CN111294106A - Method and device for controlling off-axis equivalent radiation power of communication-in-motion satellite communication antenna - Google Patents
Method and device for controlling off-axis equivalent radiation power of communication-in-motion satellite communication antenna Download PDFInfo
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1853—Satellite systems for providing telephony service to a mobile station, i.e. mobile satellite service
- H04B7/18539—Arrangements for managing radio, resources, i.e. for establishing or releasing a connection
- H04B7/18543—Arrangements for managing radio, resources, i.e. for establishing or releasing a connection for adaptation of transmission parameters, e.g. power control
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1853—Satellite systems for providing telephony service to a mobile station, i.e. mobile satellite service
- H04B7/18545—Arrangements for managing station mobility, i.e. for station registration or localisation
- H04B7/18547—Arrangements for managing station mobility, i.e. for station registration or localisation for geolocalisation of a station
- H04B7/1855—Arrangements for managing station mobility, i.e. for station registration or localisation for geolocalisation of a station using a telephonic control signal, e.g. propagation delay variation, Doppler frequency variation, power variation, beam identification
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- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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Abstract
The invention discloses a method and a device for controlling off-axis equivalent radiation power of an airborne satellite communication antenna, wherein the method comprises the following steps: calculating an azimuth angle, a pitch angle and a polarization angle of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the synchronous satellite; obtaining off-axis gain of the current airborne satellite communication antenna along the orbit direction of the synchronous satellite according to the azimuth angle, the pitch angle and the polarization angle of the airborne satellite communication antenna, and taking the off-axis gain as along-orbit off-axis gain; obtaining distribution of off-axis equivalent power spectral density on a synchronous satellite orbit according to bandwidth of transmission service, power of a power amplifier and the along-track off-axis gain, and taking the distribution as the along-track off-axis equivalent power spectral density; and controlling the transmitting power of the airborne satellite communication antenna according to the equivalent power spectral density along the off-axis. The invention can ensure that the interference of the satellite antenna to the adjacent geostationary satellite is not easy to exceed the standard, and avoids the interference to the important service of the adjacent satellite.
Description
Technical Field
The invention relates to the technical field of satellite communication, in particular to a method and a device for controlling off-axis equivalent radiation power of a satellite communication antenna in communication in motion.
Background
Satellite communication is widely applied to mobile platforms such as vehicles, ships, airplanes and the like.
The beam of electromagnetic waves emitted by a satellite communication antenna is broad, as shown in figure 1. While the satellite antenna is aligned with the service satellite, the edge of the beam interferes with the adjacent satellite in the synchronous orbit, so that the noise floor is raised, as shown in fig. 2. If the interference exceeds national or operator standards, the satellite company or radio monitoring department manages and penalizes network entry for the satellite communication system.
For a small-sized satellite communication system in motion, in order to reduce the profile height, an antenna surface with a non-circular aperture or a phased array antenna with a flat plate is often used, and the aperture is small. In this case, its beam is generally wide, and the projected shape may be elliptical or other irregular shape. As shown in fig. 2, 1 is an elliptical beam, and 2 is a service satellite; 3 is the adjacent satellite that is interfered with; and 4 is a geostationary satellite orbit.
When the antenna moves in a wide range, the beam shape changes with the latitude and longitude, as shown in fig. 3. In fig. 3, 5 is the antenna optimum (satellite antenna is at the same longitude as the satellite); 6 is a case where the longitude of the antenna is different from that of the satellite; 7 is the case when some panel antennas have severely distorted beams when the latitude or longitude differences are too large.
Although the communication-in-motion antenna can generate different beam postures in a large-range movement, even beam distortion causes interference with satellites with different strengths, the power of the traditional communication-in-motion antenna is only adjusted according to the strength of a communication link. That is, the power is adjusted to ensure that the link is clear, and whether the interference to the adjacent satellite is over-standard or not is not considered.
As the most common example, a conventional airborne two-dimensional mechanically scanned low profile antenna has a long beam length axis due to the elongated rectangular antenna surface. When the latitude is lower than 20 degrees, the long axis of the antenna beam is basically coincident with the synchronous satellite orbit, the interference is huge, a plurality of satellites can be interfered, and the antenna generally needs to be turned off manually. Due to this inconvenience, cross-tropical flights are largely unable to use an airborne satellite broadband communication system.
Disclosure of Invention
The invention aims to provide a method and a device for controlling off-axis equivalent radiation power of a satellite communication antenna in motion. The method is used for solving the following technical problems:
aiming at the mobile satellite communication antenna with the beam form changing along with the geographical position, the transmission power of the mobile satellite communication antenna ensures that the interference of off-axis radiation to the adjacent synchronous orbit satellite is reduced to a controllable range, so that the situation that the interference to communication services on other satellites exceeds the standard is reduced.
According to one aspect of the invention, a method for controlling off-axis equivalent radiation power of an airborne satellite communication antenna is provided, which comprises the following steps:
calculating an azimuth angle, a pitch angle and a polarization angle of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the synchronous satellite;
obtaining off-axis gain of the current airborne satellite communication antenna along the orbit direction of the synchronous satellite according to the azimuth angle, the pitch angle and the polarization angle of the airborne satellite communication antenna, and taking the off-axis gain as along-orbit off-axis gain;
obtaining distribution of off-axis equivalent power spectral density on a synchronous satellite orbit according to bandwidth of transmission service, power of a power amplifier and the along-track off-axis gain, and taking the distribution as the along-track off-axis equivalent power spectral density;
and controlling the transmitting power of the airborne satellite communication antenna according to the equivalent power spectral density along the off-axis.
Preferably, the calculating the azimuth angle, the pitch angle and the polarization angle of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the geostationary satellite comprises:
obtaining the longitude phi 1 and the latitude β of the current airborne satellite communication antenna according to the current position of the airborne satellite communication antenna;
obtaining the longitude phi 2 of the synchronous satellite according to the known data of the synchronous satellite;
then, the longitude φ 1 and the latitude β of the current onboard satellite communication antenna and the longitude φ 2 of the geostationary satellite are used to calculate the onboard communication antenna azimuth A, the pitch angle E and the polarization angle P.
Preferably, the method can actually measure the azimuth angle a, the pitch angle E and the polarization angle P of the airborne satellite communication antenna and the corresponding off-axis gain in advance to obtain a corresponding relation table of the azimuth angle a, the pitch angle E and the polarization angle P of the airborne satellite communication antenna and the corresponding along-rail off-axis gain G (theta).
Preferably, the along-rail off-axis gain G (θ) is obtained by looking up the correspondence table.
Preferably, the along-axis off-axis equivalent power spectral density is obtained by:
EIRP_PSD(θ)＝G(θ)＊Pa/Bw
wherein. EIRP _ PSD is off-axis equivalent power spectral density, G (theta) is along-axis off-axis gain, Pa is power amplifier maximum power, and Bw is emission bandwidth.
Preferably, the method for controlling the transmitting power of the airborne satellite communication antenna according to the off-axis equivalent power spectral density along the orbit comprises the following steps: comparing the equivalent power spectral density along the off-axis with a related management standard to obtain a difference value L between the current equivalent power spectral density along the off-axis and the related management standard; and when the difference L is not a negative value, attenuating LdB the transmission power of the airborne satellite communication antenna.
According to another aspect of the present invention, there is provided an apparatus for controlling off-axis equivalent radiation power of a communication-in-motion satellite communication antenna, comprising:
the satellite antenna parameter calculation module is used for calculating an azimuth angle, a pitch angle and a polarization angle of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the synchronous satellite;
the along-track off-axis gain acquisition module is used for acquiring off-axis gain of the current airborne satellite communication antenna along the orbit direction of the synchronous satellite according to the azimuth angle, the pitch angle and the polarization angle of the airborne satellite communication antenna and taking the off-axis gain as along-track off-axis gain;
the system comprises an acquisition module of the equivalent power spectral density along the off-axis of the track, a power amplifier module and a gain module of the off-axis of the track, wherein the acquisition module is used for acquiring the distribution of the equivalent power spectral density on the synchronous satellite track according to the bandwidth of transmission service, the power of the power amplifier and the gain along the off-axis of the track, and taking the distribution as the equivalent power spectral density along the off-axis of;
and the airborne satellite communication antenna power control module is used for controlling the transmitting power of the satellite communication antenna according to the equivalent power spectral density along the off-axis.
Preferably, the calculating the azimuth angle, the pitch angle and the polarization angle of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the geostationary satellite comprises:
obtaining the longitude phi 1 and the latitude β of the current airborne satellite communication antenna according to the current position of the airborne satellite communication antenna;
obtaining the longitude phi 2 of the synchronous satellite according to the known data of the synchronous satellite;
then, the longitude φ 1 and the latitude β of the current onboard satellite communication antenna and the longitude φ 2 of the geostationary satellite are used for calculating the azimuth angle A, the pitch angle E and the polarization angle P of the onboard satellite communication antenna.
Preferably, the along-axis off-axis equivalent power spectral density is obtained by:
EIRP_PSD(θ)＝G(θ)＊Pa/Bw
wherein EIRP _ PSD is off-axis equivalent power spectral density, G (theta) is along-axis off-axis gain, Pa is power amplifier maximum power, and Bw is emission bandwidth.
Preferably, the onboard satellite communication antenna power control module includes:
a comparing unit for comparing the equivalent power spectral density along the off-axis with the related management standard to obtain the difference L between the current equivalent power spectral density along the off-axis and the related management standard
And the attenuation unit is used for attenuating LdB the transmitting power of the airborne satellite communication antenna when the difference L is not a negative value.
Compared with the prior art, the invention has the beneficial technical effects that:
1) compared with a satellite antenna without power upper limit, the method and the system can ensure that the interference of the satellite antenna to the adjacent stationary satellite is not easy to exceed the standard, avoid generating interference to the important service of the adjacent satellite and avoid management penalty caused by the interference.
2) Compared with manual setting of the upper power limit, the method and the device can be automatically adjusted according to the geographical position. If the upper power limit is manually set, the upper transmit power limit can only be designed according to the worst geographical position in a 'one-time' manner, so that the transmission signal is deteriorated if the upper power limit is greatly reduced. The method can allow a higher power upper limit when the antenna is in a better condition (such as the antenna and the satellite are at the same longitude), and ensure that the interference to the adjacent satellite does not exceed the standard.
The above-mentioned contents, actions and effects of the present invention will be described in detail with reference to the accompanying drawings:
drawings
FIG. 1 is an elliptical beam of an airborne satellite communications antenna;
FIG. 2 is a schematic diagram of a beam projection of a conventional airborne satellite antenna when interfered;
FIG. 3 is a schematic view of beam projections of a conventional airborne satellite antenna in three different situations;
FIG. 4 is a schematic diagram of a method for controlling off-axis equivalent radiation power of a communication-in-motion satellite communication antenna according to the present invention;
FIG. 5 is a schematic of the off-axis gain along the track obtained by the present invention;
FIG. 6 is an attempt at finding the difference L between the off-axis equivalent power spectral density along the rail and the associated regulatory standards, according to the present invention;
FIG. 7 is a schematic representation of the transmit power of the power airborne satellite communication antenna of the present invention;
FIG. 8 is a schematic diagram of an apparatus for controlling off-axis equivalent radiation power of a communication-in-motion satellite communication antenna according to the present invention;
fig. 9 is an electrical schematic of the onboard satellite communications antenna power control module of the present invention.
Detailed Description
Fig. 4 shows a method for controlling off-axis equivalent radiation power of a communication-in-motion satellite communication antenna according to the present invention, and as shown in fig. 4, the method for controlling off-axis equivalent radiation power of an airborne satellite communication antenna according to the present invention includes:
calculating an azimuth angle A, a pitch angle E and a polarization angle P of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the synchronous satellite;
according to the azimuth angle a, the pitch angle E and the polarization angle P of the airborne satellite communication antenna, obtaining off-axis gain of the current airborne satellite communication antenna along the orbit direction of the geostationary satellite, and taking the off-axis gain as along-axis off-axis gain G (θ), see fig. 5;
according to the bandwidth of transmission service, the power of a power amplifier and the along-track off-axis gain, obtaining the distribution of off-axis equivalent power spectral density on a synchronous satellite orbit, and taking the distribution as the along-track off-axis equivalent power spectral density EIRP _ PSD (theta);
and controlling the transmitting power of the airborne satellite communication antenna according to the equivalent power spectral density along the off-axis.
The method for calculating the azimuth angle, the pitch angle and the polarization angle of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the synchronous satellite comprises the steps of obtaining longitude phi 1 and latitude β of the current airborne satellite communication antenna according to the current position of the airborne satellite communication antenna, obtaining longitude phi 2 of the synchronous satellite according to known data of the synchronous satellite, and then calculating the azimuth angle A, the pitch angle E and the polarization angle P of the airborne satellite communication antenna by using the longitude phi 1 and the latitude β of the current airborne satellite communication antenna and the longitude phi 2 of the synchronous satellite.
The airborne communication antenna azimuth angle a, the pitch angle E and the polarization angle P may be calculated according to the following formulas:
wherein E is an antenna pitch angle, A is an antenna azimuth angle, P is an antenna polarization angle, phi 2 is satellite longitude, phi 1 is airborne satellite antenna longitude, and β is airborne satellite antenna latitude.
As an example of obtaining the off-axis gain G (θ), the azimuth a, the pitch angle E, the polarization angle P of the airborne satellite communication antenna and the corresponding off-axis gain may be actually measured in advance to obtain a corresponding relationship table of the azimuth a, the pitch angle E, the polarization angle P of the airborne satellite communication antenna and the corresponding off-axis gain G (θ). Thus, the along-track off-axis gain G (theta) can be obtained through a table look-up mode and a corresponding relation table of the azimuth A, the pitch angle E, the polarization angle P and the corresponding off-axis gain G (theta).
In addition, the invention can obtain the equivalent power spectral density along the off-axis of the track by the following formula:
EIRP_PSD(θ)＝G(θ)＊Pa/Bw
wherein EIRP _ PSD is off-axis equivalent power spectral density, G (theta) is along-axis off-axis gain, Pa is power amplifier maximum power, and Bw is emission bandwidth.
Furthermore, in one embodiment, controlling the transmit power of the airborne satellite communication antenna may include:
comparing the along-rail off-axis equivalent power spectral density with the relevant management standard to obtain a difference value L between the current along-rail off-axis equivalent power spectral density and the relevant management standard, see fig. 6;
when the difference L is not negative, the airborne satellite communication antenna transmission power is attenuated LdB, see fig. 7.
Fig. 8 shows an apparatus for controlling off-axis equivalent radiation power of a communication-in-motion satellite communication antenna according to the present invention, as shown in fig. 8, the apparatus includes:
the system comprises a recording satellite antenna parameter acquisition module and a tracking satellite antenna parameter acquisition module, wherein the recording satellite antenna parameter acquisition module is used for acquiring an antenna azimuth angle, a pitch angle and a polarization angle.
The control module calculates the azimuth angle, the pitch angle and the polarization angle of the antenna according to the longitude phi 1 and β of the airborne satellite antenna and the longitude phi 2 of the geostationary satellite, wherein the angle can be calculated by the following formula:
wherein E is an antenna pitch angle, A is an antenna azimuth angle, P is an antenna polarization angle, phi 2 is satellite longitude, phi 1 is airborne satellite antenna longitude, and β is airborne satellite antenna latitude.
An along-track off-axis gain obtaining module, configured to obtain an off-axis gain of the antenna along the geostationary satellite orbit direction at this time according to the azimuth, the pitch, and the polarization angle of the satellite communication antenna, which is hereinafter referred to as "along-track off-axis gain", referring to fig. 5.
The physical meaning of off-axis gain along the track is a set of data in which the gain G of the antenna varies along the geostationary satellite orbit according to the off-axis angle θ. There are two methods for calculating the off-axis gain along the track:
(1) table look-up mode: because the off-axis gain along the track is uniquely determined by the azimuth, the pitch and the polarization angle for the same frequency band of the same antenna, a database can be preset in the control module, and the off-axis gain tables corresponding to each azimuth, pitch and polarization angle are all measured and stored during manufacturing. When applied, the gain along the off-axis is obtained by looking up the table according to the azimuth, the pitch and the polarization angle.
(2) Approximate calculation: the along-track off-axis gain may be derived by an approximate calculation. For a rectangular mechanical antenna surface, the control module only stores an off-axis gain table of a long axis and a short axis of an antenna beam, and then according to the projection of the long axis and the short axis on the synchronous satellite orbit, the along-track off-axis gain can be obtained, and the approximate calculation is as follows:
g (θ) ═ G major axis (θ) + sin (p) × G minor axis (θ)
Where G (θ) is the on-axis gain in dBi. The major axis (theta) and the minor axis (theta) are arrays stored in the control module, and their values are measured or simulated after the antenna is designed or manufactured.
For other different types of antennas, the off-axis gain estimation method is applicable and belongs to the basic knowledge domain of general antenna engineers, and is not listed here.
And 3, an off-axis equivalent power spectral density acquisition module along the track, which is used for acquiring the distribution of the off-axis equivalent power spectral density on the synchronous satellite track according to the bandwidth of the transmission service and the power of the power amplifier, namely the off-axis equivalent power spectral density along the track.
EIRP_PSD(θ)＝G(θ)*Pa/Bw
Where EIRP PSD is the off-axis equivalent power spectral density in units of. G (theta) is along-track off-axis gain, Pa is power amplifier maximum power, and Bw is emission bandwidth.
4. And the airborne satellite communication antenna power control module is used for controlling the transmitting power of the satellite communication antenna according to the equivalent power spectral density along the off-axis.
Fig. 9 shows a specific circuit structure of the onboard satellite communication antenna power control module of the present invention, which includes:
and the comparison unit is used for comparing the equivalent power spectral density along the off-axis with the related management standard, and obtaining the difference L between the current equivalent power spectral density along the off-axis and the related management standard. See fig. 6.
The physical meaning of this difference L is: in order for the off-axis power transmitted by the current antenna to be below regulatory standards, the antenna transmission needs to be attenuated by that amount. If the value is negative, it indicates that the antenna is currently transmitting without attenuation.
L＝Max(EIRP_PSD(θ)-EIRP_PSDadmin(θ))
Wherein: l is the attenuation value in dB; EIRP _ PSD (theta) is off-axis equivalent power spectral density with the unit of dBW/40 kHz; EIRP _ PSDadmin (θ) is the envelope upper limit set by the administrator for off-axis equivalent power density, and is given in dBW/40 kHz. The EIRP _ PSDadmin may be a specification of radio management of a country, a specification of a satellite company, or a specification of an international power federation, etc., as needed.
In fig. 6, 8 is an off-axis equivalent power spectral density EIRP _ PSD of an antenna, 9 is an upper envelope of an off-axis equivalent power spectral density transmission, 10 is a difference therebetween, and a maximum value of the difference therebetween is an antenna transmission attenuation L.
And the attenuation unit is used for attenuating the emission of the antenna by L (dB) when the L is not a negative value.
The implementation mode can control an adjustable attenuator on a transmission path through a control module, or control a power amplifier with a power adjusting function, or control a signal modulator with programmable capability.
The attenuated off-axis equivalent radiation power is lower than the management requirement, and as shown in fig. 7, 11 in fig. 7 is the attenuated off-axis equivalent radiation power.
The above modules of the present invention can also be implemented by being integrated into one control module.
The invention has the advantages that: 1) compared with a satellite antenna without power upper limit, the method and the device can ensure that the interference of the satellite antenna to the adjacent stationary satellite is not easy to exceed the standard, avoid the interference to the important service of the adjacent satellite and the management penalty brought by the interference. 2) Compared with manual setting of the upper power limit, the method and the device can be automatically adjusted according to the geographical position. If the upper power limit is manually set, the upper transmit power limit can only be designed according to the worst geographical position in a 'one-time' manner, so that the transmission signal is deteriorated if the upper power limit is greatly reduced. The method can allow a higher power upper limit when the antenna is in a better condition (such as the antenna and the satellite are at the same longitude), and ensure that the interference to the adjacent satellite does not exceed the standard.
Although the present invention has been described in detail hereinabove, the present invention is not limited thereto, and various modifications can be made by those skilled in the art in light of the principle of the present invention. Thus, modifications made in accordance with the principles of the present invention should be understood to fall within the scope of the present invention.
Claims (10)
1. A method for controlling off-axis equivalent radiation power of an airborne satellite communication antenna comprises the following steps:
calculating an azimuth angle, a pitch angle and a polarization angle of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the synchronous satellite;
obtaining off-axis gain of the current airborne satellite communication antenna along the orbit direction of the synchronous satellite according to the azimuth angle, the pitch angle and the polarization angle of the airborne satellite communication antenna, and taking the off-axis gain as along-orbit off-axis gain;
obtaining distribution of off-axis equivalent power spectral density on a synchronous satellite orbit according to bandwidth of transmission service, power of a power amplifier and the along-track off-axis gain, and taking the distribution as the along-track off-axis equivalent power spectral density;
and controlling the transmitting power of the airborne satellite communication antenna according to the equivalent power spectral density along the off-axis.
2. The method of claim 1, wherein the calculating the azimuth, the pitch, and the polarization of the satellite communication antenna from the position of the on-board satellite communication antenna and the position of the geostationary satellite comprises:
obtaining the longitude phi 1 and the latitude β of the current airborne satellite communication antenna according to the current position of the airborne satellite communication antenna;
obtaining the longitude phi 2 of the synchronous satellite according to the known data of the synchronous satellite;
then, the longitude φ 1 and the latitude β of the current onboard satellite communication antenna and the longitude φ 2 of the geostationary satellite are used to calculate the onboard communication antenna azimuth A, the pitch angle E and the polarization angle P.
3. The method according to claim 1 or 2, wherein an azimuth angle a, a pitch angle E, a polarization angle P of the airborne satellite communication antenna and corresponding off-axis gains are actually measured in advance to obtain a corresponding relationship table of the azimuth angle a, the pitch angle E, the polarization angle P of the airborne satellite communication antenna and corresponding along-axis off-axis gains G (θ).
4. The method according to claim 1 or 2, wherein an approximate relation between the azimuth angle a, the pitch angle E, the polarization angle P of the airborne satellite communication antenna and the corresponding along-orbit off-axis gain G (θ) is obtained by actually measuring the azimuth angle a, the pitch angle E, the polarization angle P of the airborne satellite communication antenna and the corresponding off-axis gain in advance.
5. The method according to claim 3 or 4, wherein the along-axis and off-axis gains G (θ) are obtained by looking up the correspondence table or according to an approximate relation.
6. The method of claim 1 or 5, wherein controlling the transmit power of the onboard satellite communications antenna based on an along-axis off-axis equivalent power spectral density comprises:
comparing the equivalent power spectral density along the off-axis with a related management standard to obtain a difference value L between the current equivalent power spectral density along the off-axis and the related management standard;
and when the difference L is not a negative value, attenuating LdB the transmission power of the airborne satellite communication antenna.
7. An apparatus for controlling off-axis equivalent radiated power of a communication-in-motion satellite communication antenna, comprising:
the satellite antenna parameter calculation module is used for calculating an azimuth angle, a pitch angle and a polarization angle of the satellite communication antenna according to the position of the airborne satellite communication antenna and the position of the synchronous satellite;
the along-track off-axis gain acquisition module is used for acquiring off-axis gain of the current airborne satellite communication antenna along the orbit direction of the synchronous satellite according to the azimuth angle, the pitch angle and the polarization angle of the airborne satellite communication antenna and taking the off-axis gain as along-track off-axis gain;
the system comprises an acquisition module of the equivalent power spectral density along the off-axis of the track, a power amplifier module and a gain module of the off-axis of the track, wherein the acquisition module is used for acquiring the distribution of the equivalent power spectral density on the synchronous satellite track according to the bandwidth of transmission service, the power of the power amplifier and the gain along the off-axis of the track, and taking the distribution as the equivalent power spectral density along the off-axis of;
and the airborne satellite communication antenna power control module is used for controlling the transmitting power of the satellite communication antenna according to the equivalent power spectral density along the off-axis.
8. The apparatus of claim 8, wherein the calculating of the azimuth, the pitch, and the polarization of the satellite communication antenna from the position of the on-board satellite communication antenna and the position of the geostationary satellite comprises:
obtaining the longitude phi 1 and the latitude β of the current airborne satellite communication antenna according to the current position of the airborne satellite communication antenna;
obtaining the longitude phi 2 of the synchronous satellite according to the known data of the synchronous satellite;
then, the longitude φ 1 and the latitude β of the current onboard satellite communication antenna and the longitude φ 2 of the geostationary satellite are used for calculating the azimuth angle A, the pitch angle E and the polarization angle P of the onboard satellite communication antenna.
9. The device according to claim 7 or 8, wherein an azimuth angle a, a pitch angle E, a polarization angle P of the airborne satellite communication antenna and a corresponding off-axis gain are actually measured in advance to obtain a corresponding relation table or an approximate relation expression of the azimuth angle a, the pitch angle E, the polarization angle P of the airborne satellite communication antenna and a corresponding along-axis off-axis gain G (θ).
10. The apparatus of claim 7 or 9, wherein the onboard satellite communication antenna power control module comprises:
a comparing unit for comparing the equivalent power spectral density along the off-axis with the related management standard to obtain the difference L between the current equivalent power spectral density along the off-axis and the related management standard
And the attenuation unit is used for attenuating LdB the transmitting power of the airborne satellite communication antenna when the difference L is not a negative value.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112531350A (en) * | 2021-02-07 | 2021-03-19 | 星展测控科技股份有限公司 | Phased array antenna, communication device and communication-in-motion equipment |
| CN112881791A (en) * | 2021-01-19 | 2021-06-01 | 中国电子科技集团公司第二十九研究所 | Method for calculating transmitting power of unknown ground radiation source through pitch angle and azimuth angle |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102565828A (en) * | 2012-01-07 | 2012-07-11 | 中国科学院国家授时中心 | Method for reducing signal emitting power of satellite navigation and positioning system |
| US9124342B2 (en) * | 2011-03-10 | 2015-09-01 | Comtech Ef Data Corp. | Method for the control of a wireless communications link for mitigating adjacent satellite interference |
| WO2015156886A2 (en) * | 2014-01-27 | 2015-10-15 | Lemme Peter | System and method for communicating via a satellite in an inclined geosynchronous orbit |
| US20160073359A1 (en) * | 2011-12-21 | 2016-03-10 | Comtech Ef Data Corp. | Method and System for Controlling a Communications Carrier's Power Spectral Density (PSD) Using Spread Spectrum for Matched Spectral Allocation |
| CN105578409A (en) * | 2015-12-18 | 2016-05-11 | 航天恒星科技有限公司 | Terminal emission power adjusting method based on multi-beam satellite communication system |
| CN107342804A (en) * | 2016-04-28 | 2017-11-10 | 北京大学 | Suppress the method for adjacent star interference in satellite communication system |
| CN107395299A (en) * | 2017-07-03 | 2017-11-24 | 北京邮电大学 | A kind of 450MHz band satellites weather service and the interference analysis method of railway train adjusting system |
| CN108494469A (en) * | 2018-02-02 | 2018-09-04 | 北京国电高科科技有限公司 | A kind of communication means of downlink for data gathering system load |
-
2018
- 2018-12-06 CN CN201811483406.4A patent/CN111294106B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9124342B2 (en) * | 2011-03-10 | 2015-09-01 | Comtech Ef Data Corp. | Method for the control of a wireless communications link for mitigating adjacent satellite interference |
| US20160073359A1 (en) * | 2011-12-21 | 2016-03-10 | Comtech Ef Data Corp. | Method and System for Controlling a Communications Carrier's Power Spectral Density (PSD) Using Spread Spectrum for Matched Spectral Allocation |
| CN102565828A (en) * | 2012-01-07 | 2012-07-11 | 中国科学院国家授时中心 | Method for reducing signal emitting power of satellite navigation and positioning system |
| WO2015156886A2 (en) * | 2014-01-27 | 2015-10-15 | Lemme Peter | System and method for communicating via a satellite in an inclined geosynchronous orbit |
| CN105578409A (en) * | 2015-12-18 | 2016-05-11 | 航天恒星科技有限公司 | Terminal emission power adjusting method based on multi-beam satellite communication system |
| CN107342804A (en) * | 2016-04-28 | 2017-11-10 | 北京大学 | Suppress the method for adjacent star interference in satellite communication system |
| CN107395299A (en) * | 2017-07-03 | 2017-11-24 | 北京邮电大学 | A kind of 450MHz band satellites weather service and the interference analysis method of railway train adjusting system |
| CN108494469A (en) * | 2018-02-02 | 2018-09-04 | 北京国电高科科技有限公司 | A kind of communication means of downlink for data gathering system load |
Non-Patent Citations (2)
| Title |
|---|
| VIJITHA WEERACKODY，ETC.: "A statistical approach to specifying the off-axis EIRP spectral density in on-the-move satellite communications", 《MILCOM 2008 - 2008 IEEE MILITARY COMMUNICATIONS CONFERENCE》 * |
| 贾玉仙，等: "相邻卫星转发干扰计算方法的研究", 《数字通信世界》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112881791A (en) * | 2021-01-19 | 2021-06-01 | 中国电子科技集团公司第二十九研究所 | Method for calculating transmitting power of unknown ground radiation source through pitch angle and azimuth angle |
| CN112881791B (en) * | 2021-01-19 | 2023-05-09 | 中国电子科技集团公司第二十九研究所 | Method for calculating unknown ground radiation source transmitting power through pitch angle and azimuth angle |
| CN112531350A (en) * | 2021-02-07 | 2021-03-19 | 星展测控科技股份有限公司 | Phased array antenna, communication device and communication-in-motion equipment |
| CN112531350B (en) * | 2021-02-07 | 2021-05-25 | 星展测控科技股份有限公司 | Phased array antenna, communication device and communication-in-motion equipment |
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