CA2255127A1 - Method for determining the orbital positions of satellites in leo networks - Google Patents
Method for determining the orbital positions of satellites in leo networks Download PDFInfo
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- CA2255127A1 CA2255127A1 CA002255127A CA2255127A CA2255127A1 CA 2255127 A1 CA2255127 A1 CA 2255127A1 CA 002255127 A CA002255127 A CA 002255127A CA 2255127 A CA2255127 A CA 2255127A CA 2255127 A1 CA2255127 A1 CA 2255127A1
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/118—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1085—Swarms and constellations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S5/00—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations
- G01S5/0009—Transmission of position information to remote stations
- G01S5/0081—Transmission between base stations
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S5/00—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations
- G01S5/02—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations using radio waves
- G01S5/12—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations using radio waves by co-ordinating position lines of different shape, e.g. hyperbolic, circular, elliptical or radial
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
Abstract
In order to achieve a considerable reduction of the outlay required on the ground in connection with the accurate calculation of the exact orbital position of each individual satellite of a constellation, first the exact orbital position of a preferably central master satellite of a sub-group of satellites embodied as a special formation is determined. This calculation is performed autonomously on board the satellite by means of customary measurements supported from the ground, or respectively by means of GPS, MANS, etc. Then the exact position of all other satellites in the same formation is determined from range and pointing data, which are provided by each IS link terminal.
These pointing data are well known after the establishment of the inter- satellite link and are continuously updated.
These pointing data are well known after the establishment of the inter- satellite link and are continuously updated.
Description
METHOD FOR DETERMINING THE ORBITAL POSITIONS
OF SATELLITES IN LEO NETWORKS
FIELD OF THE INVENTION
The invention relates to a method for determining the orbital positions of satellites in LEO networks with ring constellations. The invented method is usable everywhere in orbits that have the geometry of LEO satellite networks. The word "LEO", singular or plural, is employed interchangeably herein to refer to any orbital altitude, e.g.also in "MEO" and not to Low Earth Orbits alone.
BACKGROUND OF THE INVENTION
Inter-satellite links are used in connection with communications satellite systems, which are moving in low earth orbits (LEO) and relate to so-called global communications networks, in order to connect the individual satellites of the system in the manner of a "network in the sky". Many satellite systems have already been planned or are even under construction. Satellites) which permit real time transmission of data, sound and video and are known as "big LEOs", are particularly important for the present invention. Examples of this are the so-called IRIDIUM and CELESTRI
systems, originally introduced by Motorola, and the TELEDISC system of Microsoft and McCaw Corp. It is expected that these systems will be functional around the year 2005.
The use of inter-satellite links (ISL), besides the customary earth links (downlinks and uplinks, i.e. from the satellite to the ground or vice versa), distinguishes the above mentioned LEO systems from others) such as GLOBALSTAR (by Globalstar Telecomms. Ltd.).
The main purpose of the global real time satellite communications networks lies in assuring a variable time-dependent transmission capacity to any location in the entire world when needed. Such a dynamic communications network requires real time management. In addition, a universal ana easy access to me neiworK is aemanaea when a wireless access is offered such as is the case, for example, with IRIDIUM. The determination of the exact orbital positions of all satellites is performed by the ground station.
Customarily the maintenance and control of an orbit of a satellite is controlled from the ground. The required orbital adjustment is calculated by the ground station, and a number of commands is generated and uplinked to the satellite, which are then downlinked again for checking. Finally, the ground station transmits a command for starting the control commands and the satellite performs them by using its own cycle generated on board. Such a sequence protects the satellite against transmission errors, since often it is out of sight of the ground station.
Recently autonomous navigation systems have aided in making an autonomous maintenance of the orbit possible, efficient and dependable. These systems can be aided by GPS, or can operate completely independently (MANS by Microcosm). In connection with LEO communications networks, the economical aspect of maintaining the orbit and the constellation are of decisive importance, since a large number of satellites - up to several hundred - must be controlled simultaneously.
The so-called checked autonomy, wherein the orbital maneuvers are initially calculated on board of each satellite, but are only executed after a check by the ground station, is a mechanism for reducing the risks and for utilizing the autonomy in maintaining the orbit.
The greater portion of the LEO satellite networks mentioned above consists of several orbital planes at the same height all around the earth. Generally all orbits of an LEO network have the same inclination in respect to the equator. The same number of satellites is distributed at the same distances from each other in each orbital plane.
Such constellations are called "Walker" orbits. The total number of satellites) followed by the number of orbital planes and the inclination of the orbital plane, are characteristics, which permit a differentiation between all existing LEO
network concepts.
There are sub-groups within a satellite network, which each have a predetermined number - between four and eight - satellites connected with each other for the mentioned communications purposes. Viewed from a satellite in the center of such a sub- group, two types of inter-satellite links can be distinguished: "inter-satellite links within the plane", i.e. links with satellites, which are ahead or behind, but in the same plane) and "inter-satellite links between the planes", i.e. links with satellites located in an adjacent plane or in a plane adjacent to the latter. An additional characteristic of each satellite network is expressed by the so-called "phase between the planes", the angular displacement, which constantly results during the course, between a central satellite of a sub-group and an adjacent satellite in the directly adjacent orbital plane.
An important problem, which results normally in each real time LEO satellite network operating with a fixed "phase between the planes", is to assure that the satellite of the same sub-group always remain in the same relation toward each other.
This requirement is the result of the need to overlap the covered ground zones.
The employment of navigation methods performed or supported from the ground for monitoring the large number of satellites in LEO networks represents a relevant cost factor in maintaining the orbits during the working phase of an established satellite network.
OBJECT OF THE INVENTION
It is therefore the object of the present invention to create a method of the type mentioned at the outset, which is less expensive in maintaining the orbit during the working phase of an established satellite network.
This object is attained by a method with the features recited in the characterizing portion of claim 1.
Advantageous embodiments of this method are recited in the dependent claims.
CA 02255127 1998-12-17 .
OF SATELLITES IN LEO NETWORKS
FIELD OF THE INVENTION
The invention relates to a method for determining the orbital positions of satellites in LEO networks with ring constellations. The invented method is usable everywhere in orbits that have the geometry of LEO satellite networks. The word "LEO", singular or plural, is employed interchangeably herein to refer to any orbital altitude, e.g.also in "MEO" and not to Low Earth Orbits alone.
BACKGROUND OF THE INVENTION
Inter-satellite links are used in connection with communications satellite systems, which are moving in low earth orbits (LEO) and relate to so-called global communications networks, in order to connect the individual satellites of the system in the manner of a "network in the sky". Many satellite systems have already been planned or are even under construction. Satellites) which permit real time transmission of data, sound and video and are known as "big LEOs", are particularly important for the present invention. Examples of this are the so-called IRIDIUM and CELESTRI
systems, originally introduced by Motorola, and the TELEDISC system of Microsoft and McCaw Corp. It is expected that these systems will be functional around the year 2005.
The use of inter-satellite links (ISL), besides the customary earth links (downlinks and uplinks, i.e. from the satellite to the ground or vice versa), distinguishes the above mentioned LEO systems from others) such as GLOBALSTAR (by Globalstar Telecomms. Ltd.).
The main purpose of the global real time satellite communications networks lies in assuring a variable time-dependent transmission capacity to any location in the entire world when needed. Such a dynamic communications network requires real time management. In addition, a universal ana easy access to me neiworK is aemanaea when a wireless access is offered such as is the case, for example, with IRIDIUM. The determination of the exact orbital positions of all satellites is performed by the ground station.
Customarily the maintenance and control of an orbit of a satellite is controlled from the ground. The required orbital adjustment is calculated by the ground station, and a number of commands is generated and uplinked to the satellite, which are then downlinked again for checking. Finally, the ground station transmits a command for starting the control commands and the satellite performs them by using its own cycle generated on board. Such a sequence protects the satellite against transmission errors, since often it is out of sight of the ground station.
Recently autonomous navigation systems have aided in making an autonomous maintenance of the orbit possible, efficient and dependable. These systems can be aided by GPS, or can operate completely independently (MANS by Microcosm). In connection with LEO communications networks, the economical aspect of maintaining the orbit and the constellation are of decisive importance, since a large number of satellites - up to several hundred - must be controlled simultaneously.
The so-called checked autonomy, wherein the orbital maneuvers are initially calculated on board of each satellite, but are only executed after a check by the ground station, is a mechanism for reducing the risks and for utilizing the autonomy in maintaining the orbit.
The greater portion of the LEO satellite networks mentioned above consists of several orbital planes at the same height all around the earth. Generally all orbits of an LEO network have the same inclination in respect to the equator. The same number of satellites is distributed at the same distances from each other in each orbital plane.
Such constellations are called "Walker" orbits. The total number of satellites) followed by the number of orbital planes and the inclination of the orbital plane, are characteristics, which permit a differentiation between all existing LEO
network concepts.
There are sub-groups within a satellite network, which each have a predetermined number - between four and eight - satellites connected with each other for the mentioned communications purposes. Viewed from a satellite in the center of such a sub- group, two types of inter-satellite links can be distinguished: "inter-satellite links within the plane", i.e. links with satellites, which are ahead or behind, but in the same plane) and "inter-satellite links between the planes", i.e. links with satellites located in an adjacent plane or in a plane adjacent to the latter. An additional characteristic of each satellite network is expressed by the so-called "phase between the planes", the angular displacement, which constantly results during the course, between a central satellite of a sub-group and an adjacent satellite in the directly adjacent orbital plane.
An important problem, which results normally in each real time LEO satellite network operating with a fixed "phase between the planes", is to assure that the satellite of the same sub-group always remain in the same relation toward each other.
This requirement is the result of the need to overlap the covered ground zones.
The employment of navigation methods performed or supported from the ground for monitoring the large number of satellites in LEO networks represents a relevant cost factor in maintaining the orbits during the working phase of an established satellite network.
OBJECT OF THE INVENTION
It is therefore the object of the present invention to create a method of the type mentioned at the outset, which is less expensive in maintaining the orbit during the working phase of an established satellite network.
This object is attained by a method with the features recited in the characterizing portion of claim 1.
Advantageous embodiments of this method are recited in the dependent claims.
CA 02255127 1998-12-17 .
The invention will be explained in more detail in what follows by means of the drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a schematic representation of the linkage of individual formations with each other in accordance with the invention, Fig. 2 is a schematic representation of a satellite formation in accordance with the invention, having a master satellite, which communicates with a ground station, Fig. 3 is a schematic representation by means of the example of the CELESTRI
system of individual formations in accordance with the invention, and Fig. 4 is a schematic representation by means of the example of the CELESTRI
system of a formation in accordance with the invention with a continuous ISL
connection during the crossing of the orbital planes.
DETAILED DESCRIPTION
Six orbits are represented in Fig. 1 by respectively one orbital line P1 to P6.
Several satellites can move one after the other in each orbital plane at approximately even spacings. Only some of these many possible satellites are represented in Fig. 1, namely satellites 1 and 2 in orbit P1, satellites 3) 4 and 5 in orbit P2, satellites 6, 7 and 8 in orbit P3, satellites 9 and 10 in orbit P4, satellites 11, 12 and 13 in orbit P5 and satellites 14 and 15 in orbit P6.
The satellites 1 to 5, 7 and 8 are individually represented in Fig. 2. The satellite 4) which is in a central position, is selected as the master satellite in the sense of the invention, so that it is connected, respectively bidirectionally, via earth links with a ground station 16, and via IS links with the other satellites.
Therefore, satellites 1 and 2 form a first ring constellation, satellites 3, 4 and 5 a second ring constellation, and satellites 7 and 8 a third ring constellation.
Generally, a satellite network in accordance with the invention is formed from at least two ring constellations, which all orbit at the same orbital altitude, wherein a ring constellation consists of at least two satellites which circle in the same, in most cases circular, orbit at a defined fixed angular offset in respect to each other.
The satellites 3, 4 and 5 of the second ring constellation form a sort of a communications ring in their orbit, because they are connected with each other via IS
links. Inter alia, the present invention is based on the knowledge that miniaturized optical terminals, in combination with a specific terminal accommodation on board the satellite (Swiss Patent Application 1153/97), make possible uninterrupted inter-satellite communications not only between satellites in the same orbit, but also between a master satellite and the individual satellites of other adjacent ring constellations. In the sense of the present invention, the linkage between individual satellites of a ring constellation and individual satellites of other adjacent ring constellations is considered to be a "formation". This brings the advantage that, in addition to the actual communications purposes, the realization of a very inexpensive, permanent, constantly updated information regarding the respective course positions of all satellites of the respective formation becomes possible, wherein this information can also be used to maintain an exact "phase between the planes" of all satellites in a formation.
When using continuous inter-satellite communications as described above, inter-satellite links can be supported by computations performed in the master satellite in order to achieve a considerable reduction of the outlay required on the ground in connection with the accurate calculation of the exact orbital position of each individual satellite of the constellation.
To achieve this goal, first the exact orbital position of the preferably central master satellite in a formation is determined, and this autonomously on board the satellite by means of customary measurements supported from the ground, or respectively by means of GPS, MANS. Then the exact position of all other satellites in the same formation is determined from range and pointing data, which must be provided by each IS link terminal (Fig. 2). These pointing data are well known after the establishment of the inter-satellite link and are continuously updated.
Since at least one satellite of a network is always in contact with the ground station, any required information regarding each satellite of this network is always available in that a suitable route is formed via the various inter-satellite links, and this even when the satellite of interest is not within the sight range from the ground station.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a schematic representation of the linkage of individual formations with each other in accordance with the invention, Fig. 2 is a schematic representation of a satellite formation in accordance with the invention, having a master satellite, which communicates with a ground station, Fig. 3 is a schematic representation by means of the example of the CELESTRI
system of individual formations in accordance with the invention, and Fig. 4 is a schematic representation by means of the example of the CELESTRI
system of a formation in accordance with the invention with a continuous ISL
connection during the crossing of the orbital planes.
DETAILED DESCRIPTION
Six orbits are represented in Fig. 1 by respectively one orbital line P1 to P6.
Several satellites can move one after the other in each orbital plane at approximately even spacings. Only some of these many possible satellites are represented in Fig. 1, namely satellites 1 and 2 in orbit P1, satellites 3) 4 and 5 in orbit P2, satellites 6, 7 and 8 in orbit P3, satellites 9 and 10 in orbit P4, satellites 11, 12 and 13 in orbit P5 and satellites 14 and 15 in orbit P6.
The satellites 1 to 5, 7 and 8 are individually represented in Fig. 2. The satellite 4) which is in a central position, is selected as the master satellite in the sense of the invention, so that it is connected, respectively bidirectionally, via earth links with a ground station 16, and via IS links with the other satellites.
Therefore, satellites 1 and 2 form a first ring constellation, satellites 3, 4 and 5 a second ring constellation, and satellites 7 and 8 a third ring constellation.
Generally, a satellite network in accordance with the invention is formed from at least two ring constellations, which all orbit at the same orbital altitude, wherein a ring constellation consists of at least two satellites which circle in the same, in most cases circular, orbit at a defined fixed angular offset in respect to each other.
The satellites 3, 4 and 5 of the second ring constellation form a sort of a communications ring in their orbit, because they are connected with each other via IS
links. Inter alia, the present invention is based on the knowledge that miniaturized optical terminals, in combination with a specific terminal accommodation on board the satellite (Swiss Patent Application 1153/97), make possible uninterrupted inter-satellite communications not only between satellites in the same orbit, but also between a master satellite and the individual satellites of other adjacent ring constellations. In the sense of the present invention, the linkage between individual satellites of a ring constellation and individual satellites of other adjacent ring constellations is considered to be a "formation". This brings the advantage that, in addition to the actual communications purposes, the realization of a very inexpensive, permanent, constantly updated information regarding the respective course positions of all satellites of the respective formation becomes possible, wherein this information can also be used to maintain an exact "phase between the planes" of all satellites in a formation.
When using continuous inter-satellite communications as described above, inter-satellite links can be supported by computations performed in the master satellite in order to achieve a considerable reduction of the outlay required on the ground in connection with the accurate calculation of the exact orbital position of each individual satellite of the constellation.
To achieve this goal, first the exact orbital position of the preferably central master satellite in a formation is determined, and this autonomously on board the satellite by means of customary measurements supported from the ground, or respectively by means of GPS, MANS. Then the exact position of all other satellites in the same formation is determined from range and pointing data, which must be provided by each IS link terminal (Fig. 2). These pointing data are well known after the establishment of the inter-satellite link and are continuously updated.
Since at least one satellite of a network is always in contact with the ground station, any required information regarding each satellite of this network is always available in that a suitable route is formed via the various inter-satellite links, and this even when the satellite of interest is not within the sight range from the ground station.
Fig. 1 shows that a satellite network can be considered to consist of several formations, which together constitute the entire network. Although all satellites can be designed in the same manner, in Fig. 1 the satellites of the first formation are represented by small square ideograms, the satellites of the second formation in a similar manner by triangles, and the satellites of the third formation by circles.
Thus, it can be seen from the drawings that the satellites 3, 4, 7 and 8 participate both in the first and the second formation, and that the satellites 9 and 10 are members of the second and third formation. It is practical to select the satellites 4, 7 and 12 as master satellites in this example. The determination of the orbital position of the master satellites of a formation is provided by the use of traditional methods from a ground station, or respectively by the employment of GPS or MANS.
The exact orbital positions of all satellites of a formation are determined in that use is made of the information from the respective inter-satellite link between the central master satellite of the formation and a satellite of interest from this formation.
Customarily this inter-satellite information consists of range information, range-rate information and angle information in the pointing direction (azimuth and elevation). If the actual angle between the inter-satellite terminal of the master satellite and the satellite of interest is known) it is possible to determine from this the pointing vector from the master satellite to the satellite of interest.
In particular, the inter-satellite range information is extremely useful in connection with LEO networks with fixed inter- satellite phases, for example IRIDIUM or CELESTRI.
By monitoring the range information of an inter-satellite link it is possible to predict whether the satellites of a formation are in fixed states in respect to each other, or whether relative movements take place. Therefore, by monitoring of the inter-satellite range information it is possible to compensate for mutual relative movements between the satellites. Such a longtime drift is mainly caused by the effects of the sun, the moon and possibly the atmosphere. Since such a prediction is very sensitive, it is possible to perform small corrective maneuvers by means of the drive jets of the satellites before positional errors become cumulative.
By means of the invention it was learned that in theory, when using p formations in a network consisting of k satellites, the outlay for measurements which must be performed in the ground station to determine the exact orbital positions of all k satellites can be reduced by the factor k/p. It is not possible in actuality to attain this value, since each network has an edge, which constitutes a border of the network and therefore also . CA 02255127 1998-12-17 a geometric interruption thereof. Therefore some additional inter- satellite links are necessary for determining the positions of the satellites of a constellation which are located in the vicinity of the edge.
The additional information regarding the pointing (alignment) data of all inter-satellite terminals of a master of a formation - including values regarding distances, angles and their chronological derivations of d/dt and d2/dt2 - permit an improvement of the accuracy of one and the same position measurement by overlaying all pointing data.
As a rule, formations consist of five to nine satellites. Based on an improvement by the factor n with n pointing data sets involved in the position determination, an improvement of the accuracy by a factor of 2.2 up to a factor of 3 results.
The presence of on-board computers in all satellite types of LEO networks makes it possible to let the satellite perform a running update and storage of its position and pointing data sets autonomously, preferably during times of reduced activity, or respectively reduced burdening by other satellite sub-systems.
In case a satellite in a formation ceases to operate, it is nevertheless possible to determine the position of all other satellites. Even if the central satellite of a formation fails, a new master can be chosen from one of the adjacent satellites.
An inherent redundancy of satellite networks results because each satellite normally is connected by more than one inter-satellite link with other adjacent satellites.
Therefore every inter-satellite link can determine the exact position of a satellite via an interpositioned master. From the similarity of the structure of all satellites of a network arises the possibility of selecting, in response to the requirements, any satellite as the master of a formation. Therefore, an exact position determination of all satellites of a formation is made possible in an excellent manner by means of the ring-overlapping continuous connection of all satellites of a formation.
Fig. 3 shows some formations of the CELESTRI LEO network. From this it is possible to see that the geometric satellite network is built up of ring constellations, and that a communications network consists of ring-overlapping formations.
By means of a CELESTRI example) Fig. 4 shows that a continuous ISL connection within a formation is also possible even when orbital planes are crossed.
.$.
The long-term monitoring of all pointing data of the inter-satellite links of a master can in addition be used for transmitting control signals for the orbital correction to the satellite of the respective inter-satellite link when a defined tolerance threshold has been exceeded.
Thus, it can be seen from the drawings that the satellites 3, 4, 7 and 8 participate both in the first and the second formation, and that the satellites 9 and 10 are members of the second and third formation. It is practical to select the satellites 4, 7 and 12 as master satellites in this example. The determination of the orbital position of the master satellites of a formation is provided by the use of traditional methods from a ground station, or respectively by the employment of GPS or MANS.
The exact orbital positions of all satellites of a formation are determined in that use is made of the information from the respective inter-satellite link between the central master satellite of the formation and a satellite of interest from this formation.
Customarily this inter-satellite information consists of range information, range-rate information and angle information in the pointing direction (azimuth and elevation). If the actual angle between the inter-satellite terminal of the master satellite and the satellite of interest is known) it is possible to determine from this the pointing vector from the master satellite to the satellite of interest.
In particular, the inter-satellite range information is extremely useful in connection with LEO networks with fixed inter- satellite phases, for example IRIDIUM or CELESTRI.
By monitoring the range information of an inter-satellite link it is possible to predict whether the satellites of a formation are in fixed states in respect to each other, or whether relative movements take place. Therefore, by monitoring of the inter-satellite range information it is possible to compensate for mutual relative movements between the satellites. Such a longtime drift is mainly caused by the effects of the sun, the moon and possibly the atmosphere. Since such a prediction is very sensitive, it is possible to perform small corrective maneuvers by means of the drive jets of the satellites before positional errors become cumulative.
By means of the invention it was learned that in theory, when using p formations in a network consisting of k satellites, the outlay for measurements which must be performed in the ground station to determine the exact orbital positions of all k satellites can be reduced by the factor k/p. It is not possible in actuality to attain this value, since each network has an edge, which constitutes a border of the network and therefore also . CA 02255127 1998-12-17 a geometric interruption thereof. Therefore some additional inter- satellite links are necessary for determining the positions of the satellites of a constellation which are located in the vicinity of the edge.
The additional information regarding the pointing (alignment) data of all inter-satellite terminals of a master of a formation - including values regarding distances, angles and their chronological derivations of d/dt and d2/dt2 - permit an improvement of the accuracy of one and the same position measurement by overlaying all pointing data.
As a rule, formations consist of five to nine satellites. Based on an improvement by the factor n with n pointing data sets involved in the position determination, an improvement of the accuracy by a factor of 2.2 up to a factor of 3 results.
The presence of on-board computers in all satellite types of LEO networks makes it possible to let the satellite perform a running update and storage of its position and pointing data sets autonomously, preferably during times of reduced activity, or respectively reduced burdening by other satellite sub-systems.
In case a satellite in a formation ceases to operate, it is nevertheless possible to determine the position of all other satellites. Even if the central satellite of a formation fails, a new master can be chosen from one of the adjacent satellites.
An inherent redundancy of satellite networks results because each satellite normally is connected by more than one inter-satellite link with other adjacent satellites.
Therefore every inter-satellite link can determine the exact position of a satellite via an interpositioned master. From the similarity of the structure of all satellites of a network arises the possibility of selecting, in response to the requirements, any satellite as the master of a formation. Therefore, an exact position determination of all satellites of a formation is made possible in an excellent manner by means of the ring-overlapping continuous connection of all satellites of a formation.
Fig. 3 shows some formations of the CELESTRI LEO network. From this it is possible to see that the geometric satellite network is built up of ring constellations, and that a communications network consists of ring-overlapping formations.
By means of a CELESTRI example) Fig. 4 shows that a continuous ISL connection within a formation is also possible even when orbital planes are crossed.
.$.
The long-term monitoring of all pointing data of the inter-satellite links of a master can in addition be used for transmitting control signals for the orbital correction to the satellite of the respective inter-satellite link when a defined tolerance threshold has been exceeded.
Claims (10)
1. A method for determining the orbital positions of satellites in LEO
networks with ring constellations, characterized in that one satellite from a selected ring constellation is designated as master satellite, a satellite formation is formed by this master satellite and at least respectively one further satellite of the selected ring constellation and of two further ring constellations, the master satellite is brought into bidirectional communication with a ground station, via miniaturized optical terminals, the master satellite is optically brought into bidirectional communications with the other satellites of the formation by means of interruption-free inter- satellite links, and at least the master satellite has an on-board computer for supporting the computations of the ground station in order to obtain informational data for determining the orbital positions of the satellites of this formation.
networks with ring constellations, characterized in that one satellite from a selected ring constellation is designated as master satellite, a satellite formation is formed by this master satellite and at least respectively one further satellite of the selected ring constellation and of two further ring constellations, the master satellite is brought into bidirectional communication with a ground station, via miniaturized optical terminals, the master satellite is optically brought into bidirectional communications with the other satellites of the formation by means of interruption-free inter- satellite links, and at least the master satellite has an on-board computer for supporting the computations of the ground station in order to obtain informational data for determining the orbital positions of the satellites of this formation.
2. The method in accordance with claim 1, characterized in that at least two such formations with at least one common satellite are formed, through which an interruption-free communication path between the two master satellites is created in order to provide informational data for determining the orbital positions of the satellites of the one formation for the master satellite of the other formation.
3. The method in accordance with claim 1 or 2, characterized in that at least one master satellite always remains in communication with the ground station.
4. The method in accordance with one of claims 1 to 3, characterized in that the informational data include inter-satellite link information containing range information, pointing data information and angle information in the pointing direction (azimuth and elevation).
5. The method in accordance with one of claims 1 to 4, characterized in that initially the exact orbital position of a master satellite of a formation is determined by means of measurements supported from the ground, and then the exact position of all other satellites of the same formation is determined from range and pointing data provided by each IS link terminal.
6. The method in accordance with one of claims 1 to 5, characterized in that the range information of the satellite links is monitored from a master satellite in order to determine whether position errors, which exceed defined tolerance threshold values, become cumulative, and that in accordance with this monitoring, the master satellite provides control signals for the actuation of satellite drives in order to correct the position of a satellite in such a case.
7. The method in accordance with one of claims 2 to 6, characterized in that for improving the accuracy of the position determination, the positions of the satellites are determined by means of average values from several different pointing data sets, which are obtained via different routes and/or sequentially.
8. The method in accordance with one of claims 2 to 7, characterized in that the on-board computers of all satellites in a formation perform a running update and storage of the informational data containing position and pointing data sets, preferably at times of reduced activity or reduced burdening by other satellite sub-systems.
9. The method in accordance with one of claims 2 to 8, characterized in that each formation consists of four to twelve satellites.
10. The method in accordance with one of claims 2 to 9, characterized in that a continuous ISL connection within each formation is maintained during crossing of orbital planes.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH37098 | 1998-02-16 | ||
| CH19980370/98 | 1998-02-16 |
Publications (1)
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| CA2255127A1 true CA2255127A1 (en) | 1999-08-16 |
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Family Applications (1)
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| CA002255127A Abandoned CA2255127A1 (en) | 1998-02-16 | 1998-12-17 | Method for determining the orbital positions of satellites in leo networks |
Country Status (5)
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| US (1) | US6219617B1 (en) |
| EP (1) | EP0887656B1 (en) |
| JP (1) | JPH11255200A (en) |
| CA (1) | CA2255127A1 (en) |
| DE (1) | DE59800354D1 (en) |
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-
1998
- 1998-09-08 DE DE59800354T patent/DE59800354D1/en not_active Expired - Lifetime
- 1998-09-08 EP EP98116907A patent/EP0887656B1/en not_active Expired - Lifetime
- 1998-12-17 CA CA002255127A patent/CA2255127A1/en not_active Abandoned
-
1999
- 1999-01-05 US US09/225,916 patent/US6219617B1/en not_active Expired - Lifetime
- 1999-01-14 JP JP11007468A patent/JPH11255200A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1837680A1 (en) * | 2006-03-23 | 2007-09-26 | Alcatel Lucent | Deployment control system for spacecraft having to fly in formation using simultaneous high precision determination of their positions |
| WO2007107604A1 (en) * | 2006-03-23 | 2007-09-27 | Thales | System for controlling the deployment of spacecraft required to fly in formation, by simultaneous and high-precision determination of their positions |
| US8096511B2 (en) * | 2006-03-23 | 2012-01-17 | Thales | System for controlling the deployment of spacecraft required to fly in formation, by simultaneous and high-precision determination of their positions |
| US7595749B2 (en) | 2006-05-29 | 2009-09-29 | Eads Astrium Gmbh | Method and device for relative time and position determination for moving objects based on one-way and two-way measurements |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH11255200A (en) | 1999-09-21 |
| EP0887656A1 (en) | 1998-12-30 |
| EP0887656B1 (en) | 2000-11-29 |
| DE59800354D1 (en) | 2001-01-04 |
| US6219617B1 (en) | 2001-04-17 |
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