Title:
Structural Design, Analysis, and Test of the Prox-1
Spacecraft
Structural Design, Analysis, and Test of the Prox-1
Spacecraft
Author(s)
Willingham, Allison L.
Advisor(s)
Spencer, David A.
Editor(s)
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Abstract
HE Prox-1 spacecraft is Georgia Institute of Technology’s entry into the 7th University Nanosatellite Program
Competition, a two year cycle competition for the AFRL where university teams consisting of both graduate and
undergraduate students design, build, and test a 50 kg nanosatellite for a team-specified mission. Judging is based on
various presentations to the AFRL review teams, importance of the mission to AFRL objectives, and development
of a sound nanosatellite system among other criteria [5].
Prox-1 is a nanosatellite which will demonstrate the use of low-thrust propulsion for automated safe trajectory
control during proximity operations. Passive, image based observations will be used for the navigation and closed loop attitude control of Prox-1 relative to a deployed CubeSat. Prox-1’s objectives include: Rendezvous and
proximity operations with a target CubeSat, automated relative navigation and trajectory control, closed-loop
attitude control based upon automated image processing, and relative orbit determination using image-based angle
and range estimates, validated by the Mission Operations System [4]. The student’s particular research involved
design, build, and test of the structural components of the Prox-1 satellite. This paper will describe what design
information was based on previous Prox-1 structure iterations, what design modifications were made to improve the
structure’s capabilities and meet requirements, what analysis and testing was performed to validate those
requirements, and what was needed to integrate with the subsystem components.
When referring to different plate orientations in this document, the Prox-1 body coordinate frame is used. This is
centered at the middle of the Lightband interface ring on the bottom plate, and in the same plane as the Launch
Vehicle Interface. In the final structure configuration, the X-axis is pointing toward the Ppod deployment direction
and cameras, the positive Y-axis is in the direction opposite of the thruster, and the Z-axis is pointing from the LVI
plate toward the top plate [2]. All figures depicting the spacecraft will have this body coordinate frame pictured
Sponsor
Date Issued
2012-12-01
Extent
Resource Type
Text
Resource Subtype
Masters Project
Rights Statement
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