空间碎片超高速撞击下充气压力容器破损预报
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摘要
随着人类航天活动的日趋频繁,空间碎片环境日益恶化,严重地威胁着在轨航天器的安全运行。航天器上的各种压力容器是航天器用来储存液体或含能高压气体的部件,在空间碎片超高速撞击下,可能导致其发生泄漏,甚至发生爆炸等灾难性破坏,使航天器任务提前终止或失效。目前,虽然已对超高速撞击下压力容器破损过程进行了有益的探索,但通常定性分析多于定量计算,并且尚未针对在超高速撞击下压力容器的损伤破坏行为建立出一个相对系统的理论预报模型。压力容器的损伤破坏特性及其失效预报分析是航天器空间碎片风险评估与防护结构设计的一个重要关键技术和前沿课题。
本文以航天器上的圆柱形充气压力容器为研究对象,以速度范围为1.0km/s~7.0km/s的球形铝制弹丸模拟空间碎片,采用数值模拟和理论分析相结合的技术手段,对空间碎片超高速撞击充气压力容器的破损过程、破损机理开展系统研究,建立了包括容器前壁破损预报及容器后壁破损预报的压力容器破损预报模型,并与实验结果进行了对比。
应用AUTODYN-2D,采用Lagrange方法确定了压力容器前壁穿孔尺寸、裂纹尺寸与气体压力、撞击条件的关系。根据压力容器前壁穿孔的形态特征,将其简化为含双裂纹的圆孔,建立了压力容器前壁穿孔的简化模型。基于线弹性断裂力学的Bueckner原理,建立了前壁穿孔尺寸、裂纹尺寸及气体压力与裂纹应力强度因子之间的关系式。应用该关系式,并基于断裂力学的K准则,对在气体介质压力作用下压力容器前壁的断裂行为进行了分析,建立了压力容器前壁破损预报模型,获得了压力容器前壁发生灾难性破坏的临界条件。研究结果表明,压力容器前壁穿孔孔边是否有裂纹裂纹产生对容器前壁发生灾难性破坏的临界气体压力有较大的影响。
应用AUTODYN-2D,采用SPH方法对前壁撞击穿孔而产生的二次碎片与内充气体介质的相互作用过程建立计算模型并进行了数值模拟分析,通过与实验结果相比较,验证了数值模拟方法的有效性。根据二次碎片形态特点,建立了不同弹丸破碎模式的二次碎片初始模型。在此基础上,应用流体动力学、冲击波及气固两相流理论,结合数值模拟研究结果,对不同弹丸破碎模式下二次碎片与气体介质的相互作用过程进行了分析,建立了二次碎片与气体介质的相互作用模型,并通过与数值模拟结果、实验结果相比较验证了模型的有效性,确定了压力容器内二次碎片的运动特性及气体冲击波的传播规律。
针对不同弹丸破碎模式,根据已获得的二次碎片运动特性及气体冲击波的传播规律,将二次碎片及气体冲击波对容器后壁的作用简化为局部均布冲击载荷对固支圆板的作用,建立了不同弹丸破碎模式下二次碎片及气体冲击波对压力容器后壁作用的简化模型,获得了局部冲击载荷的作用半径及在二次碎片与冲击波共同作用下容器后壁产生的初速度。基于前人对局部冲击载荷作用下圆板的破坏分析,确定了在二次碎片与气体冲击波作用下容器后壁产生穿孔的临界条件及穿孔半径。将穿孔半径等效为贯穿直裂纹,根据线弹性断裂力学,并考虑容器壁曲率的影响,获得了容器后壁发生灾难性破坏的临界条件。
最后,集成上述研究成果建立了超高速撞击下充气压力容器的破损预报模型,并讨论了预报模型的适用范围。针对具体的实验工况应用建立的预报模型进行了计算,给出了预报流程,并通过与实验结果的比较验证了预报模型的有效性。
本文建立的球形弹丸超高速撞击充气压力容器破损预报模型对航天器防护结构的设计具有指导意义,揭示了压力容器在超高速撞击下的破损机理,为压力容器类部件空间碎片撞击风险评估及开发研制先进的压力容器防护方案具有工程应用参考价值。
With the unceasing development of space activity, the total number of space debris is ever increasing, which greatly threatens orbiting space vehicles. Spacecraft often employ pressure vessels to contain gases and liquids. A pressure vessel subjected to hypervelocity impact by meteoroids and space debris can represent a significant hazard to a space vehicle because of the energy stored within the vessel. Vessel can occur venting through the impact hole. Catastrophic rupture of the vessel can send high-velocity fragments in all directions and secondary debrisary damage becomes a serious threat to the spacecraft. The damage characteristic of pressure vessel by space debris and prediction of catastrophic failure are the important basic of shield structure design and risk evaluation of spacecraft in space debris environment.
At present, the quantitative investigation on damage process of pressure vessel under hypervelocity impact is still very limit. Systemic prediction model for damage and failure of pressure vessels under hypervelocity impact has not built.
Based on the background mentioned above, this paper investigates the damage process of pressure vessel under hypervelocity impact. The impact velocity is ranging from 1.0 km/s to 7.0 km/s, the impact condition limits to fragmentation and melt of materials. The gas-secondary debris interaction process and propagation process of shock wave are investigated, and the prediction model for damage and failure of pressure vessels under hypervelocity impact is built.
Lagrange methods in AUTODYN-2D is used for investigate the relationships between impact hole size, crack size, gas pressure and impact conditions. According to characteristics of impact hole, initial model of secondary debris is built. The model is presented by postulates the existence of two-radial cracks that emanate at the boundary of a circular hole. The relationships of impact hole size, crack size, gas pressure and the stress intensity factor which is determined by simplified linear elastic fracture mechanics are obtained. The damage process of the front wall is analyzed. The prediction model for damage and failure of front wall is built. The critical stress value is obtained.
SPH methods in AUTODYN-2D is used for investigate the gas-secondary debris interaction process. The numerical simulation results are consistent with experimental results very well. The fragmentation process of projectile is introduced. According to characteristic of secondary debris, initial model of secondary debris is built. The gas-secondary debris interaction process is analyzed. The model of the gas-secondary debris interaction is built. The calculational results are compared to experimental results to verify the usefulness of the model. The motion characteristics of secondary debris and the rules of shock wave propagation are obtained.
the paper assumes that the rear wall is subjected to uniform load when impacted by the debris cloud and shock wave. Initial velocity of the rear wall under a localized pulse loading is obtained. Based on the closed from deflection solution for thin plates subjected to localize explosive loading, the radius of discing and petalling is obtained. The prediction model for damage and failure of rear wall is built. The critical condition of catastrophic rupture of rear wall under a localized gas pressure is obtained.
Last, based on the previous study, the prediction model for damage and failure of pressure vessels under hypervelocity impact is built. The applicable scope of prediction model is discussed. The calculational results are compared to experimental results to verify the usefulness of the model. The paper gives the prediction process.
The result of this paper has some significant meanings and is valuable in engineering applications and providing theoretical guidelines. It reveals the physical process of pressure vessel damage and mechanism of damage. It provides technical foundation for risk assessment of pressure vessel and shielding design applications of pressure vessel.
本文以航天器上的圆柱形充气压力容器为研究对象,以速度范围为1.0km/s~7.0km/s的球形铝制弹丸模拟空间碎片,采用数值模拟和理论分析相结合的技术手段,对空间碎片超高速撞击充气压力容器的破损过程、破损机理开展系统研究,建立了包括容器前壁破损预报及容器后壁破损预报的压力容器破损预报模型,并与实验结果进行了对比。
应用AUTODYN-2D,采用Lagrange方法确定了压力容器前壁穿孔尺寸、裂纹尺寸与气体压力、撞击条件的关系。根据压力容器前壁穿孔的形态特征,将其简化为含双裂纹的圆孔,建立了压力容器前壁穿孔的简化模型。基于线弹性断裂力学的Bueckner原理,建立了前壁穿孔尺寸、裂纹尺寸及气体压力与裂纹应力强度因子之间的关系式。应用该关系式,并基于断裂力学的K准则,对在气体介质压力作用下压力容器前壁的断裂行为进行了分析,建立了压力容器前壁破损预报模型,获得了压力容器前壁发生灾难性破坏的临界条件。研究结果表明,压力容器前壁穿孔孔边是否有裂纹裂纹产生对容器前壁发生灾难性破坏的临界气体压力有较大的影响。
应用AUTODYN-2D,采用SPH方法对前壁撞击穿孔而产生的二次碎片与内充气体介质的相互作用过程建立计算模型并进行了数值模拟分析,通过与实验结果相比较,验证了数值模拟方法的有效性。根据二次碎片形态特点,建立了不同弹丸破碎模式的二次碎片初始模型。在此基础上,应用流体动力学、冲击波及气固两相流理论,结合数值模拟研究结果,对不同弹丸破碎模式下二次碎片与气体介质的相互作用过程进行了分析,建立了二次碎片与气体介质的相互作用模型,并通过与数值模拟结果、实验结果相比较验证了模型的有效性,确定了压力容器内二次碎片的运动特性及气体冲击波的传播规律。
针对不同弹丸破碎模式,根据已获得的二次碎片运动特性及气体冲击波的传播规律,将二次碎片及气体冲击波对容器后壁的作用简化为局部均布冲击载荷对固支圆板的作用,建立了不同弹丸破碎模式下二次碎片及气体冲击波对压力容器后壁作用的简化模型,获得了局部冲击载荷的作用半径及在二次碎片与冲击波共同作用下容器后壁产生的初速度。基于前人对局部冲击载荷作用下圆板的破坏分析,确定了在二次碎片与气体冲击波作用下容器后壁产生穿孔的临界条件及穿孔半径。将穿孔半径等效为贯穿直裂纹,根据线弹性断裂力学,并考虑容器壁曲率的影响,获得了容器后壁发生灾难性破坏的临界条件。
最后,集成上述研究成果建立了超高速撞击下充气压力容器的破损预报模型,并讨论了预报模型的适用范围。针对具体的实验工况应用建立的预报模型进行了计算,给出了预报流程,并通过与实验结果的比较验证了预报模型的有效性。
本文建立的球形弹丸超高速撞击充气压力容器破损预报模型对航天器防护结构的设计具有指导意义,揭示了压力容器在超高速撞击下的破损机理,为压力容器类部件空间碎片撞击风险评估及开发研制先进的压力容器防护方案具有工程应用参考价值。
With the unceasing development of space activity, the total number of space debris is ever increasing, which greatly threatens orbiting space vehicles. Spacecraft often employ pressure vessels to contain gases and liquids. A pressure vessel subjected to hypervelocity impact by meteoroids and space debris can represent a significant hazard to a space vehicle because of the energy stored within the vessel. Vessel can occur venting through the impact hole. Catastrophic rupture of the vessel can send high-velocity fragments in all directions and secondary debrisary damage becomes a serious threat to the spacecraft. The damage characteristic of pressure vessel by space debris and prediction of catastrophic failure are the important basic of shield structure design and risk evaluation of spacecraft in space debris environment.
At present, the quantitative investigation on damage process of pressure vessel under hypervelocity impact is still very limit. Systemic prediction model for damage and failure of pressure vessels under hypervelocity impact has not built.
Based on the background mentioned above, this paper investigates the damage process of pressure vessel under hypervelocity impact. The impact velocity is ranging from 1.0 km/s to 7.0 km/s, the impact condition limits to fragmentation and melt of materials. The gas-secondary debris interaction process and propagation process of shock wave are investigated, and the prediction model for damage and failure of pressure vessels under hypervelocity impact is built.
Lagrange methods in AUTODYN-2D is used for investigate the relationships between impact hole size, crack size, gas pressure and impact conditions. According to characteristics of impact hole, initial model of secondary debris is built. The model is presented by postulates the existence of two-radial cracks that emanate at the boundary of a circular hole. The relationships of impact hole size, crack size, gas pressure and the stress intensity factor which is determined by simplified linear elastic fracture mechanics are obtained. The damage process of the front wall is analyzed. The prediction model for damage and failure of front wall is built. The critical stress value is obtained.
SPH methods in AUTODYN-2D is used for investigate the gas-secondary debris interaction process. The numerical simulation results are consistent with experimental results very well. The fragmentation process of projectile is introduced. According to characteristic of secondary debris, initial model of secondary debris is built. The gas-secondary debris interaction process is analyzed. The model of the gas-secondary debris interaction is built. The calculational results are compared to experimental results to verify the usefulness of the model. The motion characteristics of secondary debris and the rules of shock wave propagation are obtained.
the paper assumes that the rear wall is subjected to uniform load when impacted by the debris cloud and shock wave. Initial velocity of the rear wall under a localized pulse loading is obtained. Based on the closed from deflection solution for thin plates subjected to localize explosive loading, the radius of discing and petalling is obtained. The prediction model for damage and failure of rear wall is built. The critical condition of catastrophic rupture of rear wall under a localized gas pressure is obtained.
Last, based on the previous study, the prediction model for damage and failure of pressure vessels under hypervelocity impact is built. The applicable scope of prediction model is discussed. The calculational results are compared to experimental results to verify the usefulness of the model. The paper gives the prediction process.
The result of this paper has some significant meanings and is valuable in engineering applications and providing theoretical guidelines. It reveals the physical process of pressure vessel damage and mechanism of damage. It provides technical foundation for risk assessment of pressure vessel and shielding design applications of pressure vessel.
引文
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62 P. W. Randles, L. D. Libersky. Smoothed Particle Hydrodynamics: Some Resent Improvements and Applications. Computer Methods in Applied Mechanics and Engineering, 1996, 139(1-4): 375~408
63 M. Katayama, S. Toda, S. Kibe. Numerical Simulation of Space Debris Impacts on the Whipple Shield. Acta Astronautica, 1997, 40(12): 859~869
64 R. J. Gordon, A. S. Robert, R. B. Stephen. SPH for High Velocity Impact Computations. Computer Methods in Applied Mechanics and Engineering, 1996, 139(1-4): 347~373
65 AUTODYN Users Manual Revision 6.0. Concord, CA94520 USA: Century Dynamics, Incorporated, 2005
66马文来,张伟,管公顺等.椭球弹丸超高速撞击防护屏碎片云数值模拟.材料科学与工艺, 2005, 13(3): 294~298
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68马志涛,张伟,贾斌等.弹丸超高速撞击半无限厚铝板数值模拟.材料科学与工艺, 2004, 12(3): 283~286
69 H. A. Bueckner. Principle for the Computation of Stress Intensity Factors. ZAMM, 1970, 50: 529~546
70 S. T. Xiao, M. W. Brown, K. J. Miller. Stress Intensity Factors for Cracks in Notched Finite Plates Subjected to Biaxial Loading. Fatigue&Fracture of Engineering Materials&Structures, 1985, 8(4): 349~372
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73管公顺,庞宝君,哈跃等.铝合金Whipple防护结构高速撞击实验研究.爆炸与冲击, 2005, 25(5): 461~466
74张永强.超高速撞击防护屏碎片云特性建模及损伤预报.哈尔滨工业大学硕士学位论文, 2004: 37~40
75迟润强,庞宝君,何茂坚等.球形弹丸超高速正撞击薄板破碎状态实验研究.爆炸与冲击, 2009, 29(3): 231~236
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77 A. J. Piekutowski. Effects of Scale on Debris Cloud Properties. Int. J. Impact Engng. 1997, 20:639~650
78 A. J. Piekutowski. Fragmentation-Initiation Threshold for Spheres Impacting at Hypervelocity. Int. J. Impact Eng. 2003, 29:563~574
79 A. J. Piekutowski. Characteristics of Debris Clouds Produced by Hypervelocity Impact of Aluminum Spheres with Thin Aluminum Sheets. NASA CR-201003, 1995
80 A. J. Piekutowski. Fragmentation of a Sphere Initiated by Hypervelocity Impact with a Thin Sheet. Int. J. Impact Eng. 1995, 17:627~638
81 A. J. Piekutowski. Debris Clouds Produced by the Hypervelocity Impact of Nonspherical Projectiles. Int. J. Impact Engng. 2001, 26: 613~624
82 F. Sch?fer. An Engineering Fragmentation Model for the Impact of Spherical Projectiles on Thin Metallic Plates. Int. J. Impact Engineering, 2006, 33: 1~12
83 M. E. Kipp, D. E. Grady, J. W. Swegle. Numerical and Experimental Studies ofHigh Impact Fragmentation. Int. J. Impact Engineering, 1993, 16:427~438
84 E. L. Christiansen. Design and Perforation Equation for Advanced Meteoroid and Debris Shields. Int. J. Impact Engineering, 1992, 14: 145~156
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62 P. W. Randles, L. D. Libersky. Smoothed Particle Hydrodynamics: Some Resent Improvements and Applications. Computer Methods in Applied Mechanics and Engineering, 1996, 139(1-4): 375~408
63 M. Katayama, S. Toda, S. Kibe. Numerical Simulation of Space Debris Impacts on the Whipple Shield. Acta Astronautica, 1997, 40(12): 859~869
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66马文来,张伟,管公顺等.椭球弹丸超高速撞击防护屏碎片云数值模拟.材料科学与工艺, 2005, 13(3): 294~298
67张伟,庞宝君,贾斌.弹丸超高速撞击防护屏碎片云数值模拟.高压物理学报, 2004, 18(1): 47~52
68马志涛,张伟,贾斌等.弹丸超高速撞击半无限厚铝板数值模拟.材料科学与工艺, 2004, 12(3): 283~286
69 H. A. Bueckner. Principle for the Computation of Stress Intensity Factors. ZAMM, 1970, 50: 529~546
70 S. T. Xiao, M. W. Brown, K. J. Miller. Stress Intensity Factors for Cracks in Notched Finite Plates Subjected to Biaxial Loading. Fatigue&Fracture of Engineering Materials&Structures, 1985, 8(4): 349~372
71徐芝纶.弹性力学(上册).第三版.高等教育出版社, 1990: 97~103
72 J. Piekutowski. Formation and Description of Debris Clouds Produced by Hypervelocity Impact. NASA Contractor Report 4707, Contract NAS8-38856, 1996
73管公顺,庞宝君,哈跃等.铝合金Whipple防护结构高速撞击实验研究.爆炸与冲击, 2005, 25(5): 461~466
74张永强.超高速撞击防护屏碎片云特性建模及损伤预报.哈尔滨工业大学硕士学位论文, 2004: 37~40
75迟润强,庞宝君,何茂坚等.球形弹丸超高速正撞击薄板破碎状态实验研究.爆炸与冲击, 2009, 29(3): 231~236
76迟润强.弹丸超高速撞击薄板碎片云建模研究.哈尔滨工业大学博士学位论文, 2010: 47~91
77 A. J. Piekutowski. Effects of Scale on Debris Cloud Properties. Int. J. Impact Engng. 1997, 20:639~650
78 A. J. Piekutowski. Fragmentation-Initiation Threshold for Spheres Impacting at Hypervelocity. Int. J. Impact Eng. 2003, 29:563~574
79 A. J. Piekutowski. Characteristics of Debris Clouds Produced by Hypervelocity Impact of Aluminum Spheres with Thin Aluminum Sheets. NASA CR-201003, 1995
80 A. J. Piekutowski. Fragmentation of a Sphere Initiated by Hypervelocity Impact with a Thin Sheet. Int. J. Impact Eng. 1995, 17:627~638
81 A. J. Piekutowski. Debris Clouds Produced by the Hypervelocity Impact of Nonspherical Projectiles. Int. J. Impact Engng. 2001, 26: 613~624
82 F. Sch?fer. An Engineering Fragmentation Model for the Impact of Spherical Projectiles on Thin Metallic Plates. Int. J. Impact Engineering, 2006, 33: 1~12
83 M. E. Kipp, D. E. Grady, J. W. Swegle. Numerical and Experimental Studies ofHigh Impact Fragmentation. Int. J. Impact Engineering, 1993, 16:427~438
84 E. L. Christiansen. Design and Perforation Equation for Advanced Meteoroid and Debris Shields. Int. J. Impact Engineering, 1992, 14: 145~156
85吴望一.流体力学(下册).北京大学出版社, 1983: 1~178
86 D. J. Carlson, R. F. Hoglund. Particle Drag and Heat Transfer in Rocket Nozzles. AIAA, 1970, 2(11): 1980~1984
87张兆顺,崔桂香.流体力学.清华大学出版社, 1998: 113~118
88И.戈歇克,多罗德尼钦,А.А.保高斯洛伏斯基.高速空气动力学.安继光,吕绍椿译.国防工业出版社, 1958: 1~21
89 W. P. Schonberg, A. J. Bean, K. Darzi. Hypervelocity Impact Physics. NASA Contractor Report 4343, 1991
90 V. M.Boiko, V. P. Kiselev, S. P. Kiselev. Interaction of a Shock Wave with a Cloud of Particles. Combustion, Explosion, and Shock Waves, 1996, 32(2): 191~203
91 V. M.Boiko, V. P. Kiselev, S. P. Kiselev. Shock Wave Interaction with a Cloud of Particles. Shock Waves, 1997, 32: 275~285
92张涤明.计算流体力学.中山大学出版社, 1991: 82~144
93苏明德,黄素逸.计算流体力学基础.清华大学出版社, 1997: 231~322
94刘润泉,白雪飞,朱锡.舰船单元结果模型水下接触爆炸破口试验研究.海军工程大学学报, 2001, 13(5): 41~47
95朱锡,白雪飞,黄若波等.船体板架在水下接触爆炸作用下的破口试验.中国造船, 2003, 44(1): 46~52
96 G. N. Nurick, A. M. Radford. Deformation and Tearing of Clamped Circular Plates Subjected to Localised Central Blastloads.In:Reddy BD(editor)Recent Developments in Computational and Applied Mechanics. A Volume in Honour of John B.Martin, 1997: 276~301
97 Y. W. Lee, T. Wierzbicki. Fracture Prediction of Thin Plates under Localized Impulsive Loading Part I: Dishing. Int J Impact Engineering, 2005, 31: 1253~1276
98张振华,朱锡.刚塑性板在柱状炸药接触爆炸载荷作用下的花瓣开裂研究.船舶力学, 2004, 8(5): 113~119
99 T. Wierzbick, G. N. Nurick. Large Deformation of Thin Plates under Localized Impulsive Loading. Int J Impact Engineering, 1996, 18: 899~918
100杨桂通,熊祝华.塑性动力学.清华大学出版社, 1984: 159~217
101 S. M. Mihailescu, T. Wierzbicki. Wave Solution for an Impulsively Loaded Rigid-Plastic Circular Membrane. Arch Mech, 2002, 54(5-6): 737~759
102 T. Wierzbicki. Petalling of plates under explosive and impact loading. Int J Impact Engineering, 1999, 22:935~954
103 R. L. Bjork, A E Olshaker. The Role of Melting and Vaporization in Hypervelocity Impact. Memorandum RM-3490-PR, 1965
104汤文辉,张若棋.物态方程理论及计算概论.国防科技大学出版社, 1999: 88~128
105经福谦.实验物态方程导引.科学出版社, 1999: 1~100
106管公顺.航天器空间碎片防护结构超高速撞击特性研究.哈尔滨:哈尔滨工业大学博士学位论文, 2006: 124~131