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Iris CubeSat project
Iris CubeSat project
My contributions to Iris CubeSat project as the payload lead can be found below:
Payload Sample plate Assembly
Payload Sample plate Assembly
Sample plate assembly.MOV
Payload Sample plate vibration tests
Payload Sample plate vibration tests
Test description:
Test description:
The following test shall subject an engineering model (EM) of the Iris payload sample plate assembly to the mission’s expected random vibration profile. In this test, the duration will be increased to 120 seconds and test level will be increased to +3 dB relative to the Nanoracks hard-mount test level for qualification. This test will be used to validate the clamping mechanism used to hold payload samples in place and quantify how much (if any) debris is emitted by the samples during vibrations.
Iris Hard-Mount Qualification Test Profile
Test result:
Test result:
A total of 20 samples were successfully vibration tested to the Iris hard-mount qualification test profile shown in the table . The test level was started at -3 dB relative to Nanoracks hard-mount test level for 15 seconds, then increased to 100% of Nanoracks hard-mount test level for 15 seconds, and finally, it was increased to +3dB relative to Nanoracks hard-mount test level. Tests were performed in X, Y, and Z axes.
Finite Element Analysis (FEA):
Finite Element Analysis (FEA):
Introduction:
Introduction:
In order to determine the response of the spacecraft to various environments, a Finite Element Analysis (FEA) of CubeSat is required. One of the most critical conditions that the CubeSat will experience is the launch environment. This is the time from when the satellite leaves the surface of the Earth and reaches the desired orbit. During the launch time, the CubeSat will experience various vibrational loads from the launch vehicle.
I conducted the following structural analysis required by the CSA.
Modal Analysis
Quasi-Static Analysis
Random vibration Analysis
Summary of the analysis results can be found in the following figures.
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