飞机大迎角非线性动力学特性分析与控制
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摘要
本文结合分支分析方法与非线性控制律设计方法各自的优点,将二者融为一体,提出了一种非线性动力学特性分析与控制律设计的一体化设计思想,研究、建立了几种一体化设计方法,并将其应用到飞机大迎角飞行时机翼摇晃、惯性耦合、深失速和尾旋等非线性运动现象的分析、控制及过失速机动控制律设计研究中,具体工作包括:
结合分支分析方法和模糊控制方法的优点,提出了一种非线性动力学特性分析与控制律设计一体化方法,即BACTM-FLC方法,并应用到机翼摇晃的预测与抑制中,揭示了机翼摇晃的全局运动特性并成功抑制了机翼摇晃现象;
将常规分支分析方法的推广应用,即扩展分支分析方法应用到无侧滑滚转机动飞行,提出了一种可用于约束飞行的一体化设计方法,即EBA-FLC方法。研究了某机动飞机在惯性耦合作用下的滚转动力学特性,计算了在不同副翼偏角下的平衡面和分支面,揭示了在急滚过程中的跳跃现象,用扩展分支分析方法设计了开环分支控制律,在一定范围内实现了无侧滑滚转,在此基础上设计了模糊控制器,改善了无侧滑滚转的动力学特性,扩大了无侧滑滚转机动的范围,提高了最大滚转角速度;
应用分支分析方法对几种不同构型的T尾翼飞机的深失速特性进行了分析,直观地反映了深失速的改出特性,利用李雅普诺夫函数正定性和滑模面的稳定性与系统稳定性之间的关系,分别应用李雅普诺夫方法和滑模控制方法设计了深失速改出控制律,并对二者的工作机理进行了分析讨论;
推导了推力矢量飞机的数学模型,给出了某先进战斗机的气动力模型,用奇异摄动理论和动态逆方法设计了非线性飞行控制律,用加权最小二乘法对常规气动舵面和推力矢量舵面的分配进行了设计;
根据非线性动态逆方法可以通过反馈实现全局线性化,将系统转换为简单的线性系统的特点,在用分支分析方法对某先进战斗机进行分支分析,揭示其尾旋特性的基础上,应用非线性动态逆方法实现了振荡稳定的平尾旋的改出;
最后,应用非线性动态逆方法对几种典型的过失速机动进行了仿真,以综合反映大迎角下的非线性特性和控制律的作用效果。
In conjunction with the strongpoint of both bifurcation analysis methodology and nonlinear control law design methods, an integrative design idea of nonlinear dynamic characteristic analysis and control law design is put forward, several integrative design techniques are established. And these techniques are applied to both the analysis and control of the nonlinear motion phenomena of aircraft at high angle of attack, such as wing rock, inertia coupling, deep stall and spin, and the investigation of the post-stall control law design. The main research work is listed as follows:
An integrative method of nonlinear dynamic characteristic analysis and control law design, i.e. BACTM-FLC method, is development by integrating bidurcation analysis with fuzzy logical control. The wing rock of a delta wing is investigated by employed BACTM-FLC method, the global dynamic behavior of the wing rock is shown after the bifurcation analysis, and the wing rock phenomena is suppressed by the fuzzy logical controller successfully.
The extended bifurcation analysis(EBA), which is the extension of standard bifurcation analysis, is used to the zero side slip maneuver flight. And then a new integrative design technique, which is called EBA-FLC method and effective to constrained flight analysis, is developed. As an example, the rolling dynamic behavior of a light maneuverable aircraft is investigated. The equilibrium surface and the bifurcation surface at different aileron deflection are caculated and the jump phenomena during the fast rolling is shown. With the open-loop bifurcation control law, which is devised by EBA, the stable zero side slip flight in a range of aileron delfection came true. Based on this, a fuzzy controller is designed, and the dynamic behavior of the zero side slip rolling is improved, the range of stable zero side slip rolling is enlarged, and the maximum roll rate is enhanced.
The deep stall characteristic of several“T”tail configuration aircrafts are analyzed using bifurcation analysis, and the deep stall recovery characteristic is reflected clearly. According to the relationship between the system’s stability and the positive definiteness of Liapunov function & the stability of the slide mode surface, deep stall recovery control laws are designed with Liapunov method and slide mode control respectively, and their principle of work is discussed.
The mathematical modal of aircraft with vectoring thrust is established and the aerodynamic modal of an advanced fighter is given. A nonlinear flight control law is designed with singular perturbation theory and dynamic inversion method, and the general aerodynamic deflection and the thrust deflection is alloted by weighted least squre method.
The spin characteristic of an advanced fighter aircraft is shown clearly after the bifurcation analysis, and according to that the nonlinear dynamic inversion(NDI) method can make a simple linear system out of a nonlinear system by states feedback global linearization, the NDI method is employed to design the spin recovery control law, and the oscillatory stable flat spin recovery is achieved successfully.
In order to reflect the nonlinear dynamic behavor of aircraft at high-angle-of-attack and the effectiveness of the control law, the numerical simulation of four typical post-stall maneuvers is done with the NDI method at the end of this paper.
结合分支分析方法和模糊控制方法的优点,提出了一种非线性动力学特性分析与控制律设计一体化方法,即BACTM-FLC方法,并应用到机翼摇晃的预测与抑制中,揭示了机翼摇晃的全局运动特性并成功抑制了机翼摇晃现象;
将常规分支分析方法的推广应用,即扩展分支分析方法应用到无侧滑滚转机动飞行,提出了一种可用于约束飞行的一体化设计方法,即EBA-FLC方法。研究了某机动飞机在惯性耦合作用下的滚转动力学特性,计算了在不同副翼偏角下的平衡面和分支面,揭示了在急滚过程中的跳跃现象,用扩展分支分析方法设计了开环分支控制律,在一定范围内实现了无侧滑滚转,在此基础上设计了模糊控制器,改善了无侧滑滚转的动力学特性,扩大了无侧滑滚转机动的范围,提高了最大滚转角速度;
应用分支分析方法对几种不同构型的T尾翼飞机的深失速特性进行了分析,直观地反映了深失速的改出特性,利用李雅普诺夫函数正定性和滑模面的稳定性与系统稳定性之间的关系,分别应用李雅普诺夫方法和滑模控制方法设计了深失速改出控制律,并对二者的工作机理进行了分析讨论;
推导了推力矢量飞机的数学模型,给出了某先进战斗机的气动力模型,用奇异摄动理论和动态逆方法设计了非线性飞行控制律,用加权最小二乘法对常规气动舵面和推力矢量舵面的分配进行了设计;
根据非线性动态逆方法可以通过反馈实现全局线性化,将系统转换为简单的线性系统的特点,在用分支分析方法对某先进战斗机进行分支分析,揭示其尾旋特性的基础上,应用非线性动态逆方法实现了振荡稳定的平尾旋的改出;
最后,应用非线性动态逆方法对几种典型的过失速机动进行了仿真,以综合反映大迎角下的非线性特性和控制律的作用效果。
In conjunction with the strongpoint of both bifurcation analysis methodology and nonlinear control law design methods, an integrative design idea of nonlinear dynamic characteristic analysis and control law design is put forward, several integrative design techniques are established. And these techniques are applied to both the analysis and control of the nonlinear motion phenomena of aircraft at high angle of attack, such as wing rock, inertia coupling, deep stall and spin, and the investigation of the post-stall control law design. The main research work is listed as follows:
An integrative method of nonlinear dynamic characteristic analysis and control law design, i.e. BACTM-FLC method, is development by integrating bidurcation analysis with fuzzy logical control. The wing rock of a delta wing is investigated by employed BACTM-FLC method, the global dynamic behavior of the wing rock is shown after the bifurcation analysis, and the wing rock phenomena is suppressed by the fuzzy logical controller successfully.
The extended bifurcation analysis(EBA), which is the extension of standard bifurcation analysis, is used to the zero side slip maneuver flight. And then a new integrative design technique, which is called EBA-FLC method and effective to constrained flight analysis, is developed. As an example, the rolling dynamic behavior of a light maneuverable aircraft is investigated. The equilibrium surface and the bifurcation surface at different aileron deflection are caculated and the jump phenomena during the fast rolling is shown. With the open-loop bifurcation control law, which is devised by EBA, the stable zero side slip flight in a range of aileron delfection came true. Based on this, a fuzzy controller is designed, and the dynamic behavior of the zero side slip rolling is improved, the range of stable zero side slip rolling is enlarged, and the maximum roll rate is enhanced.
The deep stall characteristic of several“T”tail configuration aircrafts are analyzed using bifurcation analysis, and the deep stall recovery characteristic is reflected clearly. According to the relationship between the system’s stability and the positive definiteness of Liapunov function & the stability of the slide mode surface, deep stall recovery control laws are designed with Liapunov method and slide mode control respectively, and their principle of work is discussed.
The mathematical modal of aircraft with vectoring thrust is established and the aerodynamic modal of an advanced fighter is given. A nonlinear flight control law is designed with singular perturbation theory and dynamic inversion method, and the general aerodynamic deflection and the thrust deflection is alloted by weighted least squre method.
The spin characteristic of an advanced fighter aircraft is shown clearly after the bifurcation analysis, and according to that the nonlinear dynamic inversion(NDI) method can make a simple linear system out of a nonlinear system by states feedback global linearization, the NDI method is employed to design the spin recovery control law, and the oscillatory stable flat spin recovery is achieved successfully.
In order to reflect the nonlinear dynamic behavor of aircraft at high-angle-of-attack and the effectiveness of the control law, the numerical simulation of four typical post-stall maneuvers is done with the NDI method at the end of this paper.
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