火箭推进

大推力火箭发动机摇摆过程中,摇摆轴承使用环境与轴承自身设计指标不同,在承受较大径向载荷的同时,还要承受一定的轴承载荷,并实现低速往复摆动。为获得轴承的静态承载能力摩擦系数及疲劳寿命等关键参数,设计了一种新的轴承试验系统,模拟轴承在发动机不同工作状态下的安装边界和受载形式。通过试验获得了相应的数据,试验结果表明:轴承静态承载能力不小于920 kN,单、双摆状态下的疲劳寿命大于实际使用寿命的10倍,单摆状态的摩擦系数0.045,双摆状态的摩擦系数不大于0.08。目前,经过该方案验证的轴承已多次成功应用于某型液体火箭发动机。

In the swing of high thrust rocket engine,unlike design index,the swing-bearing not only bears a large radial load,but also bears a certain bearing load,and realizes low-speed reciprocating swing.In order to obtain the static bearing capacity,friction coefficient and fatigue life,a new bearing test system was designed to simulate the installation boundary and loading form of the bearing under different working conditions.The test results show that the static bearing capacity is not less than 920 kN,the fatigue life is more than 10 times of actual service life under the single and double pendulum,the friction coefficient of the bearing is 0.045(single pendulum)and not more than 0.08(double pendulum).At present,the bearing verified by the scheme has been successfully applied to a certain type of liquid rocket engine for many times.

引言
1 边界及受载分析
2 系统设计
3 应用实例
4 结论

图1 轴承安装位置示意图<br/>Fig.1 The installation location of bearing in rocket engine

图1 轴承安装位置示意图
Fig.1 The installation location of bearing in rocket engine

图2 轴承模型及安装边界示意图<br/>Fig.2 The drawing of real installation mode

图2 轴承模型及安装边界示意图
Fig.2 The drawing of real installation mode

图3 轴承实际安装位置及受载分析<br/>Fig.3 The real installation location and loaded analysis of bearing

图3 轴承实际安装位置及受载分析
Fig.3 The real installation location and loaded analysis of bearing

图4 自带轴轴承轴向力与轴承摇摆角度关系曲线<br/>Fig.4 The relation between axial load of bearing in coming with axis and swing angle

图4 自带轴轴承轴向力与轴承摇摆角度关系曲线
Fig.4 The relation between axial load of bearing in coming with axis and swing angle

图5 轴承实际安装方式及载荷边界模拟示意图<br/>Fig.5 The drawing of load boundary simulation

图5 轴承实际安装方式及载荷边界模拟示意图
Fig.5 The drawing of load boundary simulation

图6 加载方式模拟示意图<br/>Fig.6 The drawing of loadding mode

图6 加载方式模拟示意图
Fig.6 The drawing of loadding mode

图7 驱动载荷施加示意图<br/>Fig.7 The schematic drawing of driven load

图7 驱动载荷施加示意图
Fig.7 The schematic drawing of driven load

图8 轴承载荷试验系统<br/>Fig.8 The schematic drawing of driven load

图8 轴承载荷试验系统
Fig.8 The schematic drawing of driven load

图9 轴承等效摩擦系数结果<br/>Fig.9 The measuring results of equivalent friction coefficient

图9 轴承等效摩擦系数结果
Fig.9 The measuring results of equivalent friction coefficient

[1] 陈守芳. 常平座的设计与应用[J].火箭推进,2004,30(5):27-30.
[2] 魏立保,陈有光. 自润滑关节轴承的研制与应用[J].轴承,2008(5):8-10.
[3] BENNETT G. Simple but strong:The plain bearing advantage[J].Machine Design,2009,81(7):76.
[4] 李斌,张小平,马冬英. 我国新一代载人火箭液氧煤油发动机[J].载人航天,2014,20(5):427-431.
[5] 马华静. 关节轴承试验机研制及磨损量检测系统热误差补偿[D].秦皇岛:燕山大学,2017.
[6] SLINEY H. Some loads limits and self-lubricating properties of plain spherical bearings with molded graphite fiber-reinforced polyimide liners to 320 ℃[EB/OL].https://www.semanticscholar.org/paper/Some-loads-limits-and-self-lubricating-properties-C-Sliney/411a2ba3960aac09bafd 7f5826a96dbf76994763,1978.
[7] KIM B C,PARK D C,KIM H S,et al. Development of composite spherical bearing[J].Composite Structures,2006,75(1/2/3/4):231-240.
[8] KIM B C,LEE D G. Endurance and performance of a composite spherical bearing[J].Composite Structures,2009,87(1):71-79.
[9] 姜韶峰,杨威启,庄汀生. 新型关节轴承寿命试验机及关节轴承寿命判断准则[J].轴承,1996(6):30-33.
[10] 吕新圃,白金石. E06-12型自润滑杆端关节轴承试验机[J].轴承,1997(3):29-32.
[11] 洪富岳,王云,陈民生,等.大中型关节轴承摩擦力矩试验机[J].轴承,1997(9):24-27.
[12] 邸世勇. 一种关节轴承试验机设计与重要零部件结构优化[D].秦皇岛:燕山大学,2014.
[13] 宋云峰,郭强,罗唯力. PTFE/铜网复合材料衬垫自润滑关节轴承的试验研究[J].机械工程材料,2003,27(6):14-15.
[14] 李斌,张小平,高玉闪. 我国可重复使用液体火箭发动机发展的思考[J].火箭推进,2017,43(1):1-7.
[15] 张相盟,陈晖,高玉闪,等.500吨级液氧煤油发动机结构动态特性[J].火箭推进,2020,46(2):44-49.
[16] 陈守芳,樊根民. 双向摇摆发动机摇摆软管设计方法的探讨[J].火箭推进,2001,27(4):8-12.
[17] 毛凯,苗旭升,陈晖,等.液体火箭发动机涡轮泵用轴承寿命试验研究[J].火箭推进,2016,42(5):24-27.
[18] 刘国平,方建敏. 金属膜盘联轴器用关节轴承磨损特性研究[J].航空发动机,2017,43(2):1-5.

备注

引言

1 边界及受载分析

2 系统设计

3 应用实例

4 结论

期刊信息