Research On The Penetration Behavior Of Kinetic Projectiles And Flying Spears Impacting Multi-layer Target

With the continuous increase of space debris,the space debris of the wrapped structure poses a huge threat to the spacecraft due to its special impact effect.At present,fruitful results have been achieved in the research of high-speed projectile damage to the spacecraft structure at home and abroad,but the kinetic energy projectile has not been damaged.The internal structure of the spacecraft is studied.At present,the active cleaning technology of space debris is still in the critical stage of technology.In order to solve the increasingly serious problem of space debris,it is necessary to explore more reliable space capture methods.Based on the research background of the end point effect of projectiles on space targets,in this paper,the kinetic energy damage of the kinetic energy projectile hitting the multi-layer target plate and the anchoring characteristics of the spear to the target plate are respectively carried out.This paper is used to solve the practical engineering application of first damage and then capture.Firstly,a kinetic energy damage projectile configuration that wraps multiple damage elements is proposed,which can damage the internal structure by regionally dispersing the damage elements after penetrating the outer wall of the spacecraft.And based on the structural characteristics of the artificial satellite,it is equivalent to a multi-layer target plate.Then the ground damage test was carried out to verify,and the finite element dynamic simulation of the test process is carried out,and the consistency between the simulation results and the test results is qualitatively and quantitatively compared.It is found that the projectile can complete the damage task when the velocity of the projectile is 325m/s,and the lateral effect and low penetration of the kinetic energy projectile are revealed.Second,based on the verified finite element simulation,the influence of the shape of the damage element,the initial velocity of the launch,and the impact angle on the damage characteristics was deeply studied.It is found that the damage effect of filling the spherical damage element on the internal structure is the best,and the effect of filling the cube damage element to penetrate the outer shell is the best.The launch velocity that meets the requirements of the damage mission is 325±25m/s,and the kinetic energy projectile can adapt to a small angle of impact.The theoretical model of the kinetic energy projectile impacting the aluminum honeycomb sandwich panel(satellite outer wall)is established,and combined with the simulation,it is obtained that the ballistic limit speed is about 150m/s.After damage,the target needs to be captured.A space non-cooperative target capture method based on spear anchoring is proposed,the integrated multi-level barbed flying spear structure is designed,and it can be fired sequentially from the same launcher as the kinetic projectile.In order to explore the feasibility of capturing the flying spear,the principle verification test and finite element dynamic simulation of the flying spear anchoring the aluminum alloy target plate were carried out.And the ballistic data under different working conditions were obtained by using the simulation model after the test verification.In order to guide engineering practice,a theoretical model of the flying spear hitting the target plate is established to predict the ballistic limit velocity and residual velocity of the flying spear hitting aluminum plates with different thicknesses,which provides theoretical guidance for future flying spear capture experiments and tasks.Finally,in order to study the adaptability of the spear to different targets,the typical targets captured by the spear and their properties are analyzed in detail.The last stage of the launch vehicle is selected as the on-orbit demonstration target captured by the spear.By studying the effects of the spear’s initial velocity,impact angle,and target plate motion on the anchoring characteristics,it is concluded that the optimal capture speed is 70m/s,and the ricochet phenomenon will occur when the impact angle is large.And the spear is relatively insensitive to the target movement posture.The study also found that the flying spears can be anchored on aluminum honeycomb sandwich panels,carbon fiber laminates,CFRP skin-aluminum honeycomb sandwich panels,which indicates that the flying spears have the possibility of anchoring and capturing space satellites.