Session
Session V: Advanced Technologies & Subsystems, Components & Sensors I
Abstract
Utah State University, the University of Washington, and Virginia Tech are teamed to form the Ionospheric Observation Nanosatellite Formation (IONF) to investigate ionospheric turbulence and formation-flying requirements for multiple small satellite missions. A communication subsystem for the mission will be composed of an uplink, a downlink, and satellite-tosatellite crosslink. The uplink will operate at UHF. The downlink and crosslink both will operate in the S-band. The design and successful implementation of a low profile, compact element with desirable properties at UHF within the physical constraints of a nanosatellite is a challenge. A resonant loop antenna mounted above the bottom surface of the spacecraft was selected for a possible satellite antenna. The linearly polarized resonant loop was chosen to satisfy the physical requirements of the spacecraft while still achieving efficient operation for a UHF signal. A full-scale prototype was fabricated to measure the frequency dependent characteristics of the antenna. A gamma match and a quarter-wave sleeve balun transformer were integrated to the system to optimize the impedance match between the antenna and the transmission line. Measured results presented in this paper indicate sufficient performance for the initial design. The antenna operating bandwidth of approximately one percent covers the estimated bandwidth of the uplink channel. However, integration with other components during fabrication could easily detune the resonant frequency of the loop antenna out of the required band. Further development of the uplink antenna design should include adjustable mounts and a capacitive tuning element.
Electrical Design and Testing of an Uplink Antenna for Nanosatellite Applications
Utah State University, the University of Washington, and Virginia Tech are teamed to form the Ionospheric Observation Nanosatellite Formation (IONF) to investigate ionospheric turbulence and formation-flying requirements for multiple small satellite missions. A communication subsystem for the mission will be composed of an uplink, a downlink, and satellite-tosatellite crosslink. The uplink will operate at UHF. The downlink and crosslink both will operate in the S-band. The design and successful implementation of a low profile, compact element with desirable properties at UHF within the physical constraints of a nanosatellite is a challenge. A resonant loop antenna mounted above the bottom surface of the spacecraft was selected for a possible satellite antenna. The linearly polarized resonant loop was chosen to satisfy the physical requirements of the spacecraft while still achieving efficient operation for a UHF signal. A full-scale prototype was fabricated to measure the frequency dependent characteristics of the antenna. A gamma match and a quarter-wave sleeve balun transformer were integrated to the system to optimize the impedance match between the antenna and the transmission line. Measured results presented in this paper indicate sufficient performance for the initial design. The antenna operating bandwidth of approximately one percent covers the estimated bandwidth of the uplink channel. However, integration with other components during fabrication could easily detune the resonant frequency of the loop antenna out of the required band. Further development of the uplink antenna design should include adjustable mounts and a capacitive tuning element.
