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US 10,518,910 B1Granted
Agile attitude control system for small spacecraft
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorsMarcello Romano, Paul Oppenheimer
Life of this patent
Estimating the term…
Abstract
An agile attitude control system (AACS) that is a three axis attitude control device for small spacecraft based on miniature single gimbal control moment gyroscopes (SGCMGs) actuators. The AACS enables agile attitude slewing and accurate pointing/tracking for spacecraft made of multiple CubeSat units, or, more generally, for nanosatellites.
Claims15
An agile attitude control system (AACS) comprising:
- a plurality of miniature single gimbal control moment gyroscopes (SGCMGs), wherein each of said miniature SGCMGs further comprises:
- a single flywheel rotor assembly, said single flywheel rotor assembly further comprising:
- a rotor motor,
- one or more rotor bearings, and
- a rotor housing enclosing said rotor motor and said one or more rotor bearings;
- a gimbal assembly, said gimbal assembly further comprising:
- a gimbal motor,
- a harmonic drive gear,
- one or more gimbal bearings, and
- a gimbal housing enclosing said gimbal motor and said one or more gimbal bearings;
- a slip ring assembly coupled with said single flywheel rotor assembly and with said gimbal assembly, said slip ring assembly located between said single flywheel rotor assembly and said gimbal assembly;
- a magnetic encoder coupled with said gimbal assembly;
- and
- a hall sensor coupled with said single flywheel rotor assembly;
- and
- one or more electronic components coupled with said plurality of miniature SGCMGs,
- wherein said agile attitude control system is entirely contained within the volume of 1 liter or less and has a total mass of 1 kilogram or less.
14 more elements
A miniature single gimbal control moment gyroscope (SGCMG) comprising:
- a single flywheel rotor assembly, said single flywheel rotor assembly further comprising:
- a rotor motor,
- one or more rotor bearings, and
- a rotor housing enclosing said rotor motor and said one or more rotor bearings;
- a gimbal assembly, said gimbal assembly further comprising:
- a gimbal motor,
- a harmonic drive gear,
- one or more gimbal bearings, and
- a gimbal housing enclosing said gimbal motor and said one or more gimbal bearings;
- a slip ring assembly coupled with said single flywheel rotor assembly and with said gimbal assembly, said slip ring assembly located between said single flywheel rotor assembly and said gimbal assembly;
- a magnetic encoder coupled with said gimbal assembly;
- and
- a hall sensor coupled with said single flywheel rotor assembly.
10 more elements
An agile attitude control system (AACS) for three axis attitude control of small spacecraft comprising:
- a plurality of miniature single gimbal control moment gyroscopes (SGCMGs), wherein each of said miniature SGCMGs further comprises:
- a single flywheel rotor assembly, said single flywheel rotor assembly further comprising:
- a rotor motor,
- one or more rotor bearings, and
- a rotor housing enclosing said rotor motor and said one or more rotor bearings;
- a gimbal assembly, said gimbal assembly further comprising:
- a gimbal motor,
- a harmonic drive gear,
- one or more gimbal bearings, and
- a gimbal housing enclosing said gimbal motor and said one or more gimbal bearings;
- a slip ring assembly gimbal coupled with said single flywheel rotor assembly and with said gimbal assembly, said slip ring assembly located between said single flywheel rotor assembly and said gimbal assembly;
- and
- one or more electronic means coupled with said plurality of miniature SGCMGs, said one or more electronic means for controlling said plurality of miniature SGCMGs to provide three axis attitude control of external small spacecraft,
- wherein said agile attitude control system is entirely contained within the volume of 1 liter or less and has a total mass of 1 kilogram or less.
11 more elements
Dependencies are inferred from the claim text.