Vibrational Analysis of a 12U Chassis

Abstract

The objective of this research is to characterize how the natural frequencies of AFIT's CubeSat design can be controlled to meet launch vehicle requirements while increasing the internal and external volume available for payload and bus components as the chassis increases in size. A reliable Finite Element (FE) model is created and validated using NASA's General Environmental Verification Standards (GEVS) vibrational test on the 12U chassis. The validated FE model proves that current boundary conditions and geometric properties with minimized chassis wall thicknesses to maximize usable internal and external volume maintain a first frequency of the fully loaded 12U chassis above 70 Hz. However, the constraints on the 1U mass stacks aren't sufficient to prevent structural failure of the mass stacks, and internal supports are necessary to maintain the structural integrity of the mass stacks.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Mar 24, 2016
Accession Number
AD1054559

Entities

People

  • Daniel G. Miller

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Artificial Satellites
  • Computer-Aided Design
  • Control Systems
  • Doppler Effect
  • Engineering
  • Failure Mode And Effect Analysis
  • Frequency
  • Geometry
  • Governments
  • Launch Vehicles
  • Materials
  • Measurement
  • Modal Analysis
  • Modulus Of Elasticity
  • Payload
  • Random Vibration
  • Resonant Frequency
  • Small Satellites
  • Space Objects
  • Spacecraft
  • Standards
  • Test Equipment
  • Test Facilities
  • United States
  • United States Government
  • Vibrometers

Readers

  • Computational Modeling and Simulation
  • Electrical Engineering
  • Missile Defense Systems.