Lightweight Control Moment Gyros for Small Satellites
Agency / Branch:
DOD / USAF
Reconnaissance and surveillance missions, using small robust spacecraft, may require that sensors be rapidly positioned to suit the specific mission requirements. These maneuvers are most effectively conducted using a CMG with an output torque of 2-100 ft.-lbs.; however, the smallest CMG currently available has an output torque that is 225 ft.-lbs. and has a weight of 112 lbs. In order to meet the needs of small robust spacecraft missions, Phase I of this project, carried out by AMT with support from Honeywell Space Systems Operations (HSSO), will attempt to demonstrate the feasibility of producing new CMGs with output torques ranging from 2-100 ft.-lbs. having a weight of less than 40 lbs. It is expected that the reliability will be typical of HSSO CMG products which is higher than .9995 after eight years of operation in space. Lightweight CMG requirements for small robust spacecraft will be established. A preliminary design of a CMG will be generated using advanced composites. A model of the smallsat CMG will be fabricated to demonstrate the overall size and componentry needed. Smallsat CMG performance and reliabililty analysis will be conducted to demonstrate that mission requirements can be met at low weight and high reliability. A Phase II plan to complete development of a prototype CMG will be developed, including a preliminary market assessment and business strategy development task.
Small Business Information at Submission:
Principal Investigator:William E. Davis
3611 S. Harbor Blvd., Suite 225 Santa Ana, CA 92704
Number of Employees: