• Home
  • Current congress
  • Public Website
  • My papers
  • root
  • browse
  • IAC-19
  • B4
  • 6B
  • paper
  • Low Mass Articulated Boom for Small Satellites

    Paper number

    IAC-19,B4,6B,2,x54421

    Author

    Ms. Katelyn Ball, Canada, University of Alberta

    Coauthor

    Prof. Ian Mann, Canada, University of Alberta

    Coauthor

    Mr. Yunqui Bai, Canada, University of Alberta

    Coauthor

    Dr. Dan Sameoto, Canada, University of Alberta

    Coauthor

    Dr. David Miles, United States, University of Iowa

    Coauthor

    Mr. Collin Cupido, Canada, University of Alberta

    Coauthor

    Mr. David Barona, Canada, University of Alberta

    Coauthor

    Mr. Charles Nokes, Canada

    Coauthor

    Prof. Duncan Elliott, Canada, University of Alberta

    Coauthor

    Mr. Christopher Robson, Canada, University of Alberta

    Year

    2019

    Abstract
    Deployable boom systems for nano-satellites are in high demand for a variety of applications but require innovative design solutions to meet mass requirements and launch vehicle restrictions on stowed spacecraft volume. Reliable deployment, and overall simplicity are key factors in boom design. Presented here is an innovative low cost, low mass deployable articulated boom system for payloads required to operate at a known position from the spacecraft’s body. The boom is simple enough to be used by University student teams who may have little experience in building intricate, high risk, boom systems. The boom was space-qualified in orbit through its flight on the three unit (3U) Experimental Albertan Satellite #1 (Ex-Alta 1) spacecraft. Recent design developments incorporating a post-deployment boom locking mechanism is also presented.
    The articulated deployable boom has a mass of 74 grams, suited to hold small payloads such as the Digital Fluxgate Magnetometer (DFGM) instrument developed at the University of Alberta. The boom is mounted to the spacecraft’s exterior and equipped with an elbow and shoulder joint to deploy the sensor 60 centimeters away from the cubesat body. At this distance, the noise in the instrument data caused by electromagnetic interference from the spacecraft electronics and permanent DC spacecraft fields is significantly reduced. While stowed, the boom sits external to the spacecraft’s body, but complies to the volume envelope imposed by the NanoRacks CubeSat Deployer system.
    On Ex-Alta 1, the boom had a non-locking elbow joint actuated by an internally mounted extension spring. Although simple and reliable, it posed a risk of damaging other spacecraft components. The revised elbow joint design allows the magnetometer sensor to be rigidly deployed to a known position and orientation relative to the spacecraft reference frame within 1 degree (1 $\sigma$) in two components, excluding rotation around boom long axis. This was achieved with small sleeve mounted to the end of one of the tubes, coupling the two tubes upon deployment. In Summer of 2019, the design and performance of the original and modified booms are to be tested on parabolic aircraft flights. The behaviour of the booms during deployment will be observed. Reliability, repeatability, and boom dynamics during deployment will be measured.
    The simplicity, high reliability, low stowed volume and mass of the articulated boom makes it a suitable design to be used on nano-satellites, especially those on a limited budget.
    Abstract document

    IAC-19,B4,6B,2,x54421.brief.pdf

    Manuscript document

    IAC-19,B4,6B,2,x54421.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.