초록 ▼

A method and system for reducing the stepping disturbances generated by a stepping mechanism is disclosed. The method is to select a desired stepping rate to step the stepping mechanism. The method further selects two desired disturbance stepping rates, one fast stepping rate and one slow stepping r

A method and system for reducing the stepping disturbances generated by a stepping mechanism is disclosed. The method is to select a desired stepping rate to step the stepping mechanism. The method further selects two desired disturbance stepping rates, one fast stepping rate and one slow stepping rate to alternate stepping of the mechanism with the two stepping rates to generate an average stepping rate that is required for the mechanism, and thereby the stepping mechanism will not significantly excite the spacecraft structural mode, and the stepping disturbance is significantly reduced while the mechanism still perform nominally its desired stepping maneuvers.

대표청구항 ▼

1. A method of reducing disturbances induced by stepping an appendage having a structural frequency with a stepping mechanism having a stepping motor, the method comprising the steps of:generating a desired stepping rate from said structural frequency to step said appendage, wherein the desired step

1. A method of reducing disturbances induced by stepping an appendage having a structural frequency with a stepping mechanism having a stepping motor, the method comprising the steps of:generating a desired stepping rate from said structural frequency to step said appendage, wherein the desired stepping rate is calculated by solving ?n=0,1, . . . for s where s represents said stepper motor stepping at s times of said structural frequency; and stepping the appendage at said desired stepping rate, thereby reducing the induced stepping disturbances generated by said stepping mechanism. 2. The method of claim 1, wherein said desired stepping rate includes 3 times of said structural frequency.3. The method of claim 1, wherein said desired stepping rate includes 2 times of said structural frequency.4. The method of claim 1, wherein said desired stepping rate includes 0.75 times of said structural frequency.5. The method of claim 1, wherein said desired stepping rate includes 0.667 times of said structural frequency.6. The method of claim 1, wherein said desired stepping rate includes 0.4285 times of said structural frequency.7. The method of claim 1, wherein said desired stepping rate includes 0.4 times of said structural frequency.8. The method of claim 1, wherein said desired stepping rate includes 0.3 times of said structural frequency.9. The method of claim 1, wherein said desired stepping rate includes 0.2857 times of said structural frequency.10. The method of claim 1, wherein said mechanism comprises a solar wing driver.11. The method of claim 1, where said mechanism comprises an antenna reflector positioner.12. The method of claim 1, wherein said mechanism comprises a payload platform positioner.13. The method of claim 1, wherein said mechanism comprises a payload scanning gimbal.14. In a spacecraft having at least one solar array controlled by a stepping mechanism having a stepper motor for rotating the at least one solar array, the at least one solar array having a structural frequency, a method for reducing stepping disturbances, comprising the steps of:generating a desired first stepping rate and a desired second stepping rate slower than the first stepping rate from said structural frequency of said at least one solar array to step said stepping mechanism; and alternately stepping between said first stepping rate and said second stepping rate to generate an average stepping rate of said stepping mechanism that equals to a desired stepping rate of the rotational rate of the at least one solar array, and thereby reducing the induced stepping disturbances generated by said stepper motor. 15. The method of claim 14, further comprising the step of calculating said desired stepping rate by solving n=0,1, . . . for S where s represents said stepper motor stepping at s times of said structural frequency.16. The method of claim 14, whererin said desired stepping rate includes 3 times of said structural frequency.17. The method of claim 14, wherein said desired stepping rate includes 2 times of said structural frequency.18. The method of claim 14, wherein said desired stepping rate includes 0.75 times of said structural frequency.19. The method of claim 14, wherein said desired stepping rate includes 0.667 times of said structural frequency.20. The method of claim 14, wherein said desired stepping rate includes 0.4285 times of said structural frequency.21. The method of claim 14, wherein said desired stepping rate includes 0.4 times of said structural frequency.22. The method of claim 14, wherein said desired stepping rate includes 0.3 times of said structural frequency.23. The method of claim 14, wherein said desired stepping rate includes 0.2857 times of said structural frequency.24. The method of claim 14, wherein said stepping mechanism comprises a solar wing driver.25. An apparatus for reducing stepping disturbances generated by a stepper motor which is controlled by a mechanism exciting a structural frequency, the apparatus comprising:means for generating a desired stepping rate from said structural frequency to step said mechanism; and means for stepping said mechanism at said desired stepping rate of said structural frequency, thereby reducing the induced stepping disturbances generated by said stepper motor; wherein the means for stepping the stepping mechanism at said desired stepping rate of said structural frequency comprises means for stepping said stepper motor at a first stepping rate and a second stepping rate slower than the first stepping rate to generate an average stepping rate that equals said desired stepping rate. 26. The apparatus of claim 25, wherein said desired stepping rate is calculated by solving n=0,1, . . . for s where s represents said stepper motor stepping at s times of said structural frequency.27. The apparatus of claim 25, wherein said desired stepping rate includes 3 of said structural frequency.28. The apparatus of claim 25, wherein said desired stepping rate includes 2 times of said structural frequency.29. The apparatus of claim 25, wherein said desired stepping rate includes 0.75 times of said structural frequency.30. The apparatus of claim 25, wherein said desired stepping rate includes 0.667 times of said structural frequency.31. The apparatus of claim 25, wherein said desired stepping rate includes 0.4285 times of said structural frequency.32. The apparatus of claim 25, wherein said desired stepping rate includes 0.4 times of said structure frequency.33. The apparatus of claim 25, wherein said desired stepping rate includes 0.3 times of said structural frequency.34. The apparatus of claim 25, wherein said desired stepping rate includes 0.2857 times of said structural frequency.35. The apparatus of claim 25, wherein said device comprises a solar wing driver.36. The apparatus of claim 25, wherein said device comprises an antenna reflector positioner.37. The apparatus of claim 25, wherein said device comprises a payload platform positioner.38. The apparatus of claim 25, wherein said device comprises a payload scanning gimbal.