The vibration testing of the KAUSAT-5 satellite includes acceleration testing, modal measurement, random vibration testing, and shock testing. For satellites intended to be integrated into a P-POD (CubeSat Deployer), vibration testing must be conducted at both the QM (Qualification Model) qualification test level and FM (Flight Model) acceptance test level, with testing performed along each axis.
The procedure for vibration testing is as follows: prior to conducting acceleration testing or random vibration testing, first collect the natural frequency data of the satellite; after completing acceleration testing and random vibration testing, perform modal surveys again to check whether the natural frequency of the satellite has changed after the tests.
System-level acceleration testing is only carried out at the qualification level, with the test conditions specified as follows: a sinusoidal wave of 0.013g²/Hz with a peak acceleration of +18.75g applied for 60 seconds. Random vibration testing is required for both qualification and acceptance tests, with the test conditions detailed in the table below. The amplitude for qualification testing is twice that of acceptance testing, and the duration is three times that of acceptance testing. Modal surveys are conducted under the same conditions for both qualification and acceptance procedures, with a test level of 0.4g and a frequency range of 5–2000Hz.
The results of the random vibration qualification testing for the KAUSAT-5 QM (Qualification Model) are shown in Figure 1. Post-test inspections revealed no structural defects or functional failures in electronic components, confirming that the KAUSAT-5 CubeSat and its standard platform feature stable structures and adequate design margins.
Figure 1 QM Vibration Test Results.
The results of the random vibration acceptance testing for the KAUSAT-5 FM (Flight Model) are shown in Figure 2. Testing indicated that the natural frequencies of the X, Y, and Z axes all met the predicted requirement of 90Hz or higher, verifying that the satellite structure is free of any defects.
Figure 2 FM Vibration Test Results.
