低温动态加载下老化HTPB推进剂强度准则研究

推进技术 ›› 2018, Vol. 39 ›› Issue (11): 2581-2587.

低温动态加载下老化HTPB推进剂强度准则研究

刘畅,强洪夫,王哲君,王广,黄拳章

火箭军工程大学动力工程系，陕西西安 710025,火箭军工程大学动力工程系，陕西西安 710025,火箭军工程大学动力工程系，陕西西安 710025,火箭军工程大学动力工程系，陕西西安 710025,火箭军工程大学动力工程系，陕西西安 710025

发布日期:2021-08-15
基金资助:
国家自然科学基金(11772352)。

Strength Criterion of Aged HTPB Propellant at Low Temperature under Dynamic Loading

Power Engineering Department，Rocket Force University of Engineering，Xi’an 710025，China,Power Engineering Department，Rocket Force University of Engineering，Xi’an 710025，China,Power Engineering Department，Rocket Force University of Engineering，Xi’an 710025，China,Power Engineering Department，Rocket Force University of Engineering，Xi’an 710025，China and Power Engineering Department，Rocket Force University of Engineering，Xi’an 710025，China

Published:2021-08-15

摘要/Abstract

摘要： 为获得低温动态加载下老化后HTPB推进剂强度准则，开展了低温动态加载下不同热老化时间后HTPB推进剂单轴与准双轴拉伸试验，根据试验结果获得的力学性能参数，基于双剪强度理论构建了推进剂强度极限线及故障包络线。研究发现:随着温度的降低和热老化时间的延长，HTPB推进剂强度极限线范围变大，即推进剂强度增强；随着热老化时间的延长，HTPB推进剂故障包络线缩小，即推进剂抵抗破坏能力逐渐减弱。研究结果可为低温点火条件下战术导弹药柱结构完整性分析提供数据支持。

关键词: 低温；动态；老化；HTPB推进剂；强度准则

Abstract: In order to obtain the strength criterion of aged HTPB propellants at low temperature under dynamic loading， uniaxial and quasi-biaxial tensile tests were taken for HTPB propellants after different aging time， strength limit line and fault envelope was constructed according to the mechanical performance parameters obtained from the test results based on twin shear strength theory. The results indicate that HTPB propellant strength limit line range becomes larger and strength increases with decreasing temperature and increasing aging time. With the increase of thermal aging time， the fault envelope of HTPB propellant is reduced， that is， the resistance to damage of the propellant is gradually weakened. The results can provide data support for analyzing the structural integrity of the tactical missile’s propellant grain under the conditions of low temperature ignition.

Key words: Low temperature；Dynamic；Aged；HTPB propellant；Strength criterion

刘畅,强洪夫,王哲君,王广,黄拳章. 低温动态加载下老化HTPB推进剂强度准则研究[J]. 推进技术, 2018, 39(11): 2581-2587.

LIU Chang,QIANG Hong-fu,WANG Zhe-jun,WANG Guang,HUANG Quan-zhang. Strength Criterion of Aged HTPB Propellant at Low Temperature under Dynamic Loading[J]. Journal of Propulsion Technology, 2018, 39(11): 2581-2587.

参考文献

[1] Gligorijevi? N, ?ivkovi? S, Suboti? S, et al. Effect of Cumulative Damage on Rocket Motor Service Life[J]. Journal of Energetic Materials, 2015, 33(4): 229-259.
[2] Hodge K, Crofoot T, Nelson S. Gelled Propellants for Tactical Missile Applications[R]. AIAA 99-2976.
[3] Nevière R, Tixier L. Fracture of Case Bonded Grains in Cold Pressurization Motors Tests[R]. AIAA 2009-5171.
[4] 刘中兵, 周艳青, 张兵. 固体发动机低温点火条件下药柱结构完整性分析[J]. 固体火箭技术, 2015, 38(3): 351-355.
[5] Zimmerman G A, Kispersky J P, Nahlovsky B D, et al. Embrittlement of Propellants Containing Itrate Ester Plasticizers[R]. AIAA 82-1099.
[6] Jeremic R. Some Aspects of Time-Temperature Superposition Principle Applied for Predicting Mechanical Properties of Solid Rocket Propellants[J]. Propellants, Explosive, Pyrotechnics, 1999, 24(4): 221-223.
[7] Chyuan S. Nonlinear Thermoviscoelastic Analysis of Solid Propellant Grains Subjected to Temperature Loading[J]. Finite Element in Analysis and Design, 2002, 38(7): 613-630.
[8] Chyuan S. Dynamic Analysis of Solid Propellant Grains Subjected to Ignition Pressurization Loading[J]. Journal of Sound and Vibration, 2003, 268(3): 465-483.
[9] D’Andrea B, Lillo F, Marcelli G. High Speed Mechanical Characterization and Temperature Constraints of Propellants with Energetic Binders[R]. AIAA 2000-3183.
[10] 阳建红, 周敬恩, 刘朝丰. 基于环境压强下NEPE固体推进剂双剪强度准则[J]. 固体火箭技术, 2007, 30(3): 253-255.
[11] 孟红磊, 赵秀超, 鞠玉涛, 等. 基于累积损伤的双基推进剂强度准则及实验[J]. 推进技术, 2011, 32(1): 109-112. (MENG Hong-lei, ZHAO Xiu-chao, JU Yu-tao, et al. Strength Criterion Based on Accumulative Damage for Double-Base Propellant and Experiment[J].Journal of Propulsion Technology, 2011, 32(1): 109-112.)
[12] Zhejun Wang, Hongfu Qiang, Guang Wang, et al. Tensile Mechanical Properties and Constitutive Model for HTPB Propellant at Low Temperature and High Strain Rate[J]. Journal of Applied Polymer Science, 2015, 132(24).
[13] 王哲君, 强洪夫, 王广, 等. 低温高应变率条件下 HTPB推进剂拉伸力学性能研究[J]. 推进技术, 2015, 36(9): 1426-1432. (WANG Zhe-jun, QIANG Hong-fu, WANG Guang, et al. Tensile Mechanical Properties of HTPB Propellant at Low Temperature and High Strain Rate[J]. Journal of Propulsion Technology, 2015, 36(9): 1426-1432.)
[14] 强洪夫, 王哲君, 王广, 等. HTPB推进剂低温动态准双轴拉伸力学性能研究[C]. 西安:中国航天空天动力联合会议, 2016.
[15] 王哲君. 低温动态加载下HTPB推进剂力学行为的实验和理论研究[D]. 西安:火箭军工程大学, 2016.
[16] GJB 770B-2005. 火药试验方法[S]. 2005.
[17] 王至存. 定速拉伸的固体推进剂双轴板条的应力分析[J]. 固体火箭技术, 1995, 18(1): 54-59.
[18] Williams M L, Landel R F, Ferry J D. The Temperature Dependence of Relaxation Mechanisms in Amorphous Polymers and Other Glass-Forming Liquids[J]. Journal of the American Chemical Society, 1955, 77(14): 3701-3705.
[19] 俞茂宏. 强度理论新体系[M]. 西安:西安交通大学出版社, 1992.　　　　　　　　　　　　　　收稿日期:2017-09-27；修订日期:2017-11-07。基金项目:国家自然科学基金(11772352)。通讯作者:刘畅,男,硕士生,研究领域为飞行器结构完整性分析。E-mail: 565834169@qq.com(编辑:史亚红)