Written By: Daniel Asante

Introduction

The purpose of this section is to include  structural analysis simulations to verify that the complete CubeSat structure, including internal and external components such as the satellite bus, solar wing frame, mounting interfaces, and deployables, can withstand the mechanical and thermal loads expected during launch and space operation. The simulations are then verified that they align with the structural verification requirements outlined in the SpaceX Falcon 9 Rideshare Payload User’s Guide [RPUG] and applicable CubeSat design standards.

This document provides an overview of:

• The structural configuration of the CubeSat.

• The design loads and constraints.

• Simulation methodology and software tools used (ANSYS Mechanical).

• Modal, static, thermal, and buckling analysis results.

• Compliance with safety factors and launch provider requirements.

Structural Configuration Overview

• Satellite form factor: 3U CubeSat (100 mm × 100 mm × 340.5 mm).

• Primary structure material: AL6061-T6 (for rails, Shells, and wing frame).

• Mounting interface: Compatible with EXOpod NOVA deployer.

• Subsystems included:

  • Solar wing deployment frame

  • Payload Reflector and Feed Arm

  • Stacked Shells

  • Corner Rails

The following tests will results in the structural finite element analysis performed on the engineering model primary structure of ArcticSat. The primary structure of ARCTICSAT is defined as the structure consisting of corner rails combined with the module shells.   All components/parts under the secondary structure  have been removed and detailed analyses will be conducted in Phase D.

Modal Analysis

Modal Analysis is a form of finite Element Analysis which provides information on the natural frequencies and mode shapes of a structure or component. All structures and components have natural frequencies and its essential to understand these natural frequencies so we can try to predict how a structure or component will behave when exposed to vibrational frequencies in the field.

Typically, a structure or component is constrained and when a modal analysis is executed, it will extract the frequencies at which the component or structure will naturally resonate. By knowing these resonance frequencies of  a structure or component, we can design our parts to ensure that these resonant frequencies are outside the range of operation of our application.

According to the SpaceX Falcon 9 Rideshare Payload User Manual, payloads must have no elastic natural frequencies below 40 Hz. An elastic natural frequency is defined as any frequency response of the payload with any modal participation, as computed any a fixed-base modal analysis.

Deorbiting

Roller Switches

Roller switches shall not exceed 3.00 N to ensure that the deployment switches do not interfere with or damage the deployer mechanism [Exolaunch] and that they reliably activate without posing a risk to structural integrity or proper ejection.