火箭推进

为了在液体火箭发动机管路结构静强度分析时考虑整机变形的影响,采用以实体单元、壳单元和梁单元为主的建模方法,建立了大推力补燃氢氧发动机试验装置的有限元模型,在热载荷、压力载荷和重力载荷的共同作用下,基于整机模型对管路结构进行了静力计算,并将计算结果与试验测量结果进行了对比。在此基础上,计算了不同类型载荷作用下的整机变形,重点分析了温度载荷的影响。对于典型管路,进一步采用子模型方法计算了不同类型载荷作用下的管路应力,对比了是否考虑整机变形对管路应力水平的影响。结果表明:基于整机模型进行的静力仿真基本能够正确反映出发动机热试验状态下各管路结构的受力状态; 对氢氧发动机而言,温度载荷对整机变形的影响最大,整机变形对管路结构应力水平的影响较大且不容忽视,故有必要考虑整机变形对管路结构的影响来进行静强度分析。

In order to take the structural integral deformation into consideration during the static structural analysis for pipeline structures of the liquid rocket engine, the finite element model of the large-thrust staged combustion cycle hydrogen/oxygen engine was established using solid, shell and beam elements. Meanwhile, the static structural analysis was performed under the joint action of the thermal, pressure and gravity loads. The simulation results were compared with the measured data from the ground firing test. Based on this, the integral deformation of the engine was calculated under different types of loads and the influence of thermal load was analyzed. For typical pipeline structures, the stress distribution was calculated under different types of loads with the submodel method and the influence of the integral deformation on stress level was further investigated. The results show the static structural analysis of the established finite element model could basically reflect the stress state of the engine under the ground firing test state. For hydrogen/oxygen rocket engine, the thermal load has the greatest influence on the integral deformation of the engine, which need to be considered during strength analysis for pipeline structures of the engine.

引言
1 有限元建模
2 结果与讨论
3 结论

图1 发动机整机有限元模型及应变测点布置<br/>Fig.1 Finite element model of the engine and the arrangement of strain measuring points

图1 发动机整机有限元模型及应变测点布置
Fig.1 Finite element model of the engine and the arrangement of strain measuring points

图2 典型组件建模方法<br/>Fig.2 Modeling method of typical components

图2 典型组件建模方法
Fig.2 Modeling method of typical components

图3 载荷示意图<br/>Fig.3 Schematic of load conditionss

图3 载荷示意图
Fig.3 Schematic of load conditionss

图4 典型管路应变测点<br/>Fig.4 Typical strain gauge instrumentation on the pipe

图4 典型管路应变测点
Fig.4 Typical strain gauge instrumentation on the pipe

图5 典型稳态应变测量信号<br/>Fig.5 Typical strain measured signal of steady state

图5 典型稳态应变测量信号
Fig.5 Typical strain measured signal of steady state

图6 稳定状态仿真与测量结果对比<br/>Fig.6 Comparison of simulation and measured results of steady state

图6 稳定状态仿真与测量结果对比
Fig.6 Comparison of simulation and measured results of steady state

图7 预冷状态仿真与测量结果对比<br/>Fig.7 Comparison of simulation and measured results of pre-cooling state

图7 预冷状态仿真与测量结果对比
Fig.7 Comparison of simulation and measured results of pre-cooling state

图8 不同载荷作用下的整机变形<br/>Fig.8 Deformation results under different types of loads

图8 不同载荷作用下的整机变形
Fig.8 Deformation results under different types of loads

图9 典型管路子模型<br/>Fig.9 Submodel of typical pipeline

图9 典型管路子模型
Fig.9 Submodel of typical pipeline

图10 不同载荷作用下典型管路应力结果<br/>Fig.10 Stress distribution of typical pipelines under different types of loads

图10 不同载荷作用下典型管路应力结果
Fig.10 Stress distribution of typical pipelines under different types of loads

[1] 岳文龙, 郑大勇, 颜勇, 等. 我国高性能液氧液氢发动机技术发展概述[J]. 中国航天, 2021(10): 20-25.

₂

[2]金平, 蔡国飙. 全流量补燃循环发动机及其特点[J]. 火箭推进, 2003, 29(4): 43-47.
[3]孙纪国, 岳文龙. 我国大推力补燃氢氧发动机研究进展[J]. 上海航天, 2019, 36(6): 19-23.
[4]郑孟伟, 岳文龙, 孙纪国, 等. 我国大推力氢氧发动机发展思考[J]. 宇航总体技术, 2019, 3(2): 12-17.
[5]杜大华, 穆朋刚, 田川, 等. 液体火箭发动机管路断裂失效分析及动力优化[J]. 火箭推进, 2018, 44(3): 16-22.
[6]周帅, 林磊, 杜大华, 等. 液体火箭发动机对接焊管道振动疲劳性能研究[J]. 火箭推进, 2021, 47(3): 90-97.
[7]ZHANG W. Failure characteristics analysis and fault diagnosis for liquid rocket engines [M]. Berlin: Springer, 2016.
[8]ROUSE J P, SUN W, HYDE T H, et al. A method to approximate the steady-state creep response of three-dimensional pipe bend finite element models under internal pressure loading using two-dimensional axisymmetric models[J]. Journal of Pressure Vessel Technology, 2014, 136(1): 011402.
[9]崔海涛, 温卫东, 佟丽莉. 纤维缠绕复合材料弯管强度分析[J]. 宇航材料工艺, 2003, 33(6): 39-42.
[10]WEBER J, KLENK A, RIEKE M. A new method of strength calculation and lifetime prediction of pipe bends operating in the creep range[J]. International Journal of Pressure Vessels and Piping, 2005, 82(2): 77-84.
[11]王开明, 方雯, 王卫国. 航空发动机支点刚度与整机变形分析方法[J]. 燃气涡轮试验与研究, 2018, 31(4): 30-36.
[12]陈晓豫, 钱文清, 鲍益东, 等. 飞机管路强度快速分析方法[J]. 航空制造技术, 2020, 63(21): 85-91.
[13]YOO J, JEON S M. Static and dynamic structural analyses for a 750 kN class liquid rocket engine with TVC actuation[J]. CEAS Space Journal, 2020, 12(3): 331-341.
[14]TANI N, YAMANISHI N, KUROSU A. An end-to-end high fidelity numerical simulation of the LE-X engine[C]//48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virginia: AIAA, 2012.
[15]王帅, 张明明, 刘桢, 等. 预载荷作用下管路结构动强度评估方法[J]. 北京航空航天大学学报, 2016, 42(4): 745-750.
[16]王帅, 荣克林, 李佰灵, 等. 航天飞行器管路结构的动力学强度分析与试验[J]. 中国科学: 物理学力学天文学, 2019, 49(2): 93-100.
[17]李斌, 闫松, 杨宝锋. 大推力液体火箭发动机结构中的力学问题[J]. 力学进展, 2021, 51(4): 831-864.
[18]叶增荣. 基于MPC简化模型的非对称换热器有限元分析[J]. 压力容器, 2017, 34(5): 38-45.
[19]张霁, 翟晓, 刘兵, 等. 固体发动机静强度试验应变数据的分析与处理[J]. 测控技术, 2016, 35(9): 36-39.
[20]中国航天工业总公司. 液体火箭发动机应变测量方法: QJ 2967—97 [S]. 北京:中国航天工业总公司, 1997.

备注

引言

1 有限元建模

2 结果与讨论

3 结论

期刊信息