振动载荷对立贮式发动机粘接界面损伤影响

推进技术 ›› 2018, Vol. 39 ›› Issue (5): 1092-1098.

振动载荷对立贮式发动机粘接界面损伤影响

张波^1,2,董可海¹,李金飞¹,唐岩辉¹

海军航空工程学院飞行器工程系，山东烟台 264001; 中国人民解放军92728部队，上海 200436,海军航空工程学院飞行器工程系，山东烟台 264001,海军航空工程学院飞行器工程系，山东烟台 264001,海军航空工程学院飞行器工程系，山东烟台 264001

发布日期:2021-08-15
作者简介:张波，男，博士生，研究领域为发动机使用工程。

Effects of Vibration Load on Bonding Interface Damage of Vertical Storage Motor

Department of Aircraft Engineering，Naval Aeronautical and Astronautical University，Yantai 264001，China;The 92728 Unit of PLA，Shanghai 200436，China,Department of Aircraft Engineering，Naval Aeronautical and Astronautical University，Yantai 264001，China,Department of Aircraft Engineering，Naval Aeronautical and Astronautical University，Yantai 264001，China and Department of Aircraft Engineering，Naval Aeronautical and Astronautical University，Yantai 264001，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究长期舰载环境下振动载荷对立贮式固体发动机粘接界面损伤的影响，计算了不同浪级下的界面剪切应力变化，利用自制的粘接试件开展了振动试验，测试了不同振动加速度和不同振动时间下的界面力学性能，根据计算和试验数据推导了某海域舰载值班时发动机界面损伤模型，分析了在某海域连续舰载值班一年振动对发动机界面损伤的影响。结果表明，发动机舰载值班过程中平均界面剪切应力变化幅值与浪级间的关系为[|Δτl|=9.375l4-150.69l3+846.88l2-1748.41l+2917.86]；在只考虑振动条件下，舰载值班时间相同，界面最大剪切应力强度随着浪级的增大下降越来越明显，同一浪级下，界面最大剪切应力强度与振动时间呈线性关系；在某海域长期连续舰载值班时受振动载荷影响粘接界面损伤与值班时间的关系为[D=6.5×10-4t-4.68×10-4]，发动机在该海域连续值班一年振动载荷使发动机损伤值至少增加23.68%。

关键词: 振动载荷；剪切应力；立式贮存；粘接界面；固体发动机

Abstract: In order to study the effects of vibration load on bonding interface damage of vertical storage motor in the shipboard environment for a long time， the interfacial shear stress variation at different wave levels was calculated. The vibration test was carried out by using self-made bonding specimen， and the interfacial mechanical properties with different vibration acceleration and vibration time were measured. According to the calculation and test data， the interfacial damage model of the motor on shipboard duty in a sea is derived. The effects of the vibration load to the interface of motor after a year continuous shipboard duty in the sea was analysed. The results show that， the relationship of average interfacial shear stress variation amplitude of motor and wave levels on shipboard duty is [|Δτl|=9.375l4-150.69l3+846.88l2-1748.41l+2917.86]. Under the condition of vibration， the decrease of the interfacial maximum shear stress intensity is more and more obvious with the increase of wave levels at the same shipboard duty time， and the maximum shear stress intensity is linear with the vibration time under the same wave levels. Affected by vibration load， the relationship between bonding interface damage and duty time is [D=6.5×10-4t-4.68×10-4] when the motor is on long term continuous shipboard duty in a sea. Affected by vibration load， the damage of motor increased by at least 23.68% after a year continuous shipboard duty in this sea area.

Key words: Vibration load；Shear stress；Vertical storage； Bonding interface；Solid motor

张波,董可海,李金飞,唐岩辉. 振动载荷对立贮式发动机粘接界面损伤影响[J]. 推进技术, 2018, 39(5): 1092-1098.

ZHANG Bo^1,2,DONG Ke-hai¹,LI Jin-fei¹,TANG Yan-hui¹. Effects of Vibration Load on Bonding Interface Damage of Vertical Storage Motor[J]. Journal of Propulsion Technology, 2018, 39(5): 1092-1098.

参考文献

[1] Kuhlmann T L, Peeters R L, Bills K W, et al. Modified Maximum Principal Stress Criterion for Propellant Liner Bond Failures[J]. Journal of Propulsion and Power, 1987, 3(3): 235-240.
[2] Herb Chelner, Jim Buswell, Dan Evans. Embedded Sensors for Monitoring Solid Propellant Grains[R]. AIAA 2005-4362.
[3] 王玉峰, 李高春, 王晓伟. 固体火箭发动机海洋环境下的贮存及寿命预估[J]. 火炸药学报, 2008, 31(6): 87-90.
[4] Thangjitham S, Heller R A. Stress Response of Rocket Motors to Environmental Thermal Loads[J]. Journal of Spacecraft and Rockets, 1986, 23( 5): 519-526.
[5] Tormey J F, Britton S C. Effect of Cycle Loading on Solid Propellant Grain Structure[R]. AIAA 63-1770.
[6] 李金飞, 黄卫东, 李高春, 等. 振动载荷对定应变HTPB推进剂力学性能影响[J]. 推进技术, 2016, 37(2): 372-377. (LI Jin-fei, HUANG Wei-dong, LI Gao-chun, et al. Effects of Vibration Load Mechanical Properties of HTPB Propellant with Constant Strain [J]. Journal of Propulsion Technology, 2016, 37(2): 372-377.)
[7] 程吉明, 李进贤, 侯晓, 等. HTPB推进剂热力耦合老化力学性能研究[J]. 推进技术, 2016, 37(10): 1984-1990. (CHENG Ji-ming, LI Jin-xian, HOU Xiao, et al. Aging Mechanical Properties of HTPB Propellant under Thermal-Mechanical Coupled Condition [J]. Journal of Propulsion Technology, 2016, 37(10): 1984-1990.)
[8] 李金飞, 黄卫东, 李瑞亮. 基于实测舰载环境温度的固体发动机药柱累积损伤分析[J]. 四川兵工学报, 2012, 33(10): 7-9.
[9] 邱欣, 李高春, 张春龙, 等. 基于主应力的固体火箭发动机界面累积损伤分布研究[J]. 固体火箭技术, 2014, 37(4): 346-351.
[10] 刘文一, 焦冀光. 舰载环境对固体发动机装药影响分析[J]. 弹箭与制导学报, 2015, 35(6): 80-86.
[11] 邢耀国, 曲凯, 许俊松, 等. 舰船摇摆条件下固体火箭发动机舰载寿命预估[J]. 推进技术, 2011, 32(1): 32-35. (XING Yao-guo, QU Kai, XU Jun-song, et al. Life Prediction of Shipborne Solid Rocket Motor under the Ship Swing Motion[J]. Journal of Propulsion Technology, 2011, 32(1): 32-35.)
[12] 李鹏. 基于工业CT的固体火箭发动机装药脱粘修复技术研究[D]. 烟台:海军航空工程学院, 2015.
[13] 张春龙. 固体发动机粘接界面受载状态监检测技术与方法研究[D]. 烟台:海军航空工程学院, 2015.
[14] 曲凯. 舰载固体火箭发动机疲劳损伤研究[D]. 烟台:海军航空工程学院, 2011.
[15] 冯建时. 固体火箭发动机燃烧室界面粘接强度测试方法[S]. 中华人民共和国航空航天工业部, QJ 2038.2-91, 1991.
[16] Wah T L. Global Wave Statistics for Structaral Design Assessments[R]. ADA-286856.　　　　　　　　　　　　　*　收稿日期:2017-03-30；修订日期:2017-05-27。作者简介:张波,男,博士生,研究领域为发动机使用工程。E-mail: zb112060@163.com(编辑: 史亚红)