Geosynchronous spacecraft autonomous navigation
First Claim
1. A spacecraft system comprising:
- a measurement device configured to measure information associated with position of a spacecraft;
a filter configured to process the measured information and to provide estimated pre-maneuver information associated with position of the spacecraft and estimated post-maneuver information associated with position of the spacecraft;
a propagator configured to predict post-maneuver information associated with position of the spacecraft based upon the estimated pre-maneuver information associated with position of the spacecraft and a model of a maneuver of the spacecraft;
an error calculator configured to calculate an acceleration error using a state transition matrix, the acceleration error based upon the estimated post-maneuver information associated with position of the spacecraft and the predicted post-maneuver information associated with position of the spacecraft; and
a maneuver archive configured to store the acceleration error for updating the model of the maneuver,wherein the state transition matrix is identified by Φ
(ts,tm) and satisfies the following relationship;
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Accused Products
Abstract
A spacecraft system is provided, including a measurement device configured to measure information associated with position of a spacecraft, a filter configured to process the measured information and to provide estimated pre-maneuver information associated with position of the spacecraft and estimated post-maneuver information associated with position of the spacecraft, a propagator configured to predict post-maneuver information associated with position of the spacecraft based upon the estimated pre-maneuver information associated with position of the spacecraft and a model of a maneuver of the spacecraft, an error calculator configured to calculate an acceleration error based upon the estimated post-maneuver information associated with position of the spacecraft and the predicted post-maneuver information associated with position of the spacecraft, and a maneuver archive configured to store the acceleration error for updating the model of the maneuver. The filter, the propagator, the error calculator and the maneuver archive may be implemented in software and/or onboard the spacecraft.
32 Citations
24 Claims
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1. A spacecraft system comprising:
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a measurement device configured to measure information associated with position of a spacecraft; a filter configured to process the measured information and to provide estimated pre-maneuver information associated with position of the spacecraft and estimated post-maneuver information associated with position of the spacecraft; a propagator configured to predict post-maneuver information associated with position of the spacecraft based upon the estimated pre-maneuver information associated with position of the spacecraft and a model of a maneuver of the spacecraft; an error calculator configured to calculate an acceleration error using a state transition matrix, the acceleration error based upon the estimated post-maneuver information associated with position of the spacecraft and the predicted post-maneuver information associated with position of the spacecraft; and a maneuver archive configured to store the acceleration error for updating the model of the maneuver, wherein the state transition matrix is identified by Φ
(ts,tm) and satisfies the following relationship; - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. A system for calibrating spacecraft maneuvers comprising a processor configured to receive information associated with position of a spacecraft having one or more thrusters, to provide estimated pre-maneuver position-related information about the spacecraft and estimated post-maneuver position-related information about the spacecraft, to predict post-maneuver position-related information about the spacecraft based upon the estimated pre-maneuver position-related information about the spacecraft and a model of a maneuver of the spacecraft, the model of the maneuver of the spacecraft including performance information about the one or more thrusters, to calculate an acceleration error using a state transition matrix, and to update the model of the maneuver, wherein the acceleration error is based upon the estimated post-maneuver position-related information about the spacecraft and the predicted post-maneuver position-related information about the spacecraft,
wherein the state transition matrix is identified by Φ - (ts,tm) and satisfies the following relationship;
- View Dependent Claims (14)
- (ts,tm) and satisfies the following relationship;
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15. A method for calibrating spacecraft maneuvers, comprising the steps of:
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generating, with a filter, estimated pre-maneuver information associated with position of a spacecraft; predicting, with a propagator, post-maneuver information associated with position of the spacecraft based upon the estimated pre-maneuver information associated with position and a model of a maneuver; performing the maneuver; generating, with the filter, estimated post-maneuver information associated with position of the spacecraft; calculating an acceleration error using a state transition matrix, the acceleration error based upon a difference between the estimated post-maneuver information associated with position and the predicted post-maneuver information associated with position; and updating the model of the maneuver based upon the calculated acceleration error, wherein the state transition matrix is identified by Φ
(ts,tm) and satisfies the following relationship; - View Dependent Claims (16, 17, 18, 19, 20, 21, 22, 23, 24)
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Specification