CN112987044B - Constellation ephemeris on-orbit updating method - Google Patents
Constellation ephemeris on-orbit updating method Download PDFInfo
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- CN112987044B CN112987044B CN202110208837.5A CN202110208837A CN112987044B CN 112987044 B CN112987044 B CN 112987044B CN 202110208837 A CN202110208837 A CN 202110208837A CN 112987044 B CN112987044 B CN 112987044B
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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
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/25—Acquisition or tracking or demodulation of signals transmitted by the system involving aiding data received from a cooperating element, e.g. assisted GPS
- G01S19/258—Acquisition or tracking or demodulation of signals transmitted by the system involving aiding data received from a cooperating element, e.g. assisted GPS relating to the satellite constellation, e.g. almanac, ephemeris data, lists of satellites in view
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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
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/27—Acquisition or tracking or demodulation of signals transmitted by the system creating, predicting or correcting ephemeris or almanac data within the receiver
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- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
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- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention discloses an on-orbit updating method of a constellation ephemeris, which comprises the steps of firstly, judging whether a satellite is a newly added network satellite, if so, updating extrapolated multi-point ephemeris data within T0-T0 +2T time, and updating a real-time broadcast two-point ephemeris at T0 and T0+ T time after the GNSS is normally positioned, wherein T0 is the current time, and T is the ephemeris extrapolation time requirement; then, updating real-time broadcast two-point ephemeris data at T0 and T0+ T moments simultaneously every second by adopting a sliding updating method; and updating the extrapolated multipoint ephemeris data in the subsequent 2T time as a spare at specified time intervals.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an on-orbit updating method for constellation ephemeris.
Background
With the continuous improvement of business requirements of space navigation, remote sensing, communication and the like, satellites with enhanced navigation, ground communication service, ground observation and the like all present massive constellation networking development situations, particularly represented by Starlink constellations and OneWeb constellations.
The constellation satellite needs to enter inter-planet antenna pointing control according to satellite ephemeris, so ephemeris update is the basis of on-orbit operation control. In addition, for the inter-satellite cooperative task satellite, the cooperative task planning needs to be performed according to the cooperative satellite ephemeris. At present, in the traditional ephemeris updating method, multipoint ephemeris data are injected on the ground or positioning is carried out in real time through a GNSS receiver, and meanwhile, satellite track points in a certain period of time are predicted by adopting an orbit extrapolation method on the satellite. The ground multi-point ephemeris data injection has the problems of low ephemeris precision, need of periodic update and large single data injection amount; the GNSS positioning extrapolation broadcasting method is mainly used for short-time orbit extrapolation, and extrapolates each track point in a subsequent time period, and has the defects of large calculation amount and high bandwidth for implementing broadcasting exhibition. The method has clear application requirements on how to realize the on-orbit updating of the constellation ephemeris with low cost and high efficiency.
Disclosure of Invention
Aiming at partial or all problems in the prior art, the invention provides an on-orbit updating method of constellation ephemeris, which comprises the following steps:
judging whether the satellite is a newly-added satellite, if so, updating the extrapolated multi-point ephemeris data within the time of T0-T0 +2T and performing whole-network broadcasting, wherein the extrapolated multi-point ephemeris data is obtained by ground injection, and after the GNSS is normally positioned, updating the real-time broadcast two-point ephemeris at the time of T0 and T0+ T and performing whole-network broadcasting, wherein T0 is the current time, and T is the ephemeris extrapolation time requirement;
when the satellite is normally in orbit during network access, updating the real-time broadcast two-point ephemeris data at the current time T0 and T0+ T simultaneously every second by adopting a sliding updating method; and updating the extrapolated multipoint ephemeris at a subsequent 2T moment as a spare at a specified time interval, wherein T is the ephemeris extrapolation time requirement.
Further, the extrapolated multi-point ephemeris data comprises satellite extrapolated ephemeris data for a plurality of time points, and the time interval of each point is equal to the sampling interval used for constellation orbit extrapolation.
Further, the extrapolated multi-point ephemeris data has the same data protocol as the real-time broadcast two-point ephemeris data.
Further, the extrapolating multi-point ephemeris and real-time broadcasting two-point ephemeris data comprises: data type, data length, ephemeris interval, initial time, satellite position, and satellite velocity.
Further, the specified time interval is constant and is equal to T.
Furthermore, the specified time interval is unchanged, the ephemeris accuracy requirement is determined, and the value of the extrapolation point in the service period T is increased to be equal to T/n, wherein T/n is a natural number.
According to the constellation ephemeris on-orbit updating method provided by the invention, through the strategies of sampling calculation and sliding updating, the calculated amount and the transmission bandwidth are reduced, meanwhile, through the design of sampling points, the use requirements of different ephemeris accuracies are met, a low-overhead and high-efficiency solution is provided for on-orbit applications such as inter-satellite link establishment communication and inter-satellite cooperative task planning, and the problems of large calculated amount and high occupied bandwidth of multi-satellite ephemeris updating are solved.
Drawings
To further clarify the above and other advantages and features of embodiments of the present invention, a more particular description of embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
Fig. 1 is a schematic flowchart illustrating an on-orbit constellation ephemeris update method according to an embodiment of the present invention; and
figure 2 illustrates an on-orbit update of constellation ephemeris, in accordance with an embodiment of the invention.
Detailed Description
In the following description, the present invention is described with reference to examples. One skilled in the relevant art will recognize, however, that the embodiments may be practiced without one or more of the specific details, or with other alternative and/or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention. Similarly, for purposes of explanation, specific numbers, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention is not limited to these specific details. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
It should be noted that the embodiment of the present invention describes the process steps in a specific order, however, this is only for the purpose of illustrating the specific embodiment, and does not limit the sequence of the steps. Rather, in various embodiments of the present invention, the order of the steps may be adjusted according to process adjustments.
Aiming at the defects of large data volume, large calculation amount and the like of single injection of the conventional ephemeris, the invention provides the on-orbit updating method of the constellation ephemeris, which reduces the calculation amount and transmission bandwidth through the strategies of sampling calculation and sliding updating, and can meet the use requirements of different ephemeris precisions through the design of sampling points. The solution of the invention is further described below with reference to the accompanying drawings of embodiments.
Fig. 1 is a flowchart illustrating an on-orbit constellation ephemeris update method according to an embodiment of the present invention. As shown in the figure, an on-orbit update method for constellation ephemeris includes:
first, in step 101, the orbiting ephemeris is updated. For a satellite newly added to the network, preferentially updating the extrapolated multi-point ephemeris data within the time of T0-T0 +2T, wherein the extrapolated multi-point ephemeris data is obtained through ground injection, the extrapolated multi-point ephemeris comprises satellite extrapolated ephemeris data of a plurality of points, the time interval of each point is equal to the constellation use sampling interval, taking T90 min as an example, after a new satellite enters the orbit, preferentially updating the extrapolated multi-point ephemeris data within the time of T0-T0 +3h, and the constellation use sampling interval is 1h, namely four points of data of T0, T0+1h, T0+2h and T0+3h are updated. When the satellite is normally positioned in the orbiting GNSS, updating a real-time broadcast two-point ephemeris at the time of T0 and T0+ T and performing full-network broadcast, wherein T is the ephemeris extrapolation time requirement, T0 is the current time, taking T equal to 90min as an example, and after the satellite is normally positioned in the orbiting GNSS, the satellite updates data at two times of T0 and T0+90 min; in the embodiment of the invention, the extrapolated multi-point ephemeris data is obtained by ground injection and the real-time broadcast two-point ephemeris, which are current time ephemeris and extrapolated time ephemeris determined after GNSS positioning;
next, at step 102, the on-orbit ephemeris is updated. When the satellite is normally in orbit after being networked, updating two-point ephemeris data once per second by adopting a sliding updating method, and updating data at two moments of T0 and T0+ T at the same time each time, as shown in FIG. 2, wherein T0 is the current moment and T0+ T is the longest moment of task requirement, and after sampling sliding updating, each satellite can be ensured to have high-precision ephemeris from the current moment to the subsequent T time period. Taking T ═ 90min as an example, the ephemeris of T0, T0+90min is updated in the first second, the data of T0+1s and T0+90min +1s are updated in the second, the data at two moments are updated each time, after 90min, all the data on the satellite are updated once and the constellation shares the ephemeris of each satellite for the subsequent 90 min; and
at the same time, at step 103, the extrapolated multi-point ephemeris data is updated. And updating the extrapolated multi-point ephemeris data in the subsequent 2T moment at a specified time interval, such as T time, and using the extrapolated multi-point ephemeris data as backup ephemeris under abnormal constellation operation. For example, at time T0, T0+90min, and the like, the constellation usage sampling interval is 1 hour, and the extrapolated multi-point ephemeris data is periodically updated (T0, T0+1h, T0+2h, T0+3h), (T0+90min, T0+1h +90min, T0+2h +90min, T0+3h +90 min). In other embodiments of the present invention, if the requirement of the satellite for ephemeris accuracy is higher, the number of ephemeris sampling points to be updated in real time is adjusted according to the actual use requirement of the constellation ephemeris and the satellite orbit extrapolation accuracy, so as to improve the ephemeris accuracy, wherein if the accuracy is high in a short time and low in a T period, the sampling points may be selected to be added within T0 to T0+ T, for example, T0, T0+1/2T, T0+ T, and T0+ T may be selected at the ephemeris update time, where T refers to a time length in which high accuracy is required; and if the ephemeris accuracy needs to be improved in the T period, increasing the sampling points from T0 to T may be selected, for example, the ephemeris update time may be selected from T0, T0+1/3T, and T0+2/3T, T0+ T.
In the embodiment of the present invention, the data protocol of the extrapolated multi-point ephemeris data is the same as that of the real-time broadcast two-point ephemeris data, and the data amount occupation is reduced in the form of accumulated seconds, and the format of the extrapolated multi-point ephemeris data is shown in table 1 and includes: data type, data length, ephemeris interval, initial time, satellite position, and satellite velocity. Wherein the data type is used to distinguish whether the data is extrapolated multi-point ephemeris or real-time broadcast two-point ephemeris, in an embodiment of the invention, 0x5A represents extrapolated multi-point ephemeris, and 0xA5 represents real-time broadcast two-point ephemeris; the data length is equal to N x 24+9, wherein N is the number of ephemeris data; the ephemeris interval is the time interval of two pieces of ephemeris data, and the unit is second; the initial time refers to the time corresponding to the first ephemeris data and the accumulated seconds after the time of the constellation timing epoch; and the ephemeris data comprises satellite coordinate values X, Y, Z and velocities VX, VY and VZ of the satellite in each direction, each ephemeris data comprising 24 bytes as a floating point number.
| Data type | Data length | Ephemeris interval | Initial time | Ephemeris |
…… | Ephemeris |
| 1 |
2 |
2 bytes | 4 bytes | 24 bytes | 24 bytes |
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
Claims (7)
1. An on-orbit update method for constellation ephemeris, comprising the steps of:
judging whether the satellite is a newly-added network satellite, if so, updating the extrapolated multi-point ephemeris data within the time of T0-T0 +2T and performing whole-network broadcasting, and after the GNSS is normally positioned, updating the real-time broadcast two-point ephemeris at the time of T0 and T0+ T and performing whole-network broadcasting, wherein T0 is the current time, and T is the ephemeris extrapolation time requirement;
when the satellite is normally in orbit during network access, updating real-time broadcast two-point ephemeris data at T0 and T0+ T moments simultaneously every second by adopting a sliding updating method; and
and updating the extrapolated multipoint ephemeris data in the subsequent 2T moment at specified time intervals for standby.
2. The method of claim 1, wherein the extrapolated multi-point ephemeris data is acquired by a ground-based injection.
3. The method of claim 1, wherein the extrapolated multi-point ephemeris data comprises extrapolated ephemeris data for a plurality of points, and wherein the time intervals for the points are equal to a constellation usage sampling interval.
4. The method of claim 1, wherein the extrapolated multi-point ephemeris data is the same data protocol as the real-time broadcast two-point ephemeris data.
5. The method of claim 4, wherein the extrapolating the multi-point ephemeris data and broadcasting the two-point ephemeris data in real-time comprises: data type, data length, ephemeris interval, initial time, and a plurality of ephemeris data, wherein the ephemeris data includes satellite position and satellite velocity.
6. The method of claim 1, wherein the specified time interval is equal to T.
7. The method of claim 1, wherein the specified time interval is determined according to ephemeris accuracy requirements, the specified time interval having a value equal to T/n, and T/n being a natural number.
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