占据式聚能装药射流形成的数值模拟及试验研究

为了研究空间超高速碎片云对飞行器防护结构的影响,采用AUTODYN软件对占据式聚能装药射流形成过程进行了数值模拟。运用正交分析法研究了铝质药型罩锥角、壁厚及占据体到药型罩锥顶距离对头部射流速度的影响并得到最优方案。测速试验表明,该方案能提供试验研究所需要的射流速度大于10 km/s的碎片云。     

真空环境下空间碎片超高速撞击试验研究

本文介绍了空间碎片的超高速发射技术及微小碎片的地面模拟试验.我国首次在真空环境下将激光驱动飞片技术应用到空间碎片的研究中.利用13.5 J的激光能量将厚60μm,直径φ2 mm的铝碎片驱动出去,速度可达3.2 km/s,并完成了微小碎片对航天器温控涂层和蜂窝板的损伤试验.     

铝双层板结构撞击损伤的板间距效应实验研究

为了研究空间碎片对航天器防护结构的超高速撞击损伤特性,采用二级轻气炮发射球形弹丸,对铝双层板结构进行了超高速撞击实验研究.弹丸直径为3.97 mm,撞击速度分别为(2.58±0.08)km/s、(3.54±0.25)km/s和(4.35±0.11)km/s,板间距为10~100 mm.实验得到了铝双层板结构在不同撞击速度区间的后板损伤模式.结果表明,弹丸撞击速度一定时,后板弹坑分布随前后板间距的不同而不同.前板背面返溅影响区和后板弹坑分布区随板间距的增大而增大,各弹坑分布区扩散角随板间距的增大而减小.     

铝弹丸超高速正撞击铝合金薄板产生溅射物云特性研究

为研究微流星体或空间碎片超高速正撞击航天器表面缓冲结构产生的溅射物形态和分布特性,采用二级轻气炮驱动铝弹丸进行超高速撞击实验。铝弹丸超高速正撞击铝合金薄板首先溅射高温微粒子或甚至是微小熔滴等闪光热源,随后是由金属粉尘及低速碎片粒子构成的溅射物云团簇。正撞击产生的溅射云团簇在空间呈环锥形状分布,3~5 km/s速度范围内,撞击速度越高,分布越密集。利用HSFC-PRO超高速相机捕捉到撞击初始阶段产生的溅射物在不同时刻的影像演化,通过跟踪影像中溅射闪光热源和溅射云团簇最前端的轮廓估算其一维膨胀速度。非球弹丸撞击时的姿态偏转可能对溅射物云团簇的分布有较大影响。     

圆柱形长杆超高速正碰撞薄板结构破碎效应

超高速碰撞多层板结构破碎效应研究对空间碎片防护及动能武器毁伤效应研究有着重要意义。采用ANSYS/AUTODYN程序的SPH方法,对超高速碰撞碎片云的形成过程进行了数值模拟,某典型时刻一次及二次碎片云形貌的数值模拟结果与实验结果吻合较好,验证了计算方法和模型参数的正确性。在此基础上采用数值模拟方法,对钨合金、轧制均质装甲(Rolled Homogeneous Armor,RHA)及LY12铝三种材料的圆柱形弹体超高速碰撞薄板的破碎规律进行了研究,基于量纲分析方法得出了弹体破碎长度随弹靶材料特性、弹靶尺寸及初始撞击速度变化的关系式。并研究了钨合金及RHA两种材料的长杆弹对八层RHA板结构的超高速碰撞效应。     

含能活性材料防护结构超高速撞击特性数值模拟研究

含能活性材料超高速撞击数值模拟研究对于新型空间碎片防护机理探索研究具有重要意义。采用AUTODYN动力学仿真程序,基于改进的Lee-Tarver点火增长模型,在验证计算模型有效性的基础上,开展球形弹丸超高速撞击含能活性材料防护结构数值模拟研究,对弹丸临界破碎速度、碎片云形貌特征及后墙损伤等进行分析。给出了铝合金弹丸超高速撞击PTFE/Al含能活性材料防护屏的临界破碎速度公式,得到弹丸直径、撞击速度和含能活性材料防护屏板厚对碎片云特征参数的影响规律,进一步揭示了含能活性材料防护结构超高速撞击条件下的新型防护机理。     

球形弹丸超高速碰撞破碎特性

讨论超高速碰撞数值模拟方法,用ANSYS/AUTODYN程序的SPH方法对球形弹丸超高速撞击时弹丸破碎、碎片云形成过程进行数值模拟并与实验结果比较,验证计算方法及模型参数的正确性。在此基础上研究钨合金、轧制均质装甲(Rolled Homogeneous Armor,RHA)两种材料球形弹丸破碎的临界速度随比值(ts/dp,ts为靶板厚,dp为弹丸直径)的变化规律,给出两种材料超高速碰撞时应变率及平均碎片尺寸随撞击速度的变化曲线以及碎片质量分布规律。     

椭球弹丸超高速撞击防护屏碎片云数值模拟

低地球轨道的各类航天器易受到微流星体及空间碎片的超高速撞击.本文采用AUTODYN软件进行了椭球弹丸超高速正撞击及斜撞击防护屏碎片云的数值模拟.给出了三维模拟的结果.研究了在相同质量的条件下,不同长径比椭球弹丸以不同速度和入射角撞击防护屏所产生碎片云的特性,并与球形弹丸撞击所应产生的碎片云特性进行了比较.结果表明:在相同的速度下,不同长径比椭球弹丸撞击的碎片云形状、质量分布和破碎程度是不同的,随撞击入射角的增加弹丸的破碎程度增大,滑弹碎片云的数量增加;随撞击速度的增加,弹丸的破碎程度也增加.     

Nomex Kevlar平纹织物超高速撞击本构模型开发

为了研究Nomex-Kevlar平纹织物对空间碎片的超高速撞击力学特性, 运用LS-DYNA本构模型二次开发技术开发了Nomex-Kevlar平纹织物在超高速撞击条件下的带最大应力失效标准的线弹性正交各向异性本构模型, 并定义了Nomex-Kevlar平纹织物在超高速撞击条件下的Gruneison状态方程参数。运用光滑粒子流体动力学方法和有限元方法建立了与NASA试验工况相同的Al-2017-T4球形弹丸以6.84km/s速度斜向30°撞击Nomex-Kevlar平纹织物的数值分析模型。仿真结果与试验结果的比较表明, 本文中开发的本构模型以及建立的数值分析模型可以准确描述Nomex-Kevlar平纹织物的超高速撞击力学特性。      

大口径网面空间可展开天线结构撞击动力响应研究

在轨运行的大口径空间可展开天线可能会遭遇空间碎片的高速撞击,这严重威胁了星载天线的安全服役。为研究空间网面可展天线支承结构及抛物面索网在高速撞击时的动力响应,选用ANSYS/AUTODYN有限元软件,建立大口径空间网面可展开天线动力学撞击仿真模型,模拟天线展开锁定时遭遇2.5 mm～7.5 mm的空间碎片撞击的全过程动力响应。考虑1.0 km/s～15.0 km/s的撞击速度和不同撞击位置工况下,天线结构的整体动力响应、关键杆件及抛物面索网损伤状态以及结构整体变形性能。结果表明：空间可展天线结构受微小空间碎片撞击的结构响应过程可分为局部振动、拉索约束以及整体振动三个阶段,撞击点越靠近天线形心,结构响应越明显,结构的平均变形越大;随着撞击速度增大,可展天线的结构平均变形表现为先增加后减小趋势,当撞击速度大于12.5 km/s时,天线受撞击的影响区域逐渐缩小;空间可展天线受微小空间碎片高速撞击时整体形面变形不可忽视,可为后续天线结构防护及易损性分析提供参考。     

Crater distribution on the rear wall of AL-Whipple shield by hypervelocity impacts of AL-spheres

All spacecraft in low orbit are subject to hypervelocity impact by meteoroids and space debris, which can in turn lead to significant damage and catastrophic failure. In order to simulate and study the hypervelocity impact of space debris on spacecraft through hypervelocity impact on AL-Whipple shield, a two-stage light gas gun was used to launch 2017-T4 aluminum alloy sphere projectiles. The projectile diameters ranged from 2.51 mm to 5.97 mm and impact velocities ranged from 0.69 km/s to 6.98 km/s. The modes of crater distribution on the rear wall of AL-Whipple shield by hypervelocity impact of AL-spheres in different impact velocity ranges were obtained. The characteristics of the crater distribution on the rear wall were analyzed. The forecast equations for crater distribution on the rear wall of AL-Whipple shield by normal hypervelocity impact were derived. The results show that the crater distribution on the rear wall is a circular area. As projectile diameter, impact velocity and shielding spacing increased, the area of crater distribution increased. The critical fragmentation velocity of impact projectile is an important factor affecting the characteristics of the crater distributions on the rear wall.     

Characterization of prompt flash signatures using high-speed broadband diode detectors

Impact flash is a brief, intense flash of light released when a target is impacted by a hypervelocity particle. It is caused by emissions from a jet of shocked material which is thrown from the impact site. Impact flash phenomenology has been known for decades, and is now being considered for applications where remote diagnostics are required to observe and diagnose impacts on satellites and space craft where micrometeoroid and orbital debris impacts are common. Additionally, this phenomena and remote diagnostics are under consideration for missile defense applications. Currently, optical signatures created from hypervelocity impact can be utilized as the basis for detectors (spectrometers, pyrometers), which characterize the material composition and temperature. More recent interest has focused on study of hypervelocity impact generated debris and the physics of the associated rapidly expanding and cooling multiphase debris cloud. To establish this capability technically in the laboratory, we have conducted a series of experiments on a two-stage light gas gun at impact velocities ranging from 6 to 19 km/s, which is representative for light emissions resulting from hypervelocity impacts in space. At these high impact velocities jetting is no longer the dominant mechanism for observed impact flash signatures. The focus of this work is to develop fast, inexpensive photo-diodes for use as a reliable prompt flash, and late time radiating debris cloud diagnostic to: (a) characterize material behavior in the shocked and expanding state when feasible; (b) ascertain scaling of luminosity with impact velocity; (c) determine the temperature of the impact flash resulting from radiating emissions when multiple silicon diodes are used in conjunction with narrow band pass filtering at specific wavelengths as a pyrometer. The results of these experiments are discussed in detail using both a metallic target, such as aluminum, and an organic material such as Composition-B explosive.     

Micrometeroid and debris impact test on space station bumper

To design the micrometeoroid and debris protection bumper of the outboard structure space station module, we made a two-stage helium light gas gun and carried out hypervelocity impact tests which simulated micrometeroid and debris impacts on space station. Fundamental characteristics of hypervelocity impact phenomena was investigated, for a projectile mass 0.45gr to 1.5gr, impact velocity about 4km/sec and aluminum-alloy bumpers. When the bumper is of double-sheet type, there exists an optimal front sheet thickness that causes melting of the front sheet. However, for thin front sheets, penetration occurs, and for thick front sheets, spall fracture occurs. In addition to the impact tests, the computational simulation of the typical test result was carried out using the PISCES code with the Tillotson constitut ive equation of aluminum-alloy. The computational sumulation result had a good agreement with the test result.     

Laboratory simulation of hypervelocity debris

A series of hypervelocity damage experiments were performed on spacecraft materials in order to simulate micro-size space debris traveling at 3 to 8 km/s. Two types of impact simulations were investigated: high-power pulsed laser and laser-launched micro-flyer plate. In the first case a laser was used to generate a high-pressure shock wave which propagated into the target by means of rapid ablation of the target surface. The second case used the same laser to accelerate micro-flyer plates at a target. The laser-ablation technique and the apparatus used to propel the micro-flyer plates were compatible with a space environmental chamber equipped with instrumentation capable of analyzing the vapor ejected from the sample. Data obtained from two separate damage effects were of interest in this study: the vapor blow-off produced by the impact and the mechanical damage to the target. The value of the data obtained from both simulation methods was evaluated in terms of likeness to actual space debris damage.

Data for this work were obtained from polysulfone resin and a graphite polysulfone composite. Polysulfone was selected because it was flown on the Long Duration Exposure Facility (LDEF) satellite which spent several years in low earth orbit and experienced many space debris impacts.

The chemistry of the vapor produced by the two simulation techniques was analyzed with a time of flight mass spectrometer (TOFMS) which measured changes in the vapor chemistry as a function of time after impact, obtained a velocity measurement of the vapor, and estimated surface temperature immediately after impact using dynamic gas equations. Samples of the vapor plume were also captured and examined by transmission electron microscopy (TEM).

The mechanical damage effects caused by the simulation methods on a graphit polysulfone composite and a polysulfone resin were studied. Impact craters were examined under optical and scanning electron microscopes (SEM). Based on the two damage effect criteria the micro-flyer method proved to be a useful way to simulate hypervelocity impact of space debris. The laser-ablation method however, had shortcomings and required drastic compromises in the set criteria.     

Response of composite materials to hypervelocity impact

Investigation of composite materials response to hypervelocity impact by space debris has been carried out. In order to simulate hypervelocity impact, a unique laser driven flyer plate (LDFP) system was used, generating hypervelocity debris with velocities of up to 3 km/s. The materials studied in this research were Kevlar 29/epoxy and Spectra1000/epoxy thin film micro-composites (thickness of about 100 μm). Both Spectra and Kevlar fibers are used in long-duration spacecraft outer wall shielding to reduce the perforation threat. The micro-mechanical response of different composites was studied and correlated to the fiber, the matrix and the fiber/matrix interface properties. Visual and microscopic examinations of the damaged area identified fiber debonding as the prevailing failure mechanism. On the basis of a simple energy balance model it can be stated that for Spectra/epoxy composite the dominant mechanism is new surface creation, whereas for Spectra surface-treated fibers/epoxy the fiber pull out is the dominant mechanism. For Kevlar/epoxy fiber, pull out mechanism plays an important role.     

空间碎片高速撞击的数值模拟方法评述

计算机数值模拟是实现空间碎片撞击效应地面模拟的重要手段之一。撞击速度增加,撞击的物理机制和效应将发生改变,计算机数值模拟方法也应随之丰富和全面。介绍了基于有网格和无网格方法的高速撞击数值模拟发展历程,并针对数值模拟中常用的有限元法和SPH法进行了分析比较,阐述了高速撞击计算机模拟中无网格法的计算优势,并提出量子力学在未来无网格法数值模拟中的可能应用。为空间碎片高速撞击更加真实可靠的数值模拟提供参考。     

Generation of transient vibrations on aluminum honeycomb sandwich panels subjected to hypervelocity impacts

This paper presents the results of a set of experiments aimed at discovering the main features of impact-induced vibrations on all-aluminum honeycomb sandwich panels, representative of the GOCE satellite's top floor, which is exposed to the orbital debris environment. The activity focused on the characterization of the vibrations induced in the vicinity of internal payloads by hypervelocity impacts occurring on the vehicle's external shell. More than 30 tests were realized by launching 0.8–2.3 mm aluminum projectiles in the velocity range 4–5.5 km/s on targets with tri-axial accelerometer assemblies mounted on both the front and rear face of the panel, at a nominal distance of 150 mm from the impact point. It was found that a hypervelocity impact produces in both the front and rear side of the sandwich panel a vibration environment which can be described through the shock response spectrum (SRS) of three different types of waves that can be distinguished on the basis of the acceleration direction: out-of-plane, in-plane longitudinal and in-plane shear. The influence of projectile mass and velocity on SRS appeared to vary with frequency, with the most significant difference in the range between ∼10³ and ∼10⁴ Hz. The results of whole experimental set were used to derive an interpolation law through standard techniques of nonlinear fit. The empirical equation obtained makes it possible to predict the near-field vibration environment produced by hypervelocity impacts with debris having given size and velocity, reproducing all the test data with an average uncertainty of ±6 dB.