基于试飞数据的飞机大迎角气动力参数辨识
摘要
为解决大迎角状态下飞机气动力模型难以建立的问题,本文基于局部线化代替非线性概念,探索了利用大迎角飞行试验数据辨识飞机空气动力参数问题。在准定常假设条件下,运用迎角分割算法对某型飞机的大迎角试飞数据进行数据分析预处理,用最小二乘回归方法验证了上述大迎角参数辨识的思想,取得了较好的结果,为进一步开展大迎角参数辨识技术的工程应用奠定了基础。
引文
[1]张婉鑫,朱纪洪.大迎角非定常气动参数辨识研究[J].清华大学学报(自然科学版),2017,57(7):673-679.
[2]范晶晶,阎超,李跃军.飞行器大迎角下俯仰静、动导数的数值计算[J].航空学报,2009,30(10):1846-1850.
[3]陈海萍,高正红.大迎角非定常气动力数学模型研究[J].飞行力学,2008(5):10-12,16.
[4]CHEN Zhen, LI Shuo, Pan E. Optimal constant-stress accelerated degradation test plans using nonlinear generalized wiener process[J].Mathematical Programming in Engineering.2016,2016;9283295-1-9283295-11.
[5]ZHANG Wanxin, ZHU Jihong. Modification of recursive least squares algorithm for linear time-varying systems[C]//Proceedings of the 35th Chinese Control Conference. Chengdu,China:IEEE;2016;2151-2153
[6]Ghoreyshi M, Cummings R M, Da R A, et al. Transonic aerodynamic load modeling of X-31 aircraft pitching motions[J]. AIAA Journal. 2013,51(10),2447-2464.
[7]Gordon, B W.,Pakmehr, M, Rabbath, C A. State-space modeling and identification of delta wing vortex-coupled roll dynamics[J].Journal of Aircraft,2009,46(1):36-45
[2]范晶晶,阎超,李跃军.飞行器大迎角下俯仰静、动导数的数值计算[J].航空学报,2009,30(10):1846-1850.
[3]陈海萍,高正红.大迎角非定常气动力数学模型研究[J].飞行力学,2008(5):10-12,16.
[4]CHEN Zhen, LI Shuo, Pan E. Optimal constant-stress accelerated degradation test plans using nonlinear generalized wiener process[J].Mathematical Programming in Engineering.2016,2016;9283295-1-9283295-11.
[5]ZHANG Wanxin, ZHU Jihong. Modification of recursive least squares algorithm for linear time-varying systems[C]//Proceedings of the 35th Chinese Control Conference. Chengdu,China:IEEE;2016;2151-2153
[6]Ghoreyshi M, Cummings R M, Da R A, et al. Transonic aerodynamic load modeling of X-31 aircraft pitching motions[J]. AIAA Journal. 2013,51(10),2447-2464.
[7]Gordon, B W.,Pakmehr, M, Rabbath, C A. State-space modeling and identification of delta wing vortex-coupled roll dynamics[J].Journal of Aircraft,2009,46(1):36-45