FEAÂ of Deep-Space Telescope
Performed Static structural Analysis on ANSYS to accomplish the stresses induced in truss structure due to self-weight of the mirrors.
Obtained the results of Model Analysis to ensure the natural frequency does not match with the frequencies during launch.
Accomplished the results of Thermal Analysis of the system at 120°C (Light Side) and -100°C (Dark Side).
Validated the Telescope structure for structural integrity using Transient Structural Analysis.
Static Structural Analysis
Total deformation : The total deformation is largest at the top of the truss and has a magnitude of 0.60755 mm.
Equivalent Stresses : The maximum stress is induced in the flexural mounts and has magnitude of 16.385 MPa.
Directional Deformation :
The directional deformation is in the range of -0.08 mm to +0.08 mm.
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Modal Analysis
Natural Frequency was analyzed for 10 modes. The value of frequency ranges from 22.501 Hz to 112.777 Hz
Transient Thermal Analysis (Find temperature distribution when heat transfer coefficient is known)
This image shows temperature variation in the mirror frame when the ambient temperature is varied from -100 to 200 deg C
Transient Structural Analysis (Impact of Earthquake)
Transient Structural Analysis to test the structural integrity of the system under earthquake load
Modal Analysis of a Satellite (P-POD launcher)
A simplified CubeSat is held in a rectangular box called a P-POD while being launched into orbit.
The 1U CubeSat with legs has dimensions of 10.5cm x 10cm x 10cm. The structure is made of Aluminum 6061-T6.
The CubeSat also contains boxes and a cylinder, which represent simplified internal components such as a main flight computer and the attitude control system.
Natural Frequency was analyzed for first 5 modes. The value of frequency ranges from 192.62 Hz to 484.43 Hz.
