真方法。该方法以民用飞机全机动力学有限元模型为基础,建立带飞行控制律的飞机气动伺服弹性模型,通过副翼、升降舵和方向舵的激励分别实现对飞机的激励响应仿真,得到飞机结构响应量值。为进一步验证该方法的可行性,进行某民用飞机副翼脉冲激励响应仿真,并将仿真响应结果与试飞结果对比,响应幅值相差15.3%,满足工程要求。民用飞机气动伺服弹性试飞仿真很好地预测试飞激励的飞机响应,为试飞激励信号的优化以及结构响应的评估提供技术参考。
In order to improve the simulation and prediction ability and realize an efficient and safe aeroservoelastic flight test for civil aircraft. On the basis of the aeroservoelastic flight test method of civil aircraft, the simulation method of civil aircraft aeroservoelastic flight test excitation response is presented. The aeroservoelastic model of aircraft with flight control law is established on the basis of the finite element model of civil aircraft full machine dynamics. The response simulation of aircraft is realized by the excitation of the aileron, elevator and rudder, and the response value of the aircraft structure is obtained. In order to further verify the feasibility of this method, the response simulation of a civil aircraft aileron impulse excitation is carried out, and the simulation response results are compared with the results of flight test. The difference of response amplitude is 15.3%, which satisfies the engineering requirements. The aeroservoelastic test flight simulation of civil aircraft has well predicted the response of the aircraft excitation during the flight test, which provides an technical method for the optimization of the test flight excitation signal and the evaluation of the structural response.
In order to improve the simulation and prediction ability and realize an efficient and safe aeroservoelastic flight test for civil aircraft. On the basis of the aeroservoelastic flight test method of civil aircraft, the simulation method of civil aircraft aeroservoelastic flight test excitation response is presented. The aeroservoelastic model of aircraft with flight control law is established on the basis of the finite element model of civil aircraft full machine dynamics. The response simulation of aircraft is realized by the excitation of the aileron, elevator and rudder, and the response value of the aircraft structure is obtained. In order to further verify the feasibility of this method, the response simulation of a civil aircraft aileron impulse excitation is carried out, and the simulation response results are compared with the results of flight test. The difference of response amplitude is 15.3%, which satisfies the engineering requirements. The aeroservoelastic test flight simulation of civil aircraft has well predicted the response of the aircraft excitation during the flight test, which provides an technical method for the optimization of the test flight excitation signal and the evaluation of the structural response.
引文
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[2]吴森堂,费玉华.飞行控制系统[M].北京:北京航空航天大学出版社,2009:139-144.
[3]LAWRENCE J,HUTTSELL R D,KROBUSEK,HOWARDL,FARMER.Application of three aeroservoelastic stability analysis techniques[R].AFFDL,1976.
[4]ARTHURS T D,GALLAGHER J T.Interaction between control augmentation system and airframe dynamic on the YF-17 [C]//16th Structural Dynamics,and Materials Conference.AIAA,1975.
[5]PELOUBET R P.YF-16 active control system/structural dynamic interaction instability[C]//16th Structural Dynamics,and Materials Conference.AIAA,1975.
[6]LOTZE A,SENSBURG O,KUHN M.Flutter investigation of a Combat aircraft with a command and stability augmentation system[J].Journal of Aircraft,1976,14(4):368-374.
[7]BRENNER M J.Aeroservoelastic modeling and validation of thrust vectoring f/a-18 aircraft[R].NASA,1996.
[8]THOMPSON P M,KLYDE D H,FARHAT C,et al.Aeroservoelastic predictive analysis capability[C]//AIAAAtmospheric Flight Mechanics Conference and Exhibit.AIAA,2007.
[9]MUKHOPADHYAY V.Flutter suppression control law design and testing for the active flexible wing[J].Journal of Aircraft,1995,32(1):45-51.
[10]RODDEN W P,HARDERARDE.Aeroelastic addition to NASTRAN[R].NASA,3094.