• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention relates to a method (50) for attitude control of a satellite in survival mode in inclined low orbit, the satellite comprising a solar generator, a magneto-coupler and a flywheel. Said method (50) comprises: a step (51), prior to the survival mode, of storing a constant non-zero internal magnetic moment setpoint in a satellite reference frame linked to the satellite, called "magnetic survival moment", and a set of non-zero internal kinetic moment constant in said satellite reference, said "kinetic moment of survival", - a step (52) for controlling the magneto-coupler and the flywheel so as to simultaneously form the magnetic moment of survival and kinetic moment of survival during at least part of the survival mode.
    公开号:FR3026858A1
    申请号:FR1459420
    申请日:2014-10-02
    公开日:2016-04-08
    发明作者:Dorian Lasnet；Emmanuel Giraud；Herve Camares
    申请人:Centre National dEtudes Spatiales CNES；Airbus Defence and Space SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention belongs to the field of attitude control of satellites in geocentric orbit, and more particularly relates to the attitude control of satellites in survival mode in inclined low orbit. STATE OF THE ART In the present application, "survival mode" is understood to mean any mode of attitude control of a satellite aiming, from a disturbed initial state, to ensure sunshine of the solar generators which is sufficient to guarantee the electrical autonomy of a platform of said satellite until it is restored to a state close to the nominal operational conditions. Thus, the survival mode can be implemented immediately after separation of the launcher and / or, after the mission of the satellite has started, in case of any incident requiring the interruption of the mission (collision with a meteorite, failure of a propellant, etc.).
    [0002] For a satellite in survival mode in low orbit, equipped with both magneto-couplers and flywheels, it is known from the patent application FR 2809502 A1 to control the attitude in a so-called "compass" mode. By a compass effect, a satellite will naturally orient itself so as to align an internal magnetic moment, formed by means of magnetocouplers, with the local terrestrial magnetic field. The angular position of the satellite around the internal magnetic moment can be controlled by means of an internal kinetic moment formed by the flywheels. In the compass mode, the internal magnetic moment to be formed is calculated from a terrestrial magnetic field model, a context information (notably the position of the satellite with respect to the Earth) and a set point of the satellite so as to ensure that, at each moment, the satellite pointing instruction is respected when the internal magnetic moment to be formed is aligned with the local terrestrial magnetic field. A disadvantage of compass mode lies in the use of many information (terrestrial magnetic field model, context information, pointing instruction), although it can not generally be guaranteed that all this information will be available in survival mode. This is the case in particular with the context information (if the associated sensor is faulty) and the pointing instruction (if it is obtained from a ground station and the associated communication has been interrupted). DISCLOSURE OF THE INVENTION The present invention aims to remedy all or part of the limitations of the solutions of the prior art, including those described above, by providing a survival mode attitude control that requires a limited number of sensors and actuators. In addition, the present invention also aims to propose a solution that is compatible with any type of inclined low orbit, particularly non-sun-synchronous orbits, called "drifting" orbits. For this purpose, and according to a first aspect, the present invention relates to a method of attitude control of a satellite in survival mode in inclined low orbit, the satellite comprising a solar generator, a magneto-coupler and a flywheel , characterized in that said method comprises: a step, prior to the survival mode, of storing a constant non-zero internal magnetic moment setpoint in a satellite reference frame linked to the satellite, called "magnetic survival moment", and a non-zero internal kinetic moment rate constant in said satellite reference, said "kinetic moment of survival", the magnetic moment of survival and the kinetic moment of survival being predefined so as to ensure that a photosensitive surface of the solar generator is at least sunny once during a satellite orbit, a step of controlling the magneto-coupler and the flywheel so as to simultaneously form the magnetic moment survival and survival kinetics during at least part of the survival mode. The attitude control method in survival mode is therefore particularly simple and robust, insofar as it implements only inertial actuators, in this case one or more magneto-couplers and one or more flywheels. In addition, these inertial actuators are used to respectively form a magnetic moment of survival and a kinetic moment of survival. The magnetic moment of survival and the kinetic moment of survival, both non-zero, are furthermore constant, so that they can be formed independently of any context information. The magnetic moment of survival makes it possible to fix, by compass effect, the attitude of the satellite along two axes with respect to the local terrestrial magnetic field. The angular position of said satellite around the magnetic moment of survival, that is to say the attitude of said satellite along the third axis, is imposed by the kinetic moment of survival. Indeed, the satellite will naturally move to have the kinetic moment of survival orthogonal to the plane of the satellite orbit.
    [0003] By applying the attitude control method in survival mode according to the invention, the attitude of the satellite varies in inertial reference, but is nevertheless controlled along three axes with respect to the local terrestrial magnetic field. It is therefore possible to choose, depending on the orbit of the satellite and the geometry of said satellite (in particular, the arrangement of the solar generator in the satellite reference), a magnetic moment of survival and a kinetic moment of survival that allow ensure that the photosensitive surface of the solar generator is sunny at least once per satellite orbit. Preferably, the magnetic moment of survival and the kinetic moment of survival are predetermined so as to maximize the average sunlight of said photosensitive surface during a satellite orbit. In particular modes of implementation, the survival mode attitude control method may further comprise one or more of the following characteristics, taken separately or in any technically possible combination.
    [0004] In particular modes of implementation, the satellite comprising several magnetocouplers and a device for measuring the local terrestrial magnetic field, said method comprises steps of: - determination, as a function of measurements of the local terrestrial magnetic field, of a internal magnetic moment, called "damping magnetic moment", to be formed to apply a magnetic torque on said satellite which opposes the variations of the local terrestrial magnetic field in the satellite reference, - control of the magneto-couplers so as to add the magnetic moment of damping at the magnetic moment of survival. Indeed, in survival mode (after separation of the launcher and / or after incident occurred during the mission), the satellite can initially be in uncontrolled rotation with a high rotation speed. In such a case, the superposition of a damping magnetic moment (variable over time) at the magnetic moment of survival (constant over time) makes it possible to reduce the speed of rotation of said satellite. The magnetic moment actually formed is then a magnetic moment modulated around the magnetic moment of survival. In particular embodiments, the solar generator being arranged along an axis X of the satellite reference, the magnetic survival moment is parallel to the X axis and the kinetic moment of survival is orthogonal to said X axis. particular modes of implementation, the solar generator 15 being substantially flat, the kinetic moment of survival forms, with the plane of the solar generator, an angle of non-zero value modulo 90 °, preferably between 100 and 80 ° modulo 90 ° . In particular embodiments, the upward node of said orbit being close to midday or midnight and the solar generator being arranged along an axis X of the satellite reference, the magnetic moment of survival is orthogonal to the axis X and the kinetic moment of survival is parallel to axis X. In particular modes of implementation, the ascending node of said orbit being close to midday or midnight, the magnetic moment of survival and the kinetic moment of survival are such that the surface photosensitive 25 of the solar generator is sunny at least twice during a satellite orbit. In particular modes of implementation, the orbit of the satellite is substantially polar. According to a second aspect, the present invention relates to a computer program product comprising a set of program code instructions which, when executed by a processor, implement an attitude control method according to the present invention. any of the embodiments of the invention.
    [0005] According to a third aspect, the present invention relates to a low inclined orbit satellite comprising a solar generator, a magneto-coupler, a flywheel and a control module of the magneto-coupler and the flywheel. According to the invention, the control module comprises a memory in which are memorized a constant non-zero internal magnetic moment setpoint in a satellite reference frame linked to the satellite, called "magnetic survival moment", and a non-zero internal kinetic momentum instruction. constant in said satellite reference, said "kinetic moment of survival". In addition, the control module is configured to control, when the satellite is in survival mode, the magneto-coupler and the flywheel so as to simultaneously form the magnetic moment of survival and the kinetic moment of survival during a part of the less of the survival mode. In particular embodiments, the satellite may further comprise one or more of the following characteristics, taken separately or in any technically possible combination. In preferred embodiments, the satellite comprises a plurality of magneto-couplers and a device for measuring the local terrestrial magnetic field, and in that the control module is configured for, when the satellite is in survival mode: measurement of the local terrestrial magnetic field, an internal magnetic moment, called "damping magnetic moment", to be formed to apply a magnetic torque on said satellite adapted to oppose the variations of the local terrestrial magnetic field in the satellite reference, - control the magneto-couplers so as to add the magnetic damping moment to the magnetic moment of survival. In preferred embodiments, the solar generator being arranged along an axis X of the satellite reference, the magnetic survival moment is parallel to the X axis and the kinetic moment of survival is orthogonal to the X axis.
    [0006] In preferred embodiments, the solar generator being substantially flat, the kinetic moment of survival forms, with said plane of said solar generator, an angle of non-zero value modulo 90 °, preferably between 100 and 80 ° modulo 90 °.
    [0007] According to a fourth aspect, the present invention relates to a method for remote control of a satellite whose attitude in survival mode is controlled according to any of the embodiments of the invention. According to the invention, the orbit of the satellite being a drift, the method comprises, when the satellite is not in survival mode, a recurrent step of updating the instructions of magnetic moment of survival and kinetic moment of survival stored in the memory of the control module. Indeed, the satellite being in drifting orbit, it may be impossible to have instructions for magnetic moment of survival and survival kinetic moment that ensure sufficient sunlight sufficient photosensitive surface of the solar generator for all the possible orbits of said satellite. Thus, the instructions for magnetic moment of survival and kinetic moment of survival are updated recurrently, when the satellite is not in survival mode, in order to better adapt them to the subsequent orbits of the satellite, if this one had to go into survival mode. These instructions are not updated during the survival mode. The instructions for magnetic moment of survival and kinetic moment of survival are constant throughout the duration of said survival mode. In particular embodiments, the remote control method may further include one or more of the following features, taken alone or in any technically possible combination. In particular embodiments, the update step is performed at each six-hour change in the solar time of the ascending node of the satellite orbit. In particular embodiments, the solar generator being substantially flat and the kinetic moment of survival forming, with said plane of said solar generator, an angle of non-zero value modulo 90 °, preferably between 100 and 80 ° modulo 90 Each update consists of a polarity reversal of the magnetic moment of survival and / or a polarity inversion of the kinetic moment of survival. In particular modes of implementation, the updating step consists in: - reversing only the polarity of the magnetic moment of survival when the ascending node of the satellite orbit is at six o'clock or at eighteen hours, - to reverse both the polarity of the magnetic moment of survival and the polarity of the kinetic moment of survival when the ascending node of the satellite orbit is at midnight or at noon. PRESENTATION OF THE FIGURES The invention will be better understood on reading the following description, given by way of non-limiting example, and with reference to the figures which represent: FIG. 1: a schematic representation of an embodiment of FIG. FIG. 2: a schematic representation of a preferred embodiment of the satellite of FIG. 1; FIG. 3: a diagram representing a preferred embodiment of an attitude control method of FIG. a satellite in survival mode and a remote control method of said satellite, - Figure 4: a schematic representation of a first example of implementation of a survival mode attitude control method, - Figure 5: a schematic representation of a second example of implementation of a method of attitude control in survival mode. In these figures, identical references from one figure to another designate identical or similar elements. For the sake of clarity, the elements shown are not to scale unless otherwise stated. DETAILED DESCRIPTION OF EMBODIMENTS The present invention relates to the attitude control of a satellite 10 in survival mode in low inclined geocentric orbit. As indicated previously, in the present application, the survival mode is an attitude control mode implemented immediately after separation of the launcher and / or, after the mission of the satellite 10 has started, in the event of any incident requiring to interrupt the mission (collision with a meteorite, failure of a thruster, etc.).
    [0008] By "low orbit" is meant that the maximum altitude of the satellite 10 is such that the local magnetic field is not negligible and allows the implementation of inertial actuators type magneto-couplers to control the attitude of said satellite. In practice, this condition is verified when the maximum altitude of the satellite 10 is less than 2000 kilometers. FIG. 1 schematically represents an exemplary embodiment of a satellite 10 according to the invention. As illustrated by FIG. 1, the satellite 10 comprises a body 11 and two solar generators 12 arranged on either side of said body 11.
    [0009] Each solar generator 12 comprises, on one side, a photosensitive surface 13 which must be oriented towards the Sun S to generate electrical power. In the remainder of the description, it is not limited to the case where the solar generators 12 are of fixed orientation and not modifiable relative to the body 11 of the satellite 10. The present invention is however also applicable to the case of generators 12 in the case where the solar generators 12 are mobile, their orientation can be changed during the survival mode, for example to optimize the sunshine of the photosensitive surfaces 13, or said solar generators 12 can be deliberately maintained in a predetermined fixed orientation for the duration of the survival mode. The satellite 10 is associated with a satellite reference, for example centered on a center of mass 0 of the satellite 10, comprising three axes X, Y and Z orthogonal to each other. The satellite reference is linked to the satellite 10, that is to say that it is entirely defined by the geometry of the satellite 10. In other words, any rotation of the satellite 10 in an inertial frame results in an equivalent rotation of the satellite. satellite reference in inertial reference. In the exemplary embodiment illustrated in FIG. 1, the body 11 of the satellite 10 is substantially in the form of a rectangular parallelepiped, and the axes X, Y and Z are orthogonal to respective orthogonal faces of said body 11. More particularly: the X axis is orthogonal to + X and -X faces of the body 11 carrying the solar generators 12, and so that said solar generators 12 are arranged along the X axis, that is to say parallel to said X axis, the Z axis is orthogonal to + Z and -Z faces of the body 11, whose + Z face carries an instrument 14 of a payload of the satellite 10 and must be directed towards the Earth T for perform its mission, the Y axis is orthogonal to the faces Y and Y of the body 11. For the purposes of the description, each of the X, Y and Z axes of the satellite coordinate system is also associated with unit vectors respectively. ux, uy and uz. The unit vectors ux, uy and uz are oriented from the center of mass 0 to the faces respectively + X, + Y and + Z, and the set (ux, uy, uz) constitutes a direct orthonormal basis of the satellite reference. The satellite 10 also comprises several inertial actuators used for the attitude control. More particularly, the satellite 10 comprises a set of magneto-couplers 15 adapted to form an internal magnetic moment of any axis in the satellite reference. The satellite 10 also comprises a set of flywheels 16, such as reaction wheels or gyroscopic actuators, adapted to form an internal kinetic moment of any axis in said satellite reference.
    [0010] The satellite 10 also comprises a control module (not shown in the figures) adapted to control the magneto-couplers 15 and the flywheels 16. The control module comprises, for example, at least one processor and at least one memory in which is stored a computer program product, in the form of a set of program code instructions to be executed to implement the different steps of a method of monitoring the attitude of the satellite 10 in survival mode. In a variant, the control module comprises one or more programmable logic circuits, of the FPGA, PLD, etc. type, and / or specialized integrated circuits (ASIC) adapted to implement all or part of the said steps of the control method 50. the attitude of said satellite 10 in survival mode. In other words, the control module comprises a set of means configured in software (specific computer program product) and / or hardware (FPGA, PLD, ASIC, etc.) to implement the control method 50 of satellite attitude 10 in survival mode. FIG. 2 schematically represents a preferred embodiment of the satellite 10 illustrated in FIG.
    [0011] In the example illustrated in FIG. 1, the solar generators 12 are substantially planar and are substantially parallel to the XY plane formed by the X and Y axes of the satellite reference mark, the photosensitive surfaces 13 being arranged on the side of the face -Z of the body 11 of the satellite 10. In the example illustrated in FIG. 2, the solar generators 12, also substantially planar, are arranged obliquely with respect to the plane XY and with respect to the plane XZ formed by the axes X and Z of the satellite reference . Preferably, the plane of each solar generator 12 forms with the XY plane an angle of non-zero value modulo 90 °, the photosensitive surfaces 13 being arranged on the side of the face -Z of the body 11 of the satellite 10. For example, the angle between the plane of each solar generator 12 and the XY plane is of between 100 and 80 ° modulo 90 °, or even between 20 ° and 70 ° modulo 90 °. In the example illustrated in FIG. 2, the angle between the plane of each solar generator 12 and the XY plane is equal to 45 °. It should be noted that, in the case of solar generators 12 mounted mobile in rotation about the X axis, the configuration of FIG. 2 is obtained by a simple rotation of the solar generators 12 with respect to the configuration of FIG. FIG. 3 diagrammatically represents the main steps of a method 50 for controlling the attitude of the satellite 10 in the survival mode according to the invention, which are: a step 51, prior to the survival mode, of storing in a memory of the module of controlling a constant internal magnetic moment setpoint in the satellite reference, said "magnetic survival moment", and a constant internal kinetic momentum setpoint in said satellite reference, said "kinetic moment of survival", a step 52 of controlling the magneto-couplers 15 and flywheels 16 so as to simultaneously form the magnetic survival moment and the kinetic moment of survival during at least part of the survival mode . Thus, the magneto-couplers 15 and the flywheels 16 are mainly used, when the satellite 10 is in survival mode, to respectively form the survival magnetic moment and the kinetic moment of survival, which are both constant in the satellite reference. The magnetic moment of survival and the kinetic moment of survival are formed simultaneously during several orbital periods, and preferably throughout the duration of the survival mode.
    [0012] The magnetic moment of survival makes it possible to fix, by compass effect, the attitude of the satellite 10 along two axes with respect to the local terrestrial magnetic field. The angular position of said satellite 10 around the magnetic moment of survival is imposed by the kinetic moment of survival. It is therefore possible to predetermine, depending on the characteristics of the orbit of the satellite 10 and the arrangement of the solar generators 12 in the satellite reference, a magnetic moment of survival and a kinetic moment of survival which make it possible to optimize the average sunning of the photosensitive surfaces 13 of the solar generators 12. In particular embodiments, the satellite 10 may comprise a three-axis measurement device of the local terrestrial magnetic field. The measuring device (not shown in the figures) comprises, for example, three magnetometers adapted to measure the components of the local terrestrial magnetic field along the axes X, Y and Z, respectively. Where appropriate, and as illustrated by FIG. the method 50 of attitude control in survival mode may comprise recurrent steps of: - 53 determination, as a function of measurements of the local terrestrial magnetic field, of an internal magnetic moment, called "damping magnetic moment", to be formed for applying a magnetic torque to said satellite 10 which opposes the variations of the local terrestrial magnetic field in the satellite reference, controlling the magneto-couplers 15 so as to superpose the magnetic damping moment at the magnetic moment of survival.
    [0013] Indeed, in survival mode (after separation of the launcher and / or after incident occurred during the mission), the satellite 10 may initially be in uncontrolled rotation with a high rotational speed. If necessary, it is quite conventional to form damping torques to reduce the speed of rotation of the satellite 10. The damping torques can be formed by means of the magneto-couplers 15, in which case the magnetic moment of damping is added to the magnetic moment of survival. Nothing, however, excludes the formation of damping torques by means of other inertial actuators of the satellite 10 and / or by means of thrusters of said satellite 10. The determination of a suitable damping magnetic moment is considered to be at the scope of the art, and can for example implement a command "B-point". FIG. 4 schematically represents an exemplary implementation of the attitude control method 50 of the satellite of FIG. 1 in survival mode. In the example illustrated in FIG. 4, said satellite 10 is in polar orbit and the ascending point of the orbit is at midday or midnight (in other words, the Sun S is in the plane of the orbit satellite 10). By controlling the magneto-couplers 15 so as to form the magnetic moment of survival, which is non-zero, the satellite 10 follows the lines of force of the Earth's magnetic field, causing the rotation of said satellite 10 on itself twice the orbital pulse wo. In the exemplary embodiment illustrated in FIG. 4, the magnetic survival moment is parallel to the X axis of the satellite reference, and the kinetic moment of survival is parallel to the Y axis. In this way, the X axis of the satellite marker, which are arranged solar generators 12, is in the plane of the orbit of the satellite 10. In addition, the plane of the solar generators 12 (which is parallel to the XY plane) is substantially orthogonal to the radii of the Sun S when the satellite 10 passes the equator E and overflies the North N and South S poles of the Earth T. Therefore, according to the direction of the magnetic moment of survival and the direction of the kinetic moment of survival, the photosensitive surfaces 13 solar generators 12 will be directed towards the Sun: - either when the satellite 10 passes the equator E (configuration of part a) of FIG. 4), - or when the satellite 10 flies over the north and south poles S (configuration part (b) of Figure 4). In particular, by designating by Ms the magnetic moment of survival (of module IMs1 nonzero) and by Hs the kinetic moment of survival (of module IHs1 nonzero), and considering that the ascending node is at noon, then the configuration of part a) is obtained in the following cases: - Ms = IMsl. ux and Hs = -IHsl. uy; or - Ms = -IMsrux and Hs = IHsruy. Considering that the ascending node is at noon, the configuration of part b) is obtained in the following cases: - Ms = IMsrux and Hs = IHsruy; or - Ms = -IMsl.ux and Hs = -IHsl. uy. It is therefore possible to force the satellite 10 to be placed in one or the other of the configurations of parts a) and b) of FIG. 4, by choosing a suitable direction of the magnetic survival moment Ms along the X axis and a suitable sense of the kinetic moment of survival Hs along the Y axis. It is further noted that for a given kinetic moment of survival Hs, the configuration of part b) can be obtained from the configuration of the part a), by a simple inversion of the polarity of the magnetic moment of survival Ms to constant module IMs1. Preferably, the magnetic survival moment Ms and the kinetic moment of survival Hs are predetermined so as to place the satellite 10 in the configuration of part b). Indeed, the photosensitive surfaces 13 of the solar generators 12 are then sunny twice in orbit of the satellite 10, and the electrical power generated is 1.5 to 2 times greater than that generated in the configuration of part a). The areas of the photosensitive surfaces 13 are dimensioned to ensure that the electrical power thus generated is sufficient to guarantee the electrical autonomy of a platform of the satellite 10 during the survival mode.
    [0014] It should be noted that similar results, in terms of performance, can be obtained in the case illustrated in FIG. 4 (satellite 10 of FIG. 1 and polar orbit with an ascending node at midday or at midnight) by choosing a magnetic moment of Ms survival parallel to the Y axis and kinetic moment of survival Hs parallel to the X axis. In addition, the magnetic moment of survival Ms and the kinetic moment of survival Hs used in the example illustrated by FIG. be used for the satellite 10 of Figure 2 in polar orbit with an ascending node at noon or midnight. In such a case, the kinetic moment of survival Hs forms, with the plane of each solar generator 12, an angle equal to 45 ° modulo 90 °. In addition, all that has been described with reference to FIG. 4 considering that the ascending node is at midday or at midnight remains valid, especially when the ascending node is close to midday or midnight, that is, to more or less two hours (± 2 hours) around noon or midnight. FIG. 5 schematically represents an exemplary implementation of the attitude control method 50 of the satellite of FIG. 1 in survival mode. In the example illustrated in FIG. 5, said satellite 10 is in polar orbit and the ascending point of the orbit is at six o'clock or at eighteen o'clock.
    [0015] In the exemplary implementation illustrated in FIG. 5, the magnetic survival moment Ms is parallel to the axis X of the satellite reference, and the kinetic moment of survival Hs is parallel to the axis Z. As illustrated in FIG. 5, the direction of the kinetic moment of survival Ms and the direction of the kinetic moment of survival can be chosen so as to ensure that the photosensitive surfaces 13 of the solar generators 12 will be sunny throughout the duration of the orbit. For the satellite 10 of FIG. 2, it is possible, in the case of a polar orbit with an ascending node at six o'clock or at six o'clock, to preserve a magnetic survival moment Ms along the X axis and a Kinetic moment of survival Hs along the Y axis (as in the case illustrated in Figure 4). Optionally, the polarity of the magnetic survival moment Ms (that is, the direction of the magnetic survival moment Ms along the X axis) and / or the kinetics of the kinetic moment of survival Hs (that is, the say the direction of the kinetic moment of survival Hs along the Y axis) can be modified, with IMs1 and constant IHs1 modules, to ensure that the photosensitive surfaces 13 of the solar generators 12 will be sunny throughout the duration of the orbit. It is therefore understood that it is always possible, for a given orbit, to predetermine a magnetic moment of survival Ms and kinetic moment of survival Hs, constant in satellite reference, to form simultaneously during all or part of the survival mode, which make it possible to optimize the average sunshine of the photosensitive surfaces 13 of the solar generators 12 for the considered orbit. The instructions for magnetic survival moment Ms and survival kinetic moment Hs can therefore be stored in a memory of the control module before the satellite 10 switches to survival mode. Then, when the satellite 10 goes into survival mode, the control module will simply recover and apply said setpoints stored in the memory.
    [0016] For example, for a satellite 10 in orbit at an altitude of 800 km, with an inertia of between 3000 and 7000 kg-m2, a magnetic survival moment Ms of IMs1 module of the order of 150 A-m2 will make it possible to form a sufficient return torque to compensate for most disturbing torques (essentially the effect of the gravity gradient). A kinetic moment of survival Hs of IHs1 module of the order of 15 N-m-s will generally be sufficient to block the angular position of the satellite 10 around the local terrestrial magnetic field. In the case of a drifting orbit, the characteristics of the orbit will evolve over time. In particular, the solar time of the ascending point of the orbit will evolve over time, so that it may be impossible to have instructions for magnetic moment of survival Ms and kinetic moment of survival Hs which provide sufficient sunlight sufficient photosensitive surfaces of solar generators 12 for all possible orbits of said satellite 10.
    [0017] For this purpose, the invention also relates to a method 60 for remote control of the satellite 10 by a ground station (not shown in the figures), shown in FIG. 3. As illustrated in FIG. 3, the method 60 of FIG. remote control comprises, when the satellite 10 is not in survival mode, a recurrent updating step 61 during which the station sends commands to the satellite 10. These commands are intended to update the instructions of magnetic moment of survival Ms and kinetic survival moment Hs stored in the memory of the control module. At the level of the satellite 10, the control module stores, during the step 51 of storage, the instructions updated according to commands received from the ground station. Typically, the update step 61 is executed with each six-hour variation of the solar time of the ascending node of the satellite orbit 10. Nothing, however, precludes performing step 61 of updating for different variations of the solar time of the ascending node of the satellite orbit 10, less than or greater than six hours. The updates of the instructions for magnetic moment of survival Ms and kinetic moment of survival Hs aim to make them better adapted to the future orbits of satellite 10, in the event that said satellite 10 would go into survival mode. For this purpose, it is possible, during the updating step 61, to modify the respective axes of the magnetic survival moment Ms and the kinetic moment of survival Hs and / or their directions along their respective axes.
    [0018] The modules IMs1 and IHs1 are preferably kept constant, but nothing excludes updating them as well. In the case of the satellite 10 of FIG. 2, it has been previously seen that it is possible to preserve a magnetic survival moment Ms along the X axis and a kinetic moment of survival Hs along the Y axis for the main possible orbits. (ascending knot at midnight, six o'clock, noon and eighteen o'clock). As a result, each update is particularly simple and can consist of a polarity inversion of the magnetic survival moment Ms and / or a reversal of the kinetics of the kinetic moment of survival Hs, while ensuring that the photosensitive surfaces 13 of the solar generators 12 are sunny at least once regardless of the orbit of the satellite 10. More generally, it is also possible in the case of the satellite 10 of FIG. 1, considering a kinetic moment of survival Hs forming, with the plane each solar generator 12, an angle of non-zero value modulo 90 °, for example between 10 ° and 80 ° modulo 90 °.
    [0019] In such a case, the updating step 61 consists, for example, in: reversing only the polarity of the magnetic survival moment Ms when the ascending node of the satellite orbit 10 is at six o'clock or at eighteen o'clock, inverting both the polarity of the magnetic survival moment Ms and the kinetics of the kinetic moment of survival Hs when the ascending node of the satellite orbit 10 is at midnight or at noon. More generally, it should be noted that the modes of implementation and realization considered above have been described by way of non-limiting examples, and that other variants are therefore possible. In particular, the invention has been described by considering a satellite 10 having several magnetocouplers 15 and several flywheels 16. To form the magnetic moment of survival and the kinetic moment of survival, which are constant in the satellite reference, it However, it may be envisaged to equip the satellite 10 with a single magneto-coupler 15 and a single flywheel 16. Where appropriate, the magneto-coupler 15 and the flywheel 16 must be arranged in the satellite 10 in the expected directions of the magnetic moment of survival and the kinetic moment of survival. However, several magneto-couplers will be necessary if these must be implemented to form a damping magnetic moment, and several flywheels will be necessary if they must be implemented to stabilize the attitude of the satellite 10 along three axes outside the survival mode. Also, the invention has been described mainly considering a satellite 10 in polar orbit. The invention is however applicable to any type of inclined low orbit. Nothing in particular excludes considering a substantially polar orbit, that is to say an orbit whose inclination is between 70 ° and 110 °. In addition, the invention finds a particularly advantageous application in the case of circular orbits, but is also applicable to non-circular orbits (for example in the case of deorbitation). In addition, the invention has been described considering a satellite 10 having two solar generators 12. However, it is understood that the invention is generalizable to any number of solar generators 12, equal to or greater than one.
    权利要求:
    Claims (3)
    [0001]
    CLAIMS 1 - A method (50) for attitude control of a satellite (10) in survival mode in inclined low orbit, the satellite (10) comprising a solar generator (12), a magneto-coupler (15) and a steering wheel inertia (16), characterized in that said method (50) comprises: a step (51), prior to the survival mode, of storing a constant non-zero internal magnetic moment setpoint in a satellite reference linked to the satellite ( 10), called the "magnetic moment of survival", and of a constant non-zero internal kinetic momentum setpoint in said satellite reference, said "kinetic moment of survival", the magnetic moment of survival and the kinetic moment of survival being predefined of so as to ensure that a photosensitive surface (13) of the solar generator (12) is sunny at least once during a satellite orbit (10), - a step (52) of controlling the magneto-coupler (15) and the flywheel (16) so as to simultaneously form the magnetic moment of survival and the kinetic moment of survival during at least part of the survival mode.
    [0002]
    2 - Method (50) according to claim 1, characterized in that, the satellite (10) comprising a plurality of magneto-couplers (15) and a device for measuring the local terrestrial magnetic field, said method comprises steps of: - (53 ) determining, according to measurements of the local terrestrial magnetic field, an internal magnetic moment, called "damping magnetic moment", to be formed for applying a magnetic torque on said satellite (10) which opposes the variations of the field local magnetic field in the satellite coordinate system; - (52) controls the magneto-couplers (15) so as to superimpose the magnetic damping moment at the magnetic moment of survival.
    [0003]
    3 - Process (50) according to one of the preceding claims, characterized in that, the solar generator (12) being arranged along an axis X of the satellite reference, the magnetic moment of survival is parallel to the axis X and le4 - The kinetic moment of survival is orthogonal to said X-axis. A method (50) according to claim 3, characterized in that, the solar generator (12) being substantially plane, the kinetic moment of survival forms, with said plane of said solar generator, an angle of non-zero value modulo 900. Method (50) according to one of claims 1 to 2, characterized in that, the upward node of said orbit being close to midday or midnight and the solar generator (12) being arranged along an axis X of the satellite reference, the magnetic moment of survival is orthogonal to the X axis and the kinetic moment of survival is parallel to said X axis. Method (50) according to one of the preceding claims, characterized in that, the ascending node of said orbit being close to midday. or at midnight, the magnetic moment of survival and the kinetic moment of survival are predetermined so as to ensure that the photosensitive surface (13) of the solar generator (12) is sunny at least twice during a satellite orbit (10). ). Method (50) according to one of the preceding claims, characterized in that the orbit of the satellite (10) is substantially polar. Computer program product characterized in that it comprises a set of program code instructions which, when executed by a processor, implement an attitude control method (50) according to one of the preceding claims. Satellite (10) inclined low orbit having a solar generator (12), a magneto-coupler (15), a flywheel (16) and a control module of the magneto-coupler (15) and the flywheel (16), characterized in that the control module comprises a memory in which are memorized a constant non-zero internal magnetic moment setpoint in a satellite reference linked to the satellite (10), called "magnetic survival moment", and a set point of non-zero internal kinetic moment constant in said satellite reference, said "kinetic moment of survival", and in that the control module is configured to control, when the satellite (10) is in survival mode, the magneto-coupler (15 ) and the flywheel (16) so as to simultaneously form the survival magnetic element and the kinetic moment of survival during at least part of the survival mode. 10- Satellite (10) according to claim 9, characterized in that it comprises a plurality of magneto-couplers (15) and a device for measuring the local terrestrial magnetic field, and in that the control module is configured for, when the satellite (10) is in survival mode: - determining, according to measurements of the local terrestrial magnetic field, an internal magnetic moment, called "damping magnetic moment", to be formed to apply a magnetic torque on said adapted satellite (10) to oppose the variations of the local terrestrial magnetic field in the satellite reference, - to control the magneto-couplers (15) so as to superpose the magnetic damping moment at the magnetic moment of survival. 11 - Satellite (10) according to one of claims 9 to 10, characterized in that the solar generator (12) being arranged along an axis X of the satellite reference, the magnetic moment of survival is parallel to the axis X and the kinetic moment of survival is orthogonal to said X-axis. 12 - Satellite (10) according to claim 11, characterized in that, the solar generator (12) being substantially plane, the kinetic moment of survival forms, with said plane of said solar generator, an angle of non-zero value modulo 90 °. 13- Method (60) for remote control of a satellite (10) according to one of claims 9 to 12, characterized in that, the orbit of said satellite being a drift, said method comprises, when the satellite (10) is not in survival mode, a recurring step (61) for updating the survival magnetic moment and survival kinetic moment setpoints stored in the memory of the control module. 14- Method (60) according to claim 13, characterized in that the updating step (61) is performed at each six-hour variation of the solar time of the ascending node of the satellite orbit (10) . 15- Method (60) according to one of claims 13 to 14, characterized in that, the solar generator (12) is substantially planar and the survival kinetics forming, with said plane of said solar generator, a non-zero value angle modulo 90 °, each update consists of a polarity reversal of the magnetic moment of survival and / or a polarity reversal of the kinetic moment of survival. 16- Method (60) according to claim 15, characterized in that the updating step (61) consists in: - reversing only the polarity of the magnetic moment of survival when the ascending node of the satellite orbit (10) ) is at six o'clock or eighteen o'clock, - reverse both the polarity of the magnetic moment of survival and the polarity of the kinetic moment of survival when the ascending node of the satellite orbit (10) is at midnight or at midday.
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    同族专利:
    公开号 | 公开日
    EP3201091A1|2017-08-09|
    WO2016051113A1|2016-04-07|
    EP3201091B1|2019-06-12|
    FR3026858B1|2016-12-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2659061A1|1990-03-05|1991-09-06|Gen Electric|Method for stabilising a satellite|
    CA2057720A1|1990-12-21|1992-06-22|Issam-Maurice Achkar|Attitude control system for stabilized three-axis satellite on low inclination orbit|
    FR2742243A1|1995-12-06|1997-06-13|Matra Marconi Space France|METHOD FOR CONTROLLING THE ATTITUDE OF A SATELLITE IN LOW ORBIT WITH SOLAR ACQUISITION|
    FR2809502A1|2000-05-29|2001-11-30|Matra Marconi Space France|Orientation control method for a low-orbit satellite using a triaxial arrangement of magneto-couplers together with a triaxial magnetometer for ensuring the satellite is correctly aligned using the Earth's magnetic field|
    EP2181923A1|2008-10-31|2010-05-05|Thales|Method and system for unloading the inertia wheels in a spacecraft|
    WO2013041575A1|2011-09-19|2013-03-28|Astrium Sas|Method of controlling the attitude of a satellite and an attitude-controlled satellite|
    FR2994287A1|2012-08-03|2014-02-07|Thales Sa|DEVICE AND METHOD FOR SATELLITE DESORBITATION|CN110389592A|2019-07-18|2019-10-29|南京航空航天大学|A kind of Spacecraft Attitude Control method based on distributed intelligence flywheel|
    CN106828981B|2017-03-13|2020-01-03|上海航天控制技术研究所|Constant interference moment compensation method and system for oblique flying large-inertia coupling satellite|
    CN108045600A|2017-10-23|2018-05-18|上海卫星工程研究所|Double super satellite platform load cabin composite control methods|
    CN109649691B|2018-12-27|2021-07-13|上海航天控制技术研究所|Single flywheel and magnetic combined control method and system for offset momentum satellite|
    CN109649693B|2019-01-21|2021-12-14|上海微小卫星工程中心|Pure magnetic control spinning sun-facing orientation method|
    FR3093326A1|2019-03-01|2020-09-04|Centre National d'Études Spatiales|Method of controlling the attitude of a satellite in low orbit|
    FR3093998B1|2019-03-20|2021-09-10|Airbus Defence & Space Sas|Method for controlling the attitude of a satellite in survival mode without a priori knowledge of the local time of the orbit of the satellite|
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1459420A|FR3026858B1|2014-10-02|2014-10-02|METHOD FOR CONTROLLING ATTITUDE OF SATELLITE IN SURVIVAL MODE, ADAPTED SATELLITE AND METHOD FOR REMOTELY CONTROLLING SATELLITE OF SATELLITE|FR1459420A| FR3026858B1|2014-10-02|2014-10-02|METHOD FOR CONTROLLING ATTITUDE OF SATELLITE IN SURVIVAL MODE, ADAPTED SATELLITE AND METHOD FOR REMOTELY CONTROLLING SATELLITE OF SATELLITE|
    PCT/FR2015/052654| WO2016051113A1|2014-10-02|2015-10-02|Method of supervising attitude of a satellite in survival mode, adapted satellite and method of remotely controlling such a satellite|
    EP15787001.5A| EP3201091B1|2014-10-02|2015-10-02|Method of supervising attitude of a satellite in survival mode, adapted satellite and method of remotely controlling such a satellite|
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