The transfer alignment of SINS/GPS navigation system of a high-speed marine missile was investigated. With the help of the big acceleration of a high-speed missile, the transfer alignment was changed into a three-time...The transfer alignment of SINS/GPS navigation system of a high-speed marine missile was investigated. With the help of the big acceleration of a high-speed missile, the transfer alignment was changed into a three-time alignment. The azimuth alignment was coarsely finished in 10s in the first time alignment, the horizontal alignment was accurately and rapidly finished in the second time alignment, and the azimuth alignment was accurately finished in the third time alignment. Because the second time alignment and the third time alignment were finished by GPS after the missile was launched, the horizontal alignment and the second azimuth alignment got rid of the influence of the warship body flexibility deforming. The precision and rapidity of the horizontal alignment were prominently increased due to the vertical launch of the marine missile with the big acceleration. Simulation verifies the effectiveness of the proposed alignment method.展开更多
In the process of missile large attack angle reentry,there exist nonlinear,strong coupling uncertainty and multi-input-multi-output(MIMO)in the movement equations,so the traditional small disturbance faces difficultie...In the process of missile large attack angle reentry,there exist nonlinear,strong coupling uncertainty and multi-input-multi-output(MIMO)in the movement equations,so the traditional small disturbance faces difficulties.For such situations,the method of feedback linearization is adopted to control the complex system,and the control method based on the fuzzy adaptive nonlinear dynamic inversion decoupling control of missile is proposed in the paper.According to the principle of time-scale separation,the system is separated into fast loop and slow loop,the method of dynamic inversion is applied to them,and the method of adaptive fuzzy approach is adopted to compensate for the uncertainty of the fast loop.The simulation results denote the control method in the paper has a better tracing characteristic and robustness.展开更多
This paper proposes a novel integrated guidance and control(IGC)method combining dynamic surface control(DSC)and active disturbance rejection control(ADRC)for the guidance and control system of hypersonic reentry miss...This paper proposes a novel integrated guidance and control(IGC)method combining dynamic surface control(DSC)and active disturbance rejection control(ADRC)for the guidance and control system of hypersonic reentry missile(HRM)with bounded uncertainties.First,the model of HRM is established.Second,the proposed IGC method based on DSC and ADRC is designed.The stability of closed-loop system is proved strictly.It is worth mentioning that the ADRC technique is used to estimate and compensate the disturbance in the proposed IGC system.This makes the closed-loop system a better performance and reduces the chattering caused by lumped disturbances.Finally,a series of simulations and comparisons with a 6-DOF non-linear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method.展开更多
文摘The transfer alignment of SINS/GPS navigation system of a high-speed marine missile was investigated. With the help of the big acceleration of a high-speed missile, the transfer alignment was changed into a three-time alignment. The azimuth alignment was coarsely finished in 10s in the first time alignment, the horizontal alignment was accurately and rapidly finished in the second time alignment, and the azimuth alignment was accurately finished in the third time alignment. Because the second time alignment and the third time alignment were finished by GPS after the missile was launched, the horizontal alignment and the second azimuth alignment got rid of the influence of the warship body flexibility deforming. The precision and rapidity of the horizontal alignment were prominently increased due to the vertical launch of the marine missile with the big acceleration. Simulation verifies the effectiveness of the proposed alignment method.
文摘In the process of missile large attack angle reentry,there exist nonlinear,strong coupling uncertainty and multi-input-multi-output(MIMO)in the movement equations,so the traditional small disturbance faces difficulties.For such situations,the method of feedback linearization is adopted to control the complex system,and the control method based on the fuzzy adaptive nonlinear dynamic inversion decoupling control of missile is proposed in the paper.According to the principle of time-scale separation,the system is separated into fast loop and slow loop,the method of dynamic inversion is applied to them,and the method of adaptive fuzzy approach is adopted to compensate for the uncertainty of the fast loop.The simulation results denote the control method in the paper has a better tracing characteristic and robustness.
基金funded in part by the National Natural Science Foundation of China under Grant 91216304。
文摘This paper proposes a novel integrated guidance and control(IGC)method combining dynamic surface control(DSC)and active disturbance rejection control(ADRC)for the guidance and control system of hypersonic reentry missile(HRM)with bounded uncertainties.First,the model of HRM is established.Second,the proposed IGC method based on DSC and ADRC is designed.The stability of closed-loop system is proved strictly.It is worth mentioning that the ADRC technique is used to estimate and compensate the disturbance in the proposed IGC system.This makes the closed-loop system a better performance and reduces the chattering caused by lumped disturbances.Finally,a series of simulations and comparisons with a 6-DOF non-linear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method.
