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Technology Maturation of a Dual-Spinning CubeSat Bus

Completed TRL 6 (started at 4, targeting 6)

Description

This microgravity parabolic flight will serve to verify the mechanical and controlled functionality of a dual-spinning CubeSat bus (2U bus attached to a 1U payload via a rotating scanning assembly). This is a student-led effort whose assembly features a custom design that integrates a motor, bearing, slipring, motor controller, and encoder. The control algorithms are likewise developed by students. The application of this dual-spinning bus is in the development of a novel platform for 1U CubeSat payloads. It enables and enhances Earth-observing missions with instruments that require periodic rotation to operate. The first use of this proposed technology is the MicroMAS (Micro-sized Microwave Atmospheric Sounder) CubeSat developed by MIT and MIT Lincoln Laboratory.

Presentation (2015): Microwave Radiometer instrument
Paper (2013): MicroMAS: A First Step Towards a Nanosatellite Constellation for Global Storm Observation

Problem Statement
This experiment addresses the need for more capable and enabling Earth sensor platforms on a nano-satellite scale. Our dual-spinning CubeSat consists of a 2U bus and 1U payload. The bus contains all the subsystems necessary for satellite operation (power, communications, avionics, attitude determination and control, and thermal). It houses a scanning assembly, which allows the payload to rotate with respect to the bus. This scanning assembly contains a slipring to accommodate the electrical interface between the payload and bus. The attitude control system is designed to keep the bus 3-axis stabilized for a 60 rpm rotation rate of a 1 kg payload.

Benefits

Future Customers
The first use of this proposed technology is the MicroMAS (Micro-sized Microwave Atmospheric Sounder) CubeSat developed by MIT and MIT Lincoln Laboratory. The payload is a microwave radiometer, and the dual-spinner bus must rotate the payload at a rate of up to 1 Hz while maintaining 1 degree of pointing control. The mission is expected to launch in early 2014. Other potential customers are the cubeSat community and Earth observation scientists.

Details

Technology areaCommunications, Navigation, and Orbital Debris Tracking and Characterization Systems > Optical Communications > Pointing, Acquisition, and Tracking Techniques and Technologies
ProgramFlight Opportunities (FO)
Lead organizationMassachusetts Institute of Technology, Cambridge, MA
Start date2013-12-01
End date2016-12-31

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