International Journal of Aerospace Engineering / 2019 / Article / Tab 3

Research Article

Development of Pogo Pin-Based Holding and Release Mechanism for Deployable Solar Panel of CubeSat

Table 3

Representative LLSS test results before and after each vibration test.

Test axisStatus1st eigenfrequency (Hz)Difference (%)

panelBefore73.050.28
After72.84
panelBefore72.840.27
After72.64

panelBefore75.302.01
After73.81
panelBefore74.060.06
After74.01

panelBefore260.560.21
After260.02
panelBefore273.841.50
After269.71

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