Method and apparatus for singularity avoidance for control moment gyroscope (CMG) systems without using null motion

dc.contributor.authorAgrawal, Brij N.
dc.contributor.authorKim, Jae Jun
dc.contributor.authorSands, Timothy Andrew
dc.contributor.corporateResearch and Sponsored Programs Office (RSPO)
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.date.accessioned2017-02-16T23:23:45Z
dc.date.available2017-02-16T23:23:45Z
dc.date.issued2017-02-14
dc.descriptionPatenten_US
dc.description.abstractA method is described for avoiding gyrocopic singularities during attitude correction to a sytem, such as a spacecraft having a CMG array. The method receives a corrective torque vector µ and gimbal angle values δ for each of at least three gimbal within the CMG array. The method a a Jacobian matrix A as a function of gimbal angle value δ. A. lf the determinant is not equal to zero, it is not singular, and the method calculate a gimbal rate δ using a using a pseudo-inverse steering law equation. lf the determinant is equal to zero, it is singular, and the method calculate a gimbal rate δ using a singularity avoidance steering law equation. The gimbal rate δ is output and can be applied to a CMG array resulting in applied torque to a spacecraft and attitude correction.en_US
dc.identifier.otherUS 9,567,112 B1
dc.identifier.urihttps://hdl.handle.net/10945/51921
dc.publisherThe Government of the United States of America, as represented by the Secretary of the Navy, Washington, DC (US)en_US
dc.relation.ispartofseriesPatents
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titleMethod and apparatus for singularity avoidance for control moment gyroscope (CMG) systems without using null motionen_US
dc.typePatenten_US
dspace.entity.typePublication
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relation.isOrgUnitOfPublication.latestForDiscovery6b655e58-5689-4419-8db8-562f3b19b2d0
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