Research On The Calculation Method Of Large Space Debris Mechanical Impact Racemic Posture

Large space debris refers to the terminal stage of a failed satellite or rocket that has lost its attitude adjustment ability in space.Since it cannot be controlled and position adjusted manually,it is also called a non-cooperative target.Since the beginning of the new century,the frequent space activities of the major aerospace countries have continuously increased the amount of space debris.Studies by NASA and others suggest that space debris management should begin by removing large pieces of debris from low and geosynchronous orbits,the only viable way to reduce the threat of spacecraft impact.Because large space debris stays in space for a long time,interference factors in space will have a continuous impact on space debris,so space debris often presents a complex triaxial rotation motion accompanied by rolling.Direct capture could cause space debris to collide violently with the robotic arm,creating more space debris.Therefore,it is necessary to deal with space debris before capturing it.In this paper,for the problem of large space debris desorption,the attitude dynamics formula was derived,the attitude dynamics model of space debris was established,and the calculation method of mechanical impact pose was proposed.A reference coordinate system was established,and the euler angle is used to describe the attitude of the object.The angular momentum and precession angular velocity of space debris are analyzed.The attitude dynamics equation of space debris racemization was derived.Under the condition that the motion state of space debris was known,the angular momentum vector was searched based on the angular momentum vector synthesis method,and the space debris active desorption method was studied based on the elimination of angular momentum.The impact pose is selected so that the moment of the couple generated during the impact will not produce overturning torque on the space debris,but only produce impedance effect on its combined angular momentum.The dynamic model of mechanical impact active desorption of space debris was established and motion parameters were input.The variation curves of space debris triaxial angular momentum,resultant angular momentum,triaxial angular velocity,nutation Angle and precession angular velocity are obtained from the simulation experiment.Experimental data show that the triaxial angular momentum and triaxial angular velocity of space debris decrease at the same time and the decrease proportion is almost the same,the precession angular velocity decreases and the change period of nutation Angle becomes longer,reaching the expected results of space debris racemization.The simulation results show that using the de-spinning strategy in this paper for large space debris de-spinning can effectively reduce the triaxial angular momentum and triaxial angular velocity of space debris,and the direction of the combined angular momentum axis before and after impact remains unchanged,thus improving the execution efficiency of the de-spinning process and shortening the de-spinning time.The de-racking strategy in this paper provides a new guiding idea for mechanical impact de-racking and provides a theoretical basis for actual de-racking missions in space.