Control of nutation in a spacecraft
Patent 4504032 Issued on March 12, 1985. Estimated Expiration Date: 
March 12, 2002. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
March 12, 2002. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References Re30429 3437288 3591108 3695554 3830447 Active nutation controller Active nutation control system for space vehicle Patent #: 4370716 InventorsAssigneeApplicationNo. 06/356824 filed on 03/10/1982US Classes:244/170By nutation damperExaminersPrimary: Barefoot, Galen L.Attorney, Agent or FirmInternational ClassesB64G 1/24 (20060101)B64G 1/28 (20060101) B64G 1/38 (20060101) B64G 1/36 (20060101) AbstractA method and apparatus for damping nutation in a spacecraft to essentially zero in less than one nutation period which has a spin axis, first and second transverse axes and a characteristic nutation frequency λ. A time interval t1 after the transverse momentum of the spacecraft about one transverse axis, such as the Y axis has crossed zero, a torque of magnitude TY is applied to the spacecraft about its Y transverse axis. After a time interval t2, the application of this torque is terminated. The time t1 =1/λ cos-1 (hY0 λ/2TY) and the time t2 =2/λ sin-1 (hY0 λ/2TY), where hY0 is the peak body momentum about the Y transverse axis.Other References
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