Design and Verification of Slip Fault Recognition of Space Antenna Locking Device
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摘要: 锁紧机构是星载可展结构中常用的压紧和释放机构。在使用过程中,锁紧机构常常会因振动过大发生接触面滑移,导致锁紧释放失效。针对此问题,本文提出了一个根据锁紧座内力变化判别滑移故障的识别方法。首先通过标定试验得到锁紧机构的载荷-应变关系标定曲线;而后设计、加工了星载天线锁紧机构模型,并进行了正弦振动试验。试验过程中分别采集锁紧机构应变数据和加速度响应数据;最后对比根据动力特性变化识别滑移故障和根据内力变化识别滑移故障这两种方法的判定结果,说明本文提出的内力变化滑移识别方法准确有效。Abstract: The locking seat is a commonly used locking and releasing mechanism in aerospace engineering. During the running status, the slipping of contact surface in locking seat often occurs due to vibration, resulting in the lock failure. In order to solve this problem, a set of sliding recognition system of lock seat is proposed. Firstly, the constitutive relation curve of the locking seat is obtained through calibration test. Then the locking device model of the overlapped antenna is designed and processed, and the vibration test is carried out. The strain data and acceleration response data of locking device are collected separately during the test. Finally, the analysis results of the two measurement methods are compared, which shows that the method of the sliding recognition system of the lock seat is accurate and effective.
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Key words:
- space antenna /
- locking device /
- slip /
- vibration test /
- fault recognition
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表 1 底座上表面载荷分析结果
状态 拉力最大值/N 压力最大值/N 弯矩最大值/(N·m) 剪力最大值/N 滑移前 131.9 -159.7 2.9 589.5 滑移后 43.6 -65.6 1.4 270.1 表 2 轴向内力平均变化
N 方向 振动量级 1 g 4 g 6 g 8 g Z向 -4 -220 -1 105 -1 340 X向 -81 -157 -232 -750 表 3 锁紧机构的滑移情况
方向 振动量级 1 g 4 g 6 g 8 g Z向 × × ○ ○ X向 × × × ○ 注: ×表示锁紧机构未发生滑移, ○表示锁紧机构发生滑移 表 4 重叠天线一阶峰值对应的加速度响应值
g 输入量级 反射面中心点 锁紧机构角片 Z向 X向 Z向 X向 1 g 131.87 13.42 2.50 9.26 4 g 243.24 55.00 7.24 37.88 6 g 267.72 72.78 9.84 49.68 8 g 280.07 69.04 12.12 48.32 -
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