warning

🚧 This document is still being actively worked on and is subject to change. 🚧

Authors	Janik Hackel
Responsible	Janik Hackel
Last Updated	10/12/2025, 12:48:54 PM
Last Author	Kai Berszin

Sine Burst

Subject	Description
Testing Model	Performed on the fully assembled CubeSat
Product Description	Sine Burst test
Test Reason	Verify that the primary structure withstands the slighly heavier satellite

• Issue date: <Insert Date>
• Approved by: <Insert Name>
• Responsible Test Engineer: <Insert Name>

Sine Burst

Testing Equipment

• Shakertable
• Structural Sensors (defined in Overview Strucutral Testing)
• EQM Adapter and EQM Model

Test Method

• A near uniform acceleration for in all principal directions. Todo: In which direction are we looking when starting.
• Duration: 1h for each axis
• The sensors used are defined in the Strucutral Testing Overview page. However, we only use the sensors on the panels, primary structure, ADCS Cube and Payload.
• The burst frequency should be 1/3 below the lowest structural eigenfrequency. Todo: Find out the lowest eigenfrequency.
• We omit to adjust the input acceleration to account for fynamic amplification (Todo: Check that we have an amplification of max around 1.2)

Check Condition and Requirements

• The strucutre should withstand 1.4 times (NASA Prototype (Qualification) Testing criteria) of the max load it expects. Todo: Max load it expects on the whole flight

Test Results

<Describe the results of the test in a short fasion>

Test Judgement

The structure shouldn't show any buckles or yielding that exceeds 10% of the max load it expects. Todo: Check if this makes sense.

Appendix

Photo of testing

<Insert picture of the exact testing configuration>

Testing data

<Insert a table or diagram of the exact output of the test (without intepretation)>