Satellite orbit maintenance system

Claim 2

A control system for autonomously maintaining an earth-orbiting satellite in a desired orbit, the system comprising: means located on the satellite for sensing successive positions of the satellite in its orbit and determining from the successive positions the actual orbit of the satellite; orbit correction computation means, also located on the satellite, for periodically computing an orbital velocity correction to be applied to the satellite; and means for applying the computed orbital velocity correction to thrusters on the satellite, to effect an incremental orbital velocity correction; wherein the orbit correction computation means includes means for computing an orbit error, defined as the difference between a measured time of passing a reference point in the orbit and a desired time of passing the same reference point; and wherein the orbit velocity correction computed by the orbit correction computation means when the orbit error is within a predefined range, is equal to a predicted velocity correction needed to compensate for atmospheric drag in one complete revolution through the orbit; whereby orbital correction is effected even though each incremental velocity change may be insufficient to make a detectable change in the orbit.

Claim 3

The control system as defined in claim 1, wherein: for orbit error values outside the predefined range and in a direction indicative of a decaying orbit, the orbital velocity correction is calculated by multiplying the orbit error value by a gain factor.

Claim 4

The control system as defined in claim 1, wherein: for orbit error values outside the predefined range and in a direction indicative of a rising orbit, the orbital velocity correction is selected to be zero, permitting the orbit to decay under the effect of atmospheric drag, until the error value is again within the predefined range.

Claim 5

A computer implemented method for maintaining a satellite in a desired orbit, the method comprising the steps of: sensing successive positions of the satellite in its orbit using onboard sensing and navigation means; determining from the successive positions the actual orbit of the satellite; periodically computing, on the satellite, an orbital velocity correction to be applied to the satellite; and applying the computed orbital velocity correction to thrusters on the satellite, to effect an incremental orbital velocity correction; wherein the step of periodically computing includes computing an orbit error, defined as the difference between a measured time of passing a reference point in the orbit and a desired time for passing the same reference point; and wherein, when the orbit error is within a predefined range, the velocity correction computed in the step of periodically computing is equal to a predicted velocity correction needed to compensate for atmospheric drag in one complete revolution through the orbit; whereby orbital correction is effected even though each incremental velocity change may be insufficient to make a detectable change in the orbit.

Claim 6

A computer implemented method for maintaining a satellite in a desired orbit, the method comprising the steps of: sensing successive positions of the satellite in its orbit using onboard sensing and navigation means; determining from the successive positions the actual orbit of the satellite; periodically computing, on the satellite, an orbital velocity correction to be applied to the satellite; and applying the computed orbital velocity correction to thrusters on the satellite, to effect an incremental orbital velocity correction; wherein the step of periodically computing includes computing an orbit error, defined as the difference between a measured time of passing a reference point in the orbit and a desired time for passing the same reference point; and wherein, when the orbit error is within a predefined range, the velocity correction computed in the step of periodically computing is equal to a predicted velocity correction needed to compensate for atmospheric drag in one complete revolution through the orbit; whereby orbital correction is effected even though each incremental velocity change may be insufficient to make a detectable change in the orbit.

Claim 7

The computer implemented method as defined in claim 4, wherein: for orbit error values outside the predefined range and in a direction indicative of a decaying orbit, the orbital velocity correction is calculated by multiplying the orbit error value by a gain factor.

Claim 8

The computer implemented method as defined in claim 4, wherein: for orbit error values outside the predefined range and in a direction indicative of a rising orbit, the orbital velocity correction is selected to be zero, permitting the orbit to decay under the effect of atmospheric drag, until the error value is again within the predefined range.

Claim 9

The computer implemented method for maintaining a satellite in a desired orbit, the method comprising the steps of: sensing successive positions of the satellite in its orbit using onboard sensing and navigation means; determining from the successive positions the actual orbit of the satellite; periodically computing, on the satellite, an orbital velocity correction to be applied to the satallite; and applying the computed orbital velocity correction to thrusters on the satellite, to effect an incremental orbital velocity correction; wherein the step of determining the actual orbit of the satellite includes measuring the time at which the satellite passes a reference point in the orbit; and wherein the step of periodically computing an orbital velocity correction is performed once for each orbit, at a selected reference point such as the crossing of a node; and wherein the step of periodically computing includes determining whether an orbital error value defining the difference between the actual orbit and a desired orbit is within a predefined range; if the orbital error value is within the predefined range, selecting the orbital velocity correction to be equal to a predicted value based on effects of atmospheric drag on the satellite; if the orbital error value is outside the predefined range in a direction indicative of a decaying orbit, computing the orbital velocity correction to be greater than the predicted value used within the predefined range; and if the orbital error value is outside the predefined range in a direction indicative of a rising orbit, computing the orbital velocity correction to be less than the predicted value used within the predefined range.

Claim 10

The computer implemented method for maintaining a satellite in a desired orbit, the method comprising the steps of: sensing successive positions of the satellite in its orbit using onboard sensing and navigation means; determining from the successive positions the actual orbit of the satellite; periodically computing, on the satellite, an orbital velocity correction to be applied to the satallite; and applying the computed orbital velocity correction to thrusters on the satellite, to effect an incremental orbital velocity correction; wherein the step of determining the actual orbit of the satellite includes measuring the time at which the satellite passes a reference point in the orbit; and wherein the step of periodically computing an orbital velocity correction is performed once for each orbit, at a selected reference point such as the crossing of a node; and wherein the step of periodically computing includes determining whether an orbital error value defining the difference between the actual orbit and a desired orbit is within a predefined range; if the orbital error value is within the predefined range, selecting the orbital velocity correction to be equal to a predicted value based on effects of atmospheric drag on the satellite; if the orbital error value is outside the predefined range in a direction indicative of a decaying orbit, computing the orbital velocity correction to be greater than the predicted value used within the predefined range; and if the orbital error value is outside the predefined range in a direction indicative of a rising orbit, computing the orbital velocity correction to be less than the predicted value used within the predefined range.

Claim 11

The computer implemented method as defined in claim 7, wherein: the orbital velocity correction for an orbital error outside of the predefined range in a direction indicative of a decaying orbit, is computed by multiplying the orbital error value by a gain factor; and the orbital velocity correction for an orbital error outside of the predefined range in a direction indicative of a rising orbit, is selected to be zero, to permit atmospheric drag to gradually change the orbital error until it falls within the predefined range.

Claim 12

A control system for maintaining an earth-orbiting satellite in a desired orbit, the system comprising: means for sensing successive positions of the satellite in its orbit and determining from the successive positions the actual orbit of the satellite; orbit correction computation means, for periodically computing a velocity correction to be applied to the satellite; and means for applying the computed velocity correction to thrusters on the satellite, to effect an incremental velocity correction; wherein the orbit correction computation means includes means for computing an orbit error, defined as the difference between a measured time of passing a reference point in the orbit and a desired time of passing the same reference point; and wherein the velocity correction computed by the orbit correction computation means when the orbit error is within a predefined range, is equal to a predicted velocity correction needed to compensate for atmospheric drag in one complete revolution through the orbit; whereby orbital correction is effected even though each incremental velocity change may be insufficient to make a detectable change in the orbit.

Claim 13

A control system for maintaining an earth-orbiting satellite in a desired orbit, the system comprising: means for sensing successive positions of the satellite in its orbit and determining from the successive positions the actual orbit of the satellite; orbit correction computation means, for periodically computing a velocity correction to be applied to the satellite; and means for applying the computed velocity correction to thrusters on the satellite, to effect an incremental velocity correction; wherein the orbit correction computation means includes means for computing an orbit error, defined as the difference between a measured time of passing a reference point in the orbit and a desired time of passing the same reference point; and wherein the velocity correction computed by the orbit correction computation means when the orbit error is within a predefined range, is equal to a predicted velocity correction needed to compensate for atmospheric drag in one complete revolution through the orbit; whereby orbital correction is effected even though each incremental velocity change may be insufficient to make a detectable change in the orbit.

Claim 14

The control system as defined in claim 9, wherein: for orbit error values outside the predefined range and in a direction indicative of a decaying orbit, the velocity correction is calculated by multiplying the orbit error value by a gain factor.

Claim 15

The control system as defined in claim 10, wherein: for orbit error values outside the predefined range and in a direction indicative of a rising orbit, the velocity correction is selected to be zero, permitting the orbit to decay under the effect of atmospheric drag, until the error value is again within the predefined range.

Claim 16

The control system as defined in claim 9, wherein: the orbit correction computation means operates once per orbit; and the means for applying the computed velocity correction also operates once per orbit.

Claim 17

The control system as defined in claim 12, wherein: the orbit correction computation means operates each time the satellite passes through an ascending or descending node; the means for applying the computed velocity correction operates at each apogee of the orbit, to raise and circularize the orbit.

Claim 18

A computer implemented method for maintaining a satellite in a desired orbit, the method comprising the steps of: sensing successive positions of the satellite in its orbit using sensing and navigation means; determining from the successive positions the actual orbit of the satellite; periodically computing a velocity correction to be applied to the satellite; and applying the computed velocity correction to thrusters on the satellite, to effect an incremental velocity correction; wherein the step of periodically computing includes computing an orbit error, defined as the difference between a measured time of passing a reference point in the orbit and a desired time for passing the same reference point; and wherein, when the orbit error is within a predefined range, the velocity correction computed in the step of periodically computing is equal to a predicted velocity correction needed to compensate for atmospheric drag in one complete revolution through the orbit; whereby orbital correction is effected even though each incremental velocity change may be insufficient to make a detectable change in the orbit.

Claim 19

A computer implemented method for maintaining a satellite in a desired orbit, the method comprising the steps of: sensing successive positions of the satellite in its orbit using sensing and navigation means; determining from the successive positions the actual orbit of the satellite; periodically computing a velocity correction to be applied to the satellite; and applying the computed velocity correction to thrusters on the satellite, to effect an incremental velocity correction; wherein the step of periodically computing includes computing an orbit error, defined as the difference between a measured time of passing a reference point in the orbit and a desired time for passing the same reference point; and wherein, when the orbit error is within a predefined range, the velocity correction computed in the step of periodically computing is equal to a predicted velocity correction needed to compensate for atmospheric drag in one complete revolution through the orbit; whereby orbital correction is effected even though each incremental velocity change may be insufficient to make a detectable change in the orbit.

Claim 20

The computer implemented method as defined in claim 14, wherein: for orbit error values outside the predefined range and in a direction indicative of a decaying orbit, the velocity correction is calculated by multiplying the orbit error value by a gain factor.

Claim 21

The computer implemented method as defined in claim 15, wherein: for orbit error values outside the predefined range and in a direction indicative of a rising orbit, the velocity correction is selected to be zero, permitting the orbit to decay under the effect of atmospheric drag, until the error value is again within the predefined range.

Claim 22

The computer implemented method as defined in claim 14, wherein: the step of determining the actual orbit of the satellite includes measuring the time at which the satellite passes a reference point in the orbit; the step of periodically computing a velocity correction is performed once for each orbit, at a selected reference point such as the crossing of a node; the step of periodically computing includes determining whether an orbital error value defining the difference between the actual orbit and a desired orbit is within a predefined range; if the orbital error value is within the predefined range, selecting the velocity correction to be equal to a predicted value based on effects of atmospheric drag on the satellite; if the orbital error value is outside the predefined range in a direction indicative of a decaying orbit, computing the velocity correction to be greater than the predicted value used within the predefined range; and if the orbital error value is outside the predefined range in a direction indicative of a rising orbit, computing the velocity correction to be less that the predicted value used within the predefined range.

Claim 23

The computer implemented method as defined in claim 17, wherein: the velocity correction for an orbital error outside of the predefined range in a direction indicative of a decaying orbit, is computed by multiplying the orbital error value by a gain factor; and the velocity correction for an orbital error outside of the predefined range is a direction indicative of a rising orbit, is selected to be zero, to permit atmospheric drag to gradually change the orbital error until it falls within the predefined range.

Claim 24

The computer implemented method as defined in claim 14, wherein: the computing step is performed once and the step of applying the computed velocity correction is also performed once per orbit.

Claim 25

The computer implemented method as defined in claim 19, wherein: computing step is performed each time the satellite passes through an ascending or descending node; the step of applying the computed velocity correction operates at each apogee of the orbit, to raise and circularize the orbit.