초록 ▼

The present invention10discloses a multi-segmented central post member with upper18, middle26, and lower28sections having a cup-holding element24, a utility member22and a clothes-hanging element16having a plurality of hook members40extending therefrom. The post segments have compatible male36and fem

The present invention10discloses a multi-segmented central post member with upper18, middle26, and lower28sections having a cup-holding element24, a utility member22and a clothes-hanging element16having a plurality of hook members40extending therefrom. The post segments have compatible male36and female threads38on their respective ends for establishing a rectilinear connection to the mating post segment. The bottom segment has a first end44which is tapered for easy insertion in sand or turf12. The threaded male portions36of the post segments are radially offset from the outer circumference to form retaining flanges42for the accessory units. The ends of the post segments with the threaded female recesses38have a similar retaining flange. The accessory units16, 22, 24have central recesses with a diameter slightly greater than the threaded male portion36but less than the diameter of the post segment thereby engaging the post segment during assembly by inserting the threaded male portion36through the central recess. A mesh tote bag32is provided for transport and storage. An elastic cord20is provided wherein one end thereof passes through a retaining aperture30of one post segment and the other end thereof passes through the retaining aperture30on another post segment. An auger-like tip50on the tapered end of the bottom post segment28is also disclosed.

대표청구항 ▼

The present invention10discloses a multi-segmented central post member with upper18, middle26, and lower28sections having a cup-holding element24, a utility member22and a clothes-hanging element16having a plurality of hook members40extending therefrom. The post segments have compatible male36and fem

The present invention10discloses a multi-segmented central post member with upper18, middle26, and lower28sections having a cup-holding element24, a utility member22and a clothes-hanging element16having a plurality of hook members40extending therefrom. The post segments have compatible male36and female threads38on their respective ends for establishing a rectilinear connection to the mating post segment. The bottom segment has a first end44which is tapered for easy insertion in sand or turf12. The threaded male portions36of the post segments are radially offset from the outer circumference to form retaining flanges42for the accessory units. The ends of the post segments with the threaded female recesses38have a similar retaining flange. The accessory units16, 22, 24have central recesses with a diameter slightly greater than the threaded male portion36but less than the diameter of the post segment thereby engaging the post segment during assembly by inserting the threaded male portion36through the central recess. A mesh tote bag32is provided for transport and storage. An elastic cord20is provided wherein one end thereof passes through a retaining aperture30of one post segment and the other end thereof passes through the retaining aperture30on another post segment. An auger-like tip50on the tapered end of the bottom post segment28is also disclosed. bit frequency as distortion angles.10. The method according to claim 1, wherein the pointing errors are periodic.11. The method according to claim 1, wherein the pointing errors include harmonics of orbit frequency.12. The method according to claim 1, further comprising: estimating an inertial to body frame quaternion. 13. A method for correcting payload pointing errors of a spacecraft, the method comprising: sensing the spacecraft attitude with an attitude sensor; determining an initial measurement unit angular rate; and estimating an orbit frequency of a distortion angle between an inertial measurement unit and the attitude sensor to determine a distortion angle between the payload and a reference frame of the attitude sensor. 14. The method according to claim 13, wherein the method employs an extended Kalman filter to estimate the orbit frequency component off the distortion angle between the inertial measurement unit and the attitude sensor.15. The method according to claim 14, wherein the extended Kalman filter comprises distortion angle states that correct for thermal distortion and attitude sensor error.16. The method according to claim 14, wherein the extended Kalman filter interprets variations in a measured attitude determination error at orbit frequency as a distortion angle.17. The method as recited in claim 13, wherein the attitude sensor comprises at least one of an earth sensor, a star tracker, and a sun sensor.18. An attitude control system for a spacecraft, comprising: a rate sensor; at least one attitude sensor; and a processor operable to estimate an orbit frequency distortion angle between the rate sensor and the at least one attitude sensor. 19. The attitude control system according to claim 18, wherein the processor is further operable to estimate an inertial to body frame quaternion of the spacecraft.20. The attitude control system according to claim 18, wherein the rate sensor is arranged in the vicinity of a spacecraft payload to minimize angular distortions between the rate sensor and the spacecraft payload.21. The attitude control system according to claim 18, wherein the processor is further operable to estimate bias in the rate sensor measurements.22. The attitude control system according to claim 18, wherein the at least one attitude sensor comprises at least one of an earth sensor, a star tracker, and a sun sensor.23. The attitude control system as recited in claim 18, wherein the rate sensor comprises an inertial measurement unit.24. The attitude control system as recited in claim 18, wherein the orbit frequency distortion angle is due to at least one of thermal distortion of the spacecraft and spacecraft attitude sensing errors.25. The attitude control system according to claim 18, wherein the orbit frequency distortion angle is estimated by an extended Kalman filter.26. The attitude control system according to claim 25, wherein the extended Kalman filter comprises a model for variations of distortion angles at orbit frequency.27. The attitude control system according to claim 25, wherein the Kalman filter interprets variations in measured attitude determination at orbit frequency as distortion angles.28. The attitude control system according to claim 18, wherein the attitude control system is adapted to correct pointing errors that are periodic.29. The attitude control system according to claim 28, wherein the pointing errors include harmonics of orbit frequency.30. An attitude control system for a spacecraft, the attitude control system comprising: an inertial measurement unit; at least one attitude sensor operable to sense spacecraft attitude; and a processor operable to determine an inertial measurement unit angular rate and estimate an orbit frequency component of a distortion angle between the inertial measurement unit and the sensed attitude to determine a distortion angle between a spacecraft payload and a reference frame of the attitude sensor. 31. The atti