Research on Inter-stage Locking Technology for High Stiffness Space Sleeve Deployment Mechanisms

doi:10.3969/j.issn.1004-132X.2025.09.009

Abstract

Abstract:

To address the challenges in achieving high-stiffness locking during the deployment of segmented space telescopes using sleeve mechanisms， a staged locking scheme was proposed for the secondary mirror sleeve-supported deployment mechanisms of long-focal-length， large-aperture space telescopes. Contact models between expansion petals and inner sleeve walls were established， and the normal contact behavior and load distribution patterns during the locking processes were investigated. Bernoulli-Euler beam theory was employed to analyze the normal contact forces between the expansion petals and the sleeve. The relationship among inter-stage locking force， design clearance and locking point positions was derived and validated through finite element methods. The Palmgreen formula was applied to analyze the ascending displacement of the driving ring's inclined surfaces. The design parameters of the inclined surfaces were determined， and finite element methods were employed to analyze the inter-stage locking force when rounded values were assigned to the ascending displacement. The magnitude and distribution patterns of the locking forces were obtained. An experimental prototype of the locking mechanisms was constructed， the experimental results indicate that rolling cylinders smoothly roll into place， the locking forces of the expansion flaps meet expectations， and the feasibility of the sleeve locking mechanism design is confirmed.

Key words: deployment mechanism, sleeve locking, passive locking, high stiffness, deflection deformation

摘要：

针对目前套筒机构应用于分体式空间望远镜展开中难以实现高刚度锁紧的问题，提出一种用于长焦距甚大口径空间望远镜次镜套筒式支撑的展开机构级间锁紧方案。通过建立胀紧瓣与套筒内壁的接触模型，探究了锁紧过程中胀紧瓣与套筒间法向接触情况以及载荷分布规律；采用伯努利-欧拉梁理论对胀紧瓣与套筒接触的法向接触力进行分析，得出级间锁紧力与设计间隙、锁紧作用点之间的规律，并通过有限元方法进行了验证；利用帕姆格林近似公式对驱动环斜面上升高度进行分析，得出了驱动环斜面设计参数，通过有限元手段对驱动环斜面上升高度取圆整数值时级间锁紧力进行分析，得到了锁紧力的数值及分布规律；搭建了锁紧机构实验样机并进行了实验测试，结果表明，滚动柱能够平稳地滚动到位，胀紧瓣的锁紧力符合预期，验证了该套筒机构锁紧方案的可行性。

关键词: 展开机构, 套筒锁紧, 无源锁紧, 高刚度, 挠度变形

CLC Number:

TH122

Yingjun GUAN, Mingqi ZHANG, Huanquan LU, Huisheng YANG, Baoyu SUN. Research on Inter-stage Locking Technology for High Stiffness Space Sleeve Deployment Mechanisms[J]. China Mechanical Engineering, 2025, 36(9): 1980-1988.

关英俊, 张铭起, 逯焕泉, 杨会生, 孙宝玉. 高刚度空间套筒展开机构级间锁紧技术研究[J]. 中国机械工程, 2025, 36(9): 1980-1988.

Figures/Tables 27

Fig.1 Space sleeve deployment mechanism diagram

Fig.2 Sectioned view of locking mechanism

Fig.3 Contact condition

Fig.4 The contact load distribution between the expansion valve and the sleeve

Fig.5 Load distribution

Fig.6 Regional division

Fig.7 Total force model

Fig.8 Deflection deformation of BD region

Fig.9 Deflection deformation of DE region

Fig.10 Deflection deformation of BC region

Fig.11 Deflection deformation of BC region

Fig.12 normal contact force variation

Fig.13 Finite element model of sleeve and expansion disc

Tab.1 Lock model parameter table

胀紧瓣高度 h/mm	滚动柱作用位置 l/mm	胀紧瓣-外套筒间隙 Δ/mm
3	30，35	0.2
3	30，35	0.3
4	30，35	0.2
4	30，35	0.3

Fig.14 Trend chart of normal contact force F with increasing height w

Tab.2 Comparison between theoretical contact force value F and finite element simulation value

胀紧瓣高度h/mm	作用位置 l/mm	间隙 Δ/mm	F理论值/N	F仿真值/N	误差绝对值/%
3	30	0.3	214.5	208.3	2.9
3	35	0.3	159.7	165.4	3.6
3	30	0.2	143.0	137.2	4.1
3	35	0.2	106.5	110.1	3.4
4	30	0.3	350.5	343.5	2.0
4	35	0.3	262.1	272.0	4.5
4	30	0.2	236.4	230.6	2.4
4	352	0.	174.7	180.3	3.0

Fig.15 Load condition

Tab.3 Simulation parameter table

胀紧瓣高度h/mm	设计间隙 $Δ$ /mm	驱动环斜面上升高度最小值 $δ D$ + $Δ$ /mm	作用点位置 l/mm
2	0.1	0.1	30，45，60
2	0.2	0.2	30，45，60
2	0.3	0.3	30，45，60
3	0.1	0.1	30，45，60
3	0.2	0.2	30，45，60
3	0.3	0.3	30，45，60

Tab.3 Simulation parameter table

胀紧瓣高度h/mm	设计间隙 $Δ$ /mm	驱动环斜面上升高度最小值 $δ D$ + $Δ$ /mm	作用点位置 l/mm
2	0.1	0.1	30，45，60
2	0.2	0.2	30，45，60
2	0.3	0.3	30，45，60
3	0.1	0.1	30，45，60
3	0.2	0.2	30，45，60
3	0.3	0.3	30，45，60

Fig.16 Boundary condition

Fig.17 Simulation results of contact force between expansion disc and sleeve

Fig.18 Locking test assembly drawing

Fig.19 Locking test assembly drawing

Fig.20 Initial experimental resistance in unlocked state

Fig.21 Experimental thrust and tension under locked state 1

Fig.22 Experimental thrust and tension under locked state 2

Fig.23 Experimental thrust and tension under locked state 3

Fig.24 Experimental thrust and tension under locked state 4

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