Session
Technical Session 8: Advanced Technologies II
Location
Utah State University, Logan, UT
Abstract
A high-speed data downlink system provides many challenges for a CubeSat design. Two major aspect are an adequate power management as well as the thermal implications of the dissipated power. The goal of the 6U CubeSat EIVE is to prove the feasibility of an E-band link at 71-76 GHz and explore the influence of different atmospheric conditions on the link quality. The requirements of the E-band transmitter in terms of mass, volume, power and pointing accuracy outline the specific constraints imposed on the design of the satellite bus. The major design drivers of the system are the peak power demand of 60 W for the payload itself and the required pointing accuracy of less than 1◦. To cope with these demands, general design considerations, the choice of the orbit and the operation of the satellite are discussed. A special focus is the power generation and consumptions by means of a dynamic attitude and power simulation. The thermal simulation is verified by building a detailed structural and thermal replica of the satellite to investigate the heat dissipation. An overview of the current EIVE CubeSat platform design concludes this paper.
The EIVE CubeSat - Developing a Satellite Bus for a 71-76 GHz E-Band Transmitter Payload
Utah State University, Logan, UT
A high-speed data downlink system provides many challenges for a CubeSat design. Two major aspect are an adequate power management as well as the thermal implications of the dissipated power. The goal of the 6U CubeSat EIVE is to prove the feasibility of an E-band link at 71-76 GHz and explore the influence of different atmospheric conditions on the link quality. The requirements of the E-band transmitter in terms of mass, volume, power and pointing accuracy outline the specific constraints imposed on the design of the satellite bus. The major design drivers of the system are the peak power demand of 60 W for the payload itself and the required pointing accuracy of less than 1◦. To cope with these demands, general design considerations, the choice of the orbit and the operation of the satellite are discussed. A special focus is the power generation and consumptions by means of a dynamic attitude and power simulation. The thermal simulation is verified by building a detailed structural and thermal replica of the satellite to investigate the heat dissipation. An overview of the current EIVE CubeSat platform design concludes this paper.
