Satellite orbit maintenance system
April 16, 2016. 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 3866025 Attitude control for space vehicle Method of controlling an extruder Spin rate timing system Method and apparatus for controlling a satellite Method of sun and earth acquisition for three axis stabilized satellites equipped with acquisition sensors Digital PWPF three axis spacecraft attitude control Artificial satellite attitude control system Autonomous spacecraft controller and related method Precision platform pointing controller for a dual-spin spacecraft InventorAssigneeApplicationNo. 633141 filed on 04/16/1996US Classes:701/226, Space orbits or paths244/164, Attitude control244/167, By gravity gradient244/169, By jet motor244/171, With attitude sensor means342/352, Including a satellite342/354, With beam steering701/4, Altitude or attitude control or indication701/13, Spacecraft or satellite701/78Control of brake pressureExaminersPrimary: Louis-Jacques, Jacques H.Attorney, Agent or FirmInternational ClassesG06G 007/78B64G 001/24 AbstractA technique for maintaining a satellite in an assigned orbit without control or intervention from the ground. Autonomously obtained navigational data provide a measurement of the actual orbit in which the satellite is traveling. So long as the measured orbit conforms to a desired orbit to within a preselected tolerance, periodic corrections of equal magnitude are made to the satellite's velocity, based on a prediction of the effect of atmospheric drag on the orbit. Measurement of the orbit is made by observation of the time that the satellite passes a reference point in the orbit, such as by crossing the ascending node. If the measured orbit departs from the desired orbit by more than the preselected tolerance, a velocity correction of a magnitude different from the one based on prediction is applied to the satellite. For a decaying orbit, the magnitude of the velocity correction is increased above the correction value based on prediction. For a rising orbit, the magnitude of the velocity correction is decreased below the value based on prediction, and may be reduced to zero, allowing atmospheric drag to bring the measured orbit back within the preselected tolerance range.Field of SearchIncluding a satelliteWith beam steering With control of satellite altitude Having plural transmitters or receivers Synchronous satellite Attitude control By gyroscope or flywheel By jet motor By solar pressure With attitude sensor means By gravity gradient By nutation damper Fuel flow control Including pressurizing means With plural repeater or relay systems With synchronizing of satellites or system | |
