Guidance Method In Flying Aircraft

Since the 21 st century,with the continuous development of science and technology,people for the research of ballistic missile technology more mature,there are many countries on the development of ballistic missiles more and more attention.Strengthen the missile penetration ability has become particularly important,you can guarantee their own strategic strike capability,to maintain the existing strategic situation balance.The focus of this paper is on the guidance method of flying aircraft.Firstly,the research status of ballistic missile penetration strategy and some guidance methods are introduced.The Lambert problem is derived from the two-point boundary value problem.Some basic characteristics of the Lambert problem are discussed,its orbital type is determined,the time is obtained by the time equation,and the velocity of the engine is controlled by the velocity gain guidance method.The aircraft is sent into the predetermined elliptical orbit The And the simulation analysis is carried out to verify the effectiveness of the algorithm.Then,when the missile enters the predetermined elliptical orbit under the influence of the Lambert guidance,it will then release the escalator,which will study the relative motion of the aircraft and the missile.First,we need to establish the relative motion equation between the two,and then based on the relative motion equation research Hill guidance method,the Hill guidance is achieved by the speed gain method.This also introduces a new problem,that is,elliptical orbit hover control,this paper uses variable structure control.The algorithm is also simulated based on MATLAB.Finally,the attitude control of the missile is studied.In this paper,the dynamic characteristics of the missile's attitude control system are neglected,that is,the attitude of the missile can track its own attitude command without inertia.And with the aircraft from the missile separation,all of its guidance control process must consider the dynamic characteristics of attitude control system.Firstly,the motion model based on quaternion is established,and then the attitude control tracking problem is described based on the quaternion of error.Finally,the variable structure control method is used to control the attitude.The method is also applied to practice,and simulation analysis.