Session
Frank J. Redd Student Competition
Location
Salt Palace Convention Center, Salt Lake City, UT
Abstract
Small satellites commonly utilize deployable systems to expand their space environment sensing and power generation capabilities. Sensing the space environment is required for certain missions, as it provides information about space weather events such as scintillation and solar flares. To accurately measure the space environment, the probes must be placed away from the spacecraft while in orbit. This paper presents the development, analysis, and qualification of a hinge and Hold-Down and Release Mechanism (HDRM) assembly for deployable space weather probes. These two mechanisms were developed as an assembly to be lightweight, compact, and reliable for deploying space weather probes. The hinge provides controlled rotational deployment while incorporating positional sensing and a mechanical locking feature. The HDRM utilizes a resistively heated polymer line to constrain the probe during launch and release the probe when cut. Multiple design iterations were developed across three missions, improving material selection, manufacturability, and reliability. Analytical modeling demonstrates sufficient deployment torque with a minimum factor of safety exceeding 24 under elevated thermal conditions. Environmental testing, including vibration (up to 9.47 GRMS), thermal cycling (-50°C to 90°C), and vacuum operation validated system performance. Operational testing demonstrated consistent release times between 10 s and 17 s for the selected thermal line configuration. Results demonstrate that the integrated hinge and HDRM assembly provides a compact, low-cost, and reliable deployment solution suitable for small satellite missions requiring deployable probes.
Document Type
Event
Development, Analysis, and Qualification of a Hinge and HDRM Assembly for Small Satellite Deployable Probes
Salt Palace Convention Center, Salt Lake City, UT
Small satellites commonly utilize deployable systems to expand their space environment sensing and power generation capabilities. Sensing the space environment is required for certain missions, as it provides information about space weather events such as scintillation and solar flares. To accurately measure the space environment, the probes must be placed away from the spacecraft while in orbit. This paper presents the development, analysis, and qualification of a hinge and Hold-Down and Release Mechanism (HDRM) assembly for deployable space weather probes. These two mechanisms were developed as an assembly to be lightweight, compact, and reliable for deploying space weather probes. The hinge provides controlled rotational deployment while incorporating positional sensing and a mechanical locking feature. The HDRM utilizes a resistively heated polymer line to constrain the probe during launch and release the probe when cut. Multiple design iterations were developed across three missions, improving material selection, manufacturability, and reliability. Analytical modeling demonstrates sufficient deployment torque with a minimum factor of safety exceeding 24 under elevated thermal conditions. Environmental testing, including vibration (up to 9.47 GRMS), thermal cycling (-50°C to 90°C), and vacuum operation validated system performance. Operational testing demonstrated consistent release times between 10 s and 17 s for the selected thermal line configuration. Results demonstrate that the integrated hinge and HDRM assembly provides a compact, low-cost, and reliable deployment solution suitable for small satellite missions requiring deployable probes.
