{"id":216182,"date":"2026-05-04T11:44:16","date_gmt":"2026-05-04T15:44:16","guid":{"rendered":"https:\/\/www.hajim.rochester.edu\/senior-design-day\/?p=216182"},"modified":"2026-05-04T11:44:16","modified_gmt":"2026-05-04T15:44:16","slug":"satellite","status":"publish","type":"post","link":"https:\/\/www.hajim.rochester.edu\/senior-design-day\/satellite\/","title":{"rendered":"Satellite"},"content":{"rendered":"\n

The Design and Optimization of a Small Cassegrain Telescope<\/p>\n\n\n\n

Team Members<\/h2>\n\n\n\n
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Morgan Edstrom<\/figcaption><\/figure>\n\n\n\n
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Izzy Doty<\/figcaption><\/figure>\n\n\n\n
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Evan Thomas<\/figcaption><\/figure>\n\n\n\n
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Mahir Abbaker<\/figcaption><\/figure>\n<\/figure>\n\n\n\n

Problem Statement<\/h2>\n\n\n\n

Satellites are highly complex and resource-intensive systems that deliver essential data and images from space, requiring significant time, cost, and technical expertise to design and maintain. Developing a small-scale version of these systems provides a more accessible and cost-effective platform for methods to study performance and testing improvements.  <\/p>\n\n\n\n

Specifications and Requirements<\/h2>\n\n\n\n

The primary requirement for this optical device is that it is cost-effective and capable of imaging. In addition, the design must imitate a Cassegrain design method. <\/p>\n\n\n\n

Value & Units<\/strong> <\/td>Description & Method of Evaluation<\/strong> <\/td><\/tr>
18.00 G <\/td>The optical structural assembly (OSA) shall maintain positive Margin of Safety (MoS) > 0.0 under Quasi-Static Limit Loads of Lateral. 
Method of evaluation: Perform simulation and a tensile test using the MTS machine. Apply strain gauges to check for permanent deformation. Inspect for cracks or visible failure. <\/td><\/tr>
180.00 Hz <\/td>The fixed-base fundamental natural frequencies of the stowed optical assembly. 
Method of evaluation: Simulation and perform an impact hammer test using accelerometers and a DAQ system to identify resonance peaks. <\/td><\/tr>
10.00 % <\/td>Reduction of part count to simplify assembly. 
Method of evaluation: Compare the part count with the previous year\u2019s design iteration. <\/td><\/tr>
10.00 % <\/td>Achieve a 10% reduction in total structural weight (including lenses) from the initial CAD design while maintaining a factor of safety of 1.25 against yield. 
Method of evaluation: Compare the final assembly weight on a digital scale with initial NX mass-property estimates. <\/td><\/tr>
0.00039 in <\/td>Resolution of secondary mirror adjustment. 
Method of evaluation: Set up the optics and image a sample target located 72 inches away. <\/td><\/tr>
0.0039 in <\/td>The optical assembly shall maintain focus over an operational soak temperature of 122\u00b0F \u00b13.6\u00b0F for 60 minutes. Thermal expansion (CTE) induced defocus shall not exceed. 
Method of evaluation: Simulate the assembly and place it in an oven; use markers to detect any lens displacement. <\/td><\/tr>
12 G <\/td>The optical structural assembly (OSA) shall maintain a positive Margin of Safety (MoS) > 0.0 under Quasi-Static Limit Loads of 12G (Axial). 
Method of evaluation: Perform simulations and verify simulations through tests. <\/td><\/tr>
1.5 FS <\/td>Factor of safety against ultimate. <\/td><\/tr>
1.25 FS <\/td>Factor of safety against yield. <\/td><\/tr>
14 % <\/td>Reduction of obstruction of the primary lens. <\/td><\/tr><\/tbody><\/table><\/figure>\n\n\n\n

Design\/Manufacturing<\/h2>\n\n\n\n
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