Device and method for deorbiting of a satellite
AssigneeThales
InventorsDamien Forestier, Laurent Houis, Sebastien Herbiniere
Life of this patent
Estimating the term…
Abstract
The present disclosure relates to the deorbiting of satellites in low orbit that have entered safe hold mode. A device makes it possible to decide in an autonomous manner and on the basis of information existing in the satellite, when and where to trigger a series of short thruster manoeuvres to modify the satellite orbit with the aim of deorbiting.
Claims9
A device for deorbiting of a satellite in safe hold mode comprising:
- a data acquisition module capable of providing:
- the direction of the terrestrial magnetic field and the satellite-sun direction in the satellite reference frame;
- and
- a prediction of the direction of the terrestrial magnetic field and the satellite-sun direction in the local orbital reference frame;
- an attitude estimation module coupled to the data acquisition module for determining the attitude of the satellite in relation to the local orbital reference frame, the angle between the sun direction and the satellite Z-axis and the position on the orbit of the satellite;
- a boost generation module coupled to the attitude estimation module for generating signals capable of activating the thrusters of the satellite when the attitude, angle and position values are equal to predefined values.
A satellite comprising:
- a device for deorbiting of a satellite in safe hold mode, the device comprising:
- a data acquisition module capable of providing:
- the direction of the terrestrial magnetic field and the satellite-sun direction in the satellite reference frame;
- and
- a prediction of the direction of the terrestrial magnetic field and the satellite-sun direction in the local orbital reference frame;
- an attitude estimation module coupled to the data acquisition module for determining the attitude of the satellite in relation to the local orbital reference frame, the angle between the sun direction and the satellite Z-axis and the position on the orbit of the satellite;
- a boost generation module coupled to the attitude estimation module for generating signals capable of activating the thrusters of the satellite when the attitude, angle and position values are equal to predefined values.
A method for deorbiting a satellite in a safe hold mode comprising the steps of:
- acquiring, at a sensor of a satellite, data relating to:
- the direction of the terrestrial magnetic field and the satellite-sun direction in the satellite reference frame;
- and
- a prediction of the direction of the terrestrial magnetic field and the satellite-sun direction in the local orbital reference frame;
- determining, at an attitude estimator, the attitude of the satellite in relation to the local orbital reference frame, the angle between the sun direction and the satellite Z-axis and the position on the orbit of the satellite;
- comparing, using a computer, the determined attitude, angle and position values to predefined values;
- and
- generating signals, using a boost manager, capable of activating the thrusters of the satellite according to the result of the comparison for generating increments of satellite linear velocity, collinear with the satellite velocity vector.
A non-transitory computer readable medium including a computer program product, said computer program product comprising instructions in code to perform deorbiting a satellite in a safe hold mode, when said code is executed on a computer to implement:
- acquiring, at a sensor of a satellite, data relating to:
- the direction of the terrestrial magnetic field and the satellite-sun direction in the satellite reference frame;
- and
- a prediction of the direction of the terrestrial magnetic field and the satellite-sun direction in the local orbital reference frame;
- determining, at an attitude estimator, the attitude of the satellite in relation to the local orbital reference frame, the angle between the sun direction and the satellite Z-axis and the position on the orbit of the satellite;
- comparing, using the computer, the determined attitude, angle and position values to predefined values;
- and
- generating signals, using a boost manager, capable of activating the thrusters of the satellite according to the result of the comparison for generating increments of satellite linear velocity, collinear with the satellite velocity vector.
Dependencies are inferred from the claim text.