空间碎片超高速撞击下太阳电池阵伏安特性

Hypervelocity impact on volt-ampere characteristic of solar arrays by using two-stage light gas gun

太阳电池阵是航天器的电力来源,时常受到微流星体和空间碎片撞击而损伤,导致太阳电池阵输出功率下降.采用二级轻气炮对航天器太阳电池阵开展了空间碎片超高速撞击地面模拟试验,研究了不同撞击速度、弹丸直径、撞击点位置工况下太阳电池阵伏安特性的衰减规律.共进行了12次试验,其中5次因弹托撞击试件而无效,7次试验数据有效.试验结果显示,弹丸的直径和撞击速度、撞击位置三者均对伏安特性影响较大,地面模拟试验与在轨飞行试验产生的损伤形貌符合良好.通过数据分析了电池阵失效面积与剥落区面积、穿孔面积、弹丸动能、撞击位置四者之间的关系.研究发现,电池阵失效面积与剥落区面积两者之比介于7-37,电池阵失效面积与穿孔面积两者之比介于50-150.撞击在电池片中心区域,失效面积明显高于撞击在电池片边缘或者连接处.电池阵失效面积△S_(SA)与动能E(E=πρd^(3)v^(2)/12)的立方根比较吻合.为了建立功率损失面积与弹丸直径和撞击速度的准确方程,首先假设三者存在幂指数关系,再通过数据拟合方法求解待定系数,最终建立了适用于国内太阳电池阵的功率损失△P_(max)方程和△S_(SA)方程.当撞击在电池片中心区域△P_(max)=0.047dv^(2/3)时,△S_(SA)=260dv^(2/3).当撞击在电池片边缘或者连接处△P_(max)=0.033dv^(2/3)时,△S_(SA)=180dv^(2/3).方程预测偏差在±13.3%以内,平均偏差为7.6%.该方程可用于描述在0°撞击角条件下电池阵功率损失或失效面积两者与弹丸的直径、撞击速度、撞击位置的函数关系.本文的研究方法对我国航天器太阳帆板超高速撞击环境下性能退化评估有借鉴意义,所建立的功率损失方程和失效面积方程,能够预测空间碎片造成的太阳电池阵的功率下降规律和失效面积规律,对我国航天工程实践具有重要的工程应用价值.

Solar array is a power source of spacecraft,which is often damaged by the impact of micrometeoroids and space debris,resulting in the decrease of output power of solar array.The degradation law of volt-ampere characteristic for spacecraft solar arrays under orbital debris hypervelocity impact is investigated by using a two-stage light gas gun.The volt-ampere characteristics of the solar arrays under different impact velocities,projectile diameters and impact positions are studied.A total of 12 shots are carried out,of which 5 shots are invalid due to the impact of the projectile carrier on the specimen,and 7 shots are valid.The experimental results show that the diameter,impact velocity,and impact position of the projectile all have a great influence on the volt-ampere characteristics,and the damage morphology generated by the ground simulation test is in line with the in-orbit flight test results.The relationship between the failure area of the solar arrays and the area of the spalling area,the perforation area,the kinetic energy of the projectile as well as the impact position are analyzed.It is found that the ratio of failure area to peeling area is between 7 and 37,and the ratio of failure area to perforation area is between 50 and 150.The failure area in the center of the solar cell is significantly larger than that on the edge or at the connection of the solar cell.Failure area of solar array△S_(SA)and the cube root of kinetic energy E(E=πρd^(3)v^(2)/12)is consistent.In order to establish the accurate equation of power loss area with projectile diameter and impact velocity,in this paper it is assumed that there is a power exponential relationship among them,and then solve the undetermined coefficient by the data fitting method.Finally,we establish the power loss△P_(max)equation and failure area△S_(SA)equation suitable for domestic solar array.The equation will be△P_(max)=0.047dv^(2/3),△S_(SA)=260dv^(2/3)when the impact occurs in the center of the cell,and△P_(max)=0.033dv^(2/3),△S_(SA)=180dv^(2/3)when the impact occurs on the edge or at the connection of the solar cell.The prediction error of the equation is in a range of 13.3%,and the average deviation is 7.6%.This equation can be used to describe the function relationship between the power loss or failure area of the solar arrays and the diameter,impact velocity and impact position of the projectile under the condition of 0°impact angle.The research method in this paper can be used as a reference for the performance degradation assessment of Chinese spacecraft solar panels under the hypervelocity impact of orbital debris,the established power loss equation and failure area equation can predict the law of power decline and failure area of solar array caused by space debris,and the results have important application value for Chinese aerospace engineering.