A Deployable Conical Log Spiral Antenna for Small Spacecraft: Mechanical Design and Test
We present the design and manufacturing of a deployable conical log spiral spring antenna for small spacecraft, along with a test campaign to evaluate its suitability for space applications. The conical spring was 45.7 cm in height, with base and apex diameters of 18.9 and 2.8 cm, respectively. The...
Saved in:
| Main Authors: | , , , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2025-04-01
|
| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/12/4/326 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1849712041014591488 |
|---|---|
| author | Lewis R. Williams Natanael Hjermann Bendik Sagsveen Arthur Romeijer Karina Vieira Hoel Lars Erling Bråten |
| author_facet | Lewis R. Williams Natanael Hjermann Bendik Sagsveen Arthur Romeijer Karina Vieira Hoel Lars Erling Bråten |
| author_sort | Lewis R. Williams |
| collection | DOAJ |
| description | We present the design and manufacturing of a deployable conical log spiral spring antenna for small spacecraft, along with a test campaign to evaluate its suitability for space applications. The conical spring was 45.7 cm in height, with base and apex diameters of 18.9 and 2.8 cm, respectively. The spring had a mass of 0.138 kg and was constructed from a carbon fiber-infused epoxy matrix with an embedded coaxial cable. We conducted dynamic and thermal mechanical analysis to determine the coefficient of thermal expansion and glass transition temperature. The initial 10 compressions of the spring shortened the structure’s overall height, but the change had a negligible effect on the antenna’s radio frequency (RF) performance. Thermal cycling between −70 °C and 80 °C did not cause any damage or deformation to the spring structure. Outgassing tests were conducted in a thermal vacuum chamber, and the total mass loss was 0.03%. We conducted vibration tests representative for a typical launch vehicle, and all natural frequencies remained stable above 250 Hz, while the antenna was stowed, satisfying launch vehicle requirements. Post-test functional checks confirmed that there was no change in antenna functionality. The environmental test results provide confidence that the antenna is suitable for spacecraft applications. |
| format | Article |
| id | doaj-art-b7b0abef49c243e49c87e6eceb3f4812 |
| institution | DOAJ |
| issn | 2226-4310 |
| language | English |
| publishDate | 2025-04-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj-art-b7b0abef49c243e49c87e6eceb3f48122025-08-20T03:14:24ZengMDPI AGAerospace2226-43102025-04-0112432610.3390/aerospace12040326A Deployable Conical Log Spiral Antenna for Small Spacecraft: Mechanical Design and TestLewis R. Williams0Natanael Hjermann1Bendik Sagsveen2Arthur Romeijer3Karina Vieira Hoel4Lars Erling Bråten5Department of Technology Systems, The University of Oslo, Gunnar Randersvei 19, 2007 Kjeller, NorwayNorwegian Defence Research Establishment, Instituttveien 20, 2007 Kjeller, NorwayNorwegian Defence Research Establishment, Instituttveien 20, 2007 Kjeller, NorwayPulsaart by AGC Glass Europe, Rue Louis Blériot 12, 6041 Gosselies, BelgiumNorwegian Defence Research Establishment, Instituttveien 20, 2007 Kjeller, NorwayDepartment of Technology Systems, The University of Oslo, Gunnar Randersvei 19, 2007 Kjeller, NorwayWe present the design and manufacturing of a deployable conical log spiral spring antenna for small spacecraft, along with a test campaign to evaluate its suitability for space applications. The conical spring was 45.7 cm in height, with base and apex diameters of 18.9 and 2.8 cm, respectively. The spring had a mass of 0.138 kg and was constructed from a carbon fiber-infused epoxy matrix with an embedded coaxial cable. We conducted dynamic and thermal mechanical analysis to determine the coefficient of thermal expansion and glass transition temperature. The initial 10 compressions of the spring shortened the structure’s overall height, but the change had a negligible effect on the antenna’s radio frequency (RF) performance. Thermal cycling between −70 °C and 80 °C did not cause any damage or deformation to the spring structure. Outgassing tests were conducted in a thermal vacuum chamber, and the total mass loss was 0.03%. We conducted vibration tests representative for a typical launch vehicle, and all natural frequencies remained stable above 250 Hz, while the antenna was stowed, satisfying launch vehicle requirements. Post-test functional checks confirmed that there was no change in antenna functionality. The environmental test results provide confidence that the antenna is suitable for spacecraft applications.https://www.mdpi.com/2226-4310/12/4/326carbon composite springantennadeployableenvironmental test campaignsmall satellite |
| spellingShingle | Lewis R. Williams Natanael Hjermann Bendik Sagsveen Arthur Romeijer Karina Vieira Hoel Lars Erling Bråten A Deployable Conical Log Spiral Antenna for Small Spacecraft: Mechanical Design and Test Aerospace carbon composite spring antenna deployable environmental test campaign small satellite |
| title | A Deployable Conical Log Spiral Antenna for Small Spacecraft: Mechanical Design and Test |
| title_full | A Deployable Conical Log Spiral Antenna for Small Spacecraft: Mechanical Design and Test |
| title_fullStr | A Deployable Conical Log Spiral Antenna for Small Spacecraft: Mechanical Design and Test |
| title_full_unstemmed | A Deployable Conical Log Spiral Antenna for Small Spacecraft: Mechanical Design and Test |
| title_short | A Deployable Conical Log Spiral Antenna for Small Spacecraft: Mechanical Design and Test |
| title_sort | deployable conical log spiral antenna for small spacecraft mechanical design and test |
| topic | carbon composite spring antenna deployable environmental test campaign small satellite |
| url | https://www.mdpi.com/2226-4310/12/4/326 |
| work_keys_str_mv | AT lewisrwilliams adeployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT natanaelhjermann adeployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT bendiksagsveen adeployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT arthurromeijer adeployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT karinavieirahoel adeployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT larserlingbraten adeployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT lewisrwilliams deployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT natanaelhjermann deployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT bendiksagsveen deployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT arthurromeijer deployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT karinavieirahoel deployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest AT larserlingbraten deployableconicallogspiralantennaforsmallspacecraftmechanicaldesignandtest |