CN116015405A - Access method of LEO communication system low orbit satellite - Google Patents
Access method of LEO communication system low orbit satellite Download PDFInfo
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- CN116015405A CN116015405A CN202211598417.3A CN202211598417A CN116015405A CN 116015405 A CN116015405 A CN 116015405A CN 202211598417 A CN202211598417 A CN 202211598417A CN 116015405 A CN116015405 A CN 116015405A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention provides an access method of a low orbit satellite of an LEO communication system, which comprises the following steps: and estimating azimuth angle and pitch angle of a terminal antenna based on GPS position information, inertial navigation attitude information and LEO satellite position information of a satellite terminal, and simultaneously estimating signal transmitting time and signal transmitting power so as to complete real-time tracking and access of a low-orbit satellite. Compared with the existing satellite network access scheme, the method and the system can enable the satellite terminal to quickly complete searching and tracking of the low-orbit satellite, ensure that the satellite terminal can access the satellite network in real time to carry out service communication, and solve the problems of long satellite access time, difficult satellite dynamic tracking, poor practicability and the like caused by long power retrieval time and other reasons of the existing satellite network access.
Description
Technical Field
The invention relates to the technical field of LEO communication systems, in particular to an access method of a low-orbit satellite of an LEO communication system.
Background
At present, the known satellite network access schemes are all access schemes based on a high-orbit satellite network, and the schemes have the following characteristics:
1. LEO satellite search
The access scheme satellite search process of the high orbit satellite network adopts a power search scheme: the power scanning is carried out in the general direction of the satellite through the satellite terminal antenna, and the maximum direction of the received signal power is determined to be the direction of the satellite.
2. LEO satellite tracking
After the satellite search is completed, tracking the satellite by the satellite terminal is completed by utilizing inertial navigation attitude measurement information, namely, a servo system of the satellite terminal adjusts the orientation of an antenna according to the attitude change of the satellite terminal so as to complete the tracking of the satellite by the mobile terminal;
3. time of signal transmission
Because the moving speed of the ground satellite terminal is usually very slow, the time delay from the high orbit satellite to the satellite terminal is basically fixed; the service communication can be completed without changing the transmitting time window in the terminal access process;
4. signal transmission power
Since the movement speed of a ground satellite terminal is generally slow, the distance from a high orbit satellite to the satellite terminal is substantially fixed for a period of time; the terminal can complete service communication without changing signal transmitting power in the communication process;
the satellite terminals need to face the following problems if they need to complete access to the TDMA low-orbit satellite network:
1. LEO satellite search
Because the high-speed motion of the low-orbit satellite, the satellite search by adopting the power detection scheme can be faced with the condition that the satellite position is transformed just after the satellite search is finished, so the low-orbit satellite is difficult to finish the search by adopting the power detection scheme.
2. LEO satellite tracking
Because of the high-speed motion of the low-orbit satellite, the satellite terminal not only needs to solve the azimuth change caused by the motion of the satellite, but also needs to solve the azimuth change caused by the high-speed motion of the satellite.
3. Time of signal transmission
High throughput low orbit satellite communication generally adopts a TDMA mode to access a plurality of terminals, which requires that the transmitting signals of the terminals reach the receiving ports of the satellites in a fixed time window; because of the high-speed motion of the satellite, the terminal needs to solve the transmission delay change caused by the high-speed motion of the satellite, so as to ensure that the transmitting signal of the satellite terminal can reach the satellite in a fixed time window.
4. Signal transmission power
Because of the high-speed motion of the low-orbit satellite, the distance between the low-orbit satellite and the satellite terminal can be greatly changed in a short time; the satellite terminal needs to monitor the distance to the satellite in real time and adjust the signal transmission power accordingly.
Disclosure of Invention
The invention aims to provide an access method of a low-orbit satellite of an LEO communication system, which aims to solve the problem that a satellite terminal completes the access to the low-orbit satellite.
The invention provides an access method of a low orbit satellite of an LEO communication system, which comprises the following steps:
and estimating azimuth angle and pitch angle of a terminal antenna based on GPS position information, inertial navigation attitude information and LEO satellite position information of a satellite terminal, and simultaneously estimating signal transmitting time and signal transmitting power so as to complete real-time tracking and access of a low-orbit satellite.
Further, the access method of the LEO communication system low-orbit satellite comprises the following steps:
s100, the satellite terminal captures and analyzes satellite broadcast information;
s200, satellite coordinate data in satellite broadcast information analyzed by a satellite terminal are coordinate data of 6 orbits based on an SGP4 model, and the satellite terminal performs coordinate conversion and calculation on the coordinate data of the 6 orbits to obtain satellite position information and satellite speed information based on an ECEF coordinate system;
s300, based on satellite position information and satellite speed information, estimating the position of a satellite in a period of time in the future to form a time-position information table, and controlling a terminal antenna servo system according to the time-position information table, so that the search and real-time tracking of the satellite are completed;
s400, calculating the distance between the satellite and the satellite terminal in a future period based on the GPS position information of the satellite terminal and the satellite position information, so as to estimate the satellite signal space transmission loss in the future period;
s500, adjusting the signal transmitting power of the satellite terminal according to the estimated satellite signal space transmission loss so as to ensure that the power of the satellite terminal signal when reaching the satellite is within the satellite signal receiving range;
s600, calculating signal transmission time delay according to the distance between the satellite and the satellite terminal in a future period, and adjusting signal emission time according to the signal transmission time delay so as to ensure that the signal can reach the satellite in a specific time window;
and S700, the satellite terminal sends a login request to log in.
Further, in step S100, when the satellite terminal first accesses the satellite, the long-term almanac locally stored in the satellite terminal is used to obtain relevant information.
Further, in step S200, the method for performing coordinate transformation and calculation includes:
s201, calculating a close point angle E by using an iteration method: m=e-E sin E;
s202, calculating a true near point angle v:
s203, a satellite position information calculation formula based on an ECEF coordinate system is as follows:
x s ＝a(1-ecosE)cos(v+ω)cosΩ-a(1-ecosE)sin(v+ω)cosisinΩ；
y s ＝a(1-ecosE)cos(v+ω)sinΩ+a(1-ecosE)sin(v+ω)cosicosΩ；
z s ＝a(1-ecosE)sin(v+ω)sini；
wherein x is s 、y s 、z s Representing coordinates of satellite position information in three directions of x, y and z based on an ECEF coordinate system; a, e, i, omega, M are 6 tracks based on SGP4 model;
s204, a satellite speed information calculation formula based on an ECEF coordinate system is as follows:
V x ＝dx s /dt；
V y ＝dx s /dt；
V z ＝dx s /dt。
wherein V is x 、V y 、V z The velocity of satellite velocity information in the x, y, z directions based on the ECEF coordinate system is represented.
Further, in step S400, the method for calculating the distance between the satellite and the satellite terminal in a future period of time includes:
where d represents the distance between the satellite and the satellite terminal for a future period of time, x ue 、y ue 、z ue And the coordinates of the satellite terminal in the x, y and z directions are shown.
Further, in step S400, the method for estimating the satellite signal space transmission loss in a future period of time includes:
Lu＝92.44+20lg(d)+20lg(f)
where Lu denotes the satellite signal space transmission loss in a future period of time and f denotes the frequency of the satellite signal.
Further, in step S600, the method for calculating the signal transmission delay is as follows:
δt＝d/c
wherein δt represents the signal transmission delay, and c represents the speed of light.
Further, in step S600, the signal transmission time is adjusted to be t-d/c according to the signal transmission delay, where t represents the signal transmission time before adjustment.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
compared with the existing satellite network access scheme, the method and the system can enable the satellite terminal to quickly complete searching and tracking of the low-orbit satellite, ensure that the satellite terminal can access the satellite network in real time to carry out service communication, and solve the problems of long satellite access time, difficult satellite dynamic tracking, poor practicability and the like caused by long power retrieval time and other reasons of the existing satellite network access.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following description will briefly describe the drawings in the embodiments, it being understood that the following drawings only illustrate some embodiments of the present invention and should not be considered as limiting the scope, and that other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a flowchart of a method for accessing a low-orbit satellite of an LEO communication system according to an embodiment of the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Examples
The embodiment provides an access method of a low orbit satellite of an LEO communication system, which comprises the following steps: and estimating azimuth angle and pitch angle of a terminal antenna based on GPS position information, inertial navigation attitude information and LEO satellite position information of a satellite terminal, and simultaneously estimating signal transmitting time and signal transmitting power so as to complete real-time tracking and access of a low-orbit satellite. As shown in fig. 1, the method specifically comprises the following steps:
s100, the satellite terminal captures and analyzes satellite broadcast information; it should be noted that, when the satellite terminal first accesses the satellite, the relevant information is acquired using the long-term almanac locally stored by the satellite terminal.
S200, satellite coordinate data in satellite broadcast information analyzed by a satellite terminal are coordinate data of the number (a, e, i, omega, M) of orbits 6 based on an SGP4 model, and the satellite terminal performs coordinate conversion and calculation on the coordinate data of the number of orbits 6 to obtain satellite position information and satellite speed information based on an ECEF coordinate system; the method for carrying out coordinate conversion and calculation comprises the following steps:
s201, calculating a close point angle E by using an iteration method: m=e-E sin E;
s202, calculating a true near point angle v:
s203, a satellite position information calculation formula based on an ECEF coordinate system is as follows:
x s ＝a(1-ecosE)cos(v+ω)cosΩ-a(1-ecosE)sin(v+ω)cosisinΩ；
y s ＝a(1-ecosE)cos(v+ω)sinΩ+a(1-ecosE)sin(v+ω)cosicosΩ；
z s ＝a(1-ecosE)sin(v+ω)sini；
wherein x is s 、y s 、z s Representing coordinates of satellite position information in three directions of x, y and z based on an ECEF coordinate system;
s204, a satellite speed information calculation formula based on an ECEF coordinate system is as follows:
V x ＝dx s /dt；
V y ＝dx s /dt；
V z ＝dx s /dt。
wherein V is x 、V y 、V z The velocity of satellite velocity information in the x, y, z directions based on the ECEF coordinate system is represented.
S300, based on satellite position information and satellite speed information, estimating the position of a satellite in a period of time in the future to form a time-position information table, and controlling a terminal antenna servo system according to the time-position information table, so that the search and real-time tracking of the satellite are completed;
s400, calculating the distance between the satellite and the satellite terminal in a future period based on the GPS position information of the satellite terminal and the satellite position information, so as to estimate the satellite signal space transmission loss in the future period; the method for calculating the distance between the satellite and the satellite terminal in a future period of time comprises the following steps:
where d represents the distance between the satellite and the satellite terminal for a future period of time, x ue 、y ue 、z ue And the coordinates of the satellite terminal in the x, y and z directions are shown.
S500, adjusting the satellite terminal signal transmitting power Po according to the estimated satellite signal space transmission loss so as to ensure that the power of the satellite terminal signal reaching the satellite is within the satellite signal receiving range; wherein:
the method for estimating the satellite signal space transmission loss in a future period of time comprises the following steps:
Lu＝92.44+20lg(d)+20lg(f)
where Lu denotes the satellite signal space transmission loss in a future period of time and f denotes the frequency of the satellite signal.
S600, calculating signal transmission time delay according to the distance between the satellite and the satellite terminal in a future period, and adjusting signal emission time according to the signal transmission time delay so as to ensure that the signal can reach the satellite in a specific time window; wherein: the method for calculating the signal transmission delay comprises the following steps:
δt＝d/c
wherein δt represents the signal transmission delay, and c represents the speed of light.
Adjusting the signal transmitting time according to the signal transmission time delay is as follows:
t-d/c
where t represents the signal transmission time before adjustment.
S700, setting the antenna transmitting power as Po and the transmitting time as t-d/c, and transmitting a login request by the satellite terminal for login.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. An access method for a low-orbit satellite of an LEO communication system, comprising:
and estimating azimuth angle and pitch angle of a terminal antenna based on GPS position information, inertial navigation attitude information and LEO satellite position information of a satellite terminal, and simultaneously estimating signal transmitting time and signal transmitting power so as to complete real-time tracking and access of a low-orbit satellite.
2. The method for accessing a low-orbit satellite for an LEO communication system according to claim 1, comprising the steps of:
s100, the satellite terminal captures and analyzes satellite broadcast information;
s200, satellite coordinate data in satellite broadcast information analyzed by a satellite terminal are coordinate data of 6 orbits based on an SGP4 model, and the satellite terminal performs coordinate conversion and calculation on the coordinate data of the 6 orbits to obtain satellite position information and satellite speed information based on an ECEF coordinate system;
s300, based on satellite position information and satellite speed information, estimating the position of a satellite in a period of time in the future to form a time-position information table, and controlling a terminal antenna servo system according to the time-position information table, so that the search and real-time tracking of the satellite are completed;
s400, calculating the distance between the satellite and the satellite terminal in a future period based on the GPS position information of the satellite terminal and the satellite position information, so as to estimate the satellite signal space transmission loss in the future period;
s500, adjusting the signal transmitting power of the satellite terminal according to the estimated satellite signal space transmission loss so as to ensure that the power of the satellite terminal signal when reaching the satellite is within the satellite signal receiving range;
s600, calculating signal transmission time delay according to the distance between the satellite and the satellite terminal in a future period, and adjusting signal emission time according to the signal transmission time delay so as to ensure that the signal can reach the satellite in a specific time window;
and S700, the satellite terminal sends a login request to log in.
3. The method according to claim 2, wherein in step S100, the satellite terminal obtains the relevant information by using a long-term almanac stored locally in the satellite terminal when the satellite terminal first accesses the satellite.
4. The method for accessing a low-orbit satellite of an LEO communication system according to claim 2, wherein in step S200, the method for performing coordinate transformation and calculation is as follows:
s201, calculating a close point angle E by using an iteration method: m=e-E sin E;
s202, calculating a true near point angle v:
s203, a satellite position information calculation formula based on an ECEF coordinate system is as follows:
x s ＝a(1-ecosE)cos(v+ω)cosΩ-a(1-ecosE)sin(v+ω)cosisinΩ；
y s ＝a(1-ecosE)cos(v+ω)sinΩ+a(1-ecosE)sin(v+ω)cosicosΩ；
z s ＝a(1-ecosE)sin(v+ω)sini；
wherein x is s 、y s 、z s Representing coordinates of satellite position information in three directions of x, y and z based on an ECEF coordinate system; a, e, i, omega, M are 6 tracks based on SGP4 model;
s204, a satellite speed information calculation formula based on an ECEF coordinate system is as follows:
V x ＝dx s /dt；
V y ＝dx s /dt；
V z ＝dx s /dt。
wherein V is x 、V y 、V z The velocity of satellite velocity information in the x, y, z directions based on the ECEF coordinate system is represented.
5. The method for accessing a low-orbit satellite for an LEO communication system according to claim 4, wherein in step S400, the method for calculating the distance between the satellite and the satellite terminal in a future period of time comprises:
where d represents the distance between the satellite and the satellite terminal for a future period of time, x ue 、y ue 、z ue And the coordinates of the satellite terminal in the x, y and z directions are shown.
6. The method for accessing a low-orbit satellite for an LEO communication system according to claim 5, wherein in step S400, the method for estimating the satellite signal space transmission loss in a future period of time comprises:
Lu＝92.44+20lg(d)+20lg(f)
where Lu denotes the satellite signal space transmission loss in a future period of time and f denotes the frequency of the satellite signal.
7. The method for accessing a low-orbit satellite for an LEO communication system according to claim 6, wherein in step S600, the method for calculating the signal transmission delay is as follows:
δt＝d/c
wherein δt represents the signal transmission delay, and c represents the speed of light.
8. The method according to claim 7, wherein in step S600, the signal transmission time is adjusted to t-d/c according to the signal transmission delay, wherein t represents the signal transmission time before adjustment.
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