Guindance Control Design Of Contact Attitude-track Measuring Device For Non-cooperative Target

The cooperation of non-cooperative goals is the precondition for space operations such as in-orbit service,maintenance and refueling of spacecraft.In this paper,by controlling the carrier spacecraft to track the target,close to a certain distance,launch the contact attitude-track measuring system(Nano Sat),after hitting the target,its surface,which is coated adhesive material,would adhere to the target's surface.after that,they become a combination,we can get accurate pose and track information,and then control.In this paper,based on the C-W relative orbit dynamics model,using the quaternion feedback PD control method to control the attitude of the spacecraft attitude,constant thrust control and other control methods are used to control the track of the spacecraft's orbit.When approaching,according to the current conditions to determine the launch angle and speed,launch the Nano Sat,it would hit the target and establish a stable connection.The research content of this paper can be divided into the following stages: the orbital transfer stage,the homo-orbit approximation stage,and the final Nano Sat launch stage.Tracking of the spacecraft in Leo,transfer to the target orbit,and in the rear target tracking,in close up to several meters behind the goal in the x axis direction,according to the current conditions,launch Nano Sat,and it would fly to the target.First of all,this paper analyses the movement of the spacecraft in the ontology system situations,the research of the spacecraft in space form of exercise,such as pulse motor,motor thrust and impulse motor,such as the different movements,including drift motion,mooring,orbit movement,etc.;Secondly,the Lambert problem of orbit transfer is analyzed,and the relationship between the time and velocity increment of orbit transfer and the semi-long axis of orbit transfer is discussed.Then,control the spacecraft attitude and orbit control respectively,control the attitude with the quaternion feedback PD control,control the orbital adopted three kinds of control methods,makes the tracking of the spacecraft in the body coordinate system of the target spacecraft,other relative conditions are 0,except the location of the x,and keep with the target position in the orbit and attitude is relatively static,keep the carrier tracking spacecraft at that point,for prelaunch preparations;Finally,using the spring ejection to launch Nano Sta,during the ejection process,the elastic may or not through the center of mass,so the Nano Sta may flip,through control the launch direction and speed,puts forward the Nano Sta hit non-cooperative target surface.This paper analyzes the motion of the process and deduces the constraint conditions that can hit the target surface and establish a stable connection.Because the target is uncooperative,compared with the real value,the earlier dataes of pose and track would have certain error,which would be considered on the impact of the task,the control effect and errors are analyzed,the methods of reducing errors are put forward.Through the study of the phase analysis of the whole process,task simulation,validation and the feasibility and the validity of the method and process to solve the non-cooperative target collaborative problems under control.