CN115580333A - Geostationary orbit satellite space-ground integrated measurement and control system and method - Google Patents
Geostationary orbit satellite space-ground integrated measurement and control system and method Download PDFInfo
- Publication number
- CN115580333A CN115580333A CN202211109583.2A CN202211109583A CN115580333A CN 115580333 A CN115580333 A CN 115580333A CN 202211109583 A CN202211109583 A CN 202211109583A CN 115580333 A CN115580333 A CN 115580333A
- Authority
- CN
- China
- Prior art keywords
- control
- measurement
- ground
- switch
- receiving
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
- H04B7/1851—Systems using a satellite or space-based relay
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- 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
Abstract
The invention provides a geostationary orbit satellite space-ground integrated measurement and control system and a method, which comprise a space-ground integrated measurement and control device, wherein measurement and control communication is carried out by adjusting the space-ground integrated measurement and control device, and the measurement and control communication mode comprises quasi-omnidirectional communication to a relay satellite, quasi-omnidirectional communication to a ground system or power consumption reduction communication to the ground system. The relay measurement and control method reduces the resource overhead such as the relay measurement and control weight and power consumption of the geostationary orbit satellite, and improves the use efficiency of the relay measurement and control of the geostationary orbit satellite; the antenna switching multiplexing of ground measurement and control and relay measurement and control is realized, and the quasi-omnidirectional coverage of ground measurement and control and relay measurement and control is realized.
Description
Technical Field
The invention relates to the technical field of fusion design of a relay measurement and control function and a ground measurement and control function of a geostationary orbit satellite, in particular to a geostationary orbit satellite space-ground integrated measurement and control system and a method.
Background
Compared with the measurement and control on the ground, the relay measurement and control has the technical advantage of long tracking arc section, and can be used for measurement and control tasks in stages of civil satellite launching, in-orbit and the like. The geostationary orbit satellite adopts a relay tracking mode of a ground measurement and control station and a measuring ship in a launching active section, and can adopt relay measurement and control to reduce a marine measurement and control blind area. The orbit heights of the geostationary orbit satellite and the relay satellite are the same, and the geostationary orbit satellite and the relay satellite cannot carry out forwarding communication after fixed-point positioning; meanwhile, the geostationary orbit satellite can continuously communicate with the ground after fixed-point positioning, and the relay satellite is not required to be used for forwarding communication.
Chinese patent publication No. CN107332605A discloses a measurement and control method based on a Ka-S frequency band relay integrated measurement and control system, which adopts dual antennas to realize omnidirectional relay measurement and control coverage to the sky and the ground, and adopts a design scheme of Ka-S dual frequency bands.
Chinese patent publication No. CN107959526A discloses a space-ground based integrated measurement and control system applied to near-earth space, wherein different antennas are used for receiving different signals for ground measurement and control and space-ground based measurement and control, and the system is suitable for an aircraft in near-earth space.
The Chinese patent invention with the publication number of CN102333057A discloses a micro/nano satellite measurement and control communication integrated transceiver system and an implementation method thereof, which implement the processing flow of uplink reception and downlink transmission, and do not relate to the implementation scheme of ground measurement and control and relay measurement and control.
Chinese patent publication No. CN111679300A discloses a LEO-HEO multi-orbit satellite measurement and control system and method, where the LEO-HEO multi-orbit satellite measurement and control system includes an orbit measurement module, a first telemetry module, a second telemetry module, and a remote control module, where: the gauging track module is configured to measure the way that the track is measured by USB and combined with GNSS; the remote control module is configured to realize global beam coverage by combining two measurement and control transmitting and receiving antennas and receive remote control signals in all orbital operation stages; the first telemetry module is configured to realize global beam coverage by combining two measurement and control transmitting and receiving antennas, and transmit low-power telemetry signals in an LEO track and an early stage of track transfer; the second telemetry module is configured to be in a single antenna transmission mode to achieve hemispherical beam coverage, time-sharing global beam coverage is achieved through switching of the two measurement and control transmission antennas, and high-power telemetry signals are transmitted in the later stage of orbital transfer and the HEO orbit.
For the above related technologies, the inventor considers that the relay measurement and control of the geostationary orbit satellite has high resource overhead such as weight and power consumption, and the relay measurement and control of the geostationary orbit satellite has low use efficiency.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a geostationary orbit satellite space-ground integrated measurement and control system and a method.
The invention provides a geostationary orbit satellite earth-ground integrated measurement and control system, which comprises an earth-ground integrated measurement and control device; the measurement and control communication is carried out by adjusting the space-ground integrated measurement and control device, and the measurement and control communication mode comprises quasi-omnidirectional communication to a relay satellite, quasi-omnidirectional communication to a ground system or power consumption reduction communication to the ground system.
Preferably, the integrated space-ground measurement and control device comprises a first receiving antenna, a first receiving microwave switch, a first transponder, a first transmitting microwave switch, a first power amplifier, a position switch and a first transmitting antenna;
the first receiving antenna is connected with the master control position of the first receiving microwave switch;
the first control position of the first microwave receiving switch is connected with a relay receiving channel of a first transponder;
the relay transmitting channel of the first transponder is connected with the first control position of the first microwave transmitting switch;
the master control position of the first transmitting microwave switch is connected with the input port of the first power amplifier;
the output port of the first power amplifier is connected with the fourth port of the position switch;
and the third port of the position switch is connected with the first transmitting antenna.
Preferably, the integrated space-ground measurement and control device further comprises a second transmitting antenna;
and the first port of the position switch is connected with the second transmitting antenna.
Preferably, the integrated space-ground measurement and control device further comprises a second receiving antenna, a second receiving microwave switch, a second transponder, a second transmitting microwave switch and a second power amplifier;
the second receiving antenna is connected with the master control position of the second receiving microwave switch;
the first control position of the second microwave receiving switch is connected with a relay receiving channel of a second transponder;
the relay transmitting channel of the second transponder is connected with the first control position of the second microwave transmitting switch;
the master control position of the second transmitting microwave switch is connected with the input port of the second power amplifier;
and the output port of the second power amplifier is connected with the second port of the position switch.
Preferably, the integrated space-ground measurement and control device further comprises a receiving combined power divider;
the second control position of the first microwave receiving switch is connected with the first port of the receiving combiner power divider;
the third port of the receiving combined power divider is connected with a ground receiving channel of the first responder;
the fourth port of the receiving combiner power divider is connected with a ground receiving channel of a second transponder;
the ground transmitting channel of the first transponder is connected with the second control position of the first microwave transmitting switch; (ii) a
The ground transmitting channel of the second transponder is connected with the second control position of the second transmitting microwave switch.
Preferably, the second control position of the second microwave receiving switch is connected to the second port of the receiving combiner power divider.
Preferably, the mode of measurement and control communication further comprises communicating to the relay satellite and to the ground system simultaneously.
The invention provides a geostationary orbit satellite space-ground integrated measurement and control method, which applies a geostationary orbit satellite space-ground integrated measurement and control system and comprises the following steps:
the construction steps are as follows: constructing a space-ground integrated measurement and control device;
the measurement and control steps are as follows: and adjusting the space-ground integrated measurement and control device, and carrying out measurement and control communication according to the adjusted space-ground integrated measurement and control device.
Preferably, in the measurement and control step, the measurement and control communication mode includes quasi-omnidirectional communication to a relay satellite, quasi-omnidirectional communication to a ground system, or power consumption reduction communication to the ground system.
Preferably, in the measurement and control step, the mode of measurement and control communication further includes communicating to the relay satellite and to the ground system simultaneously.
Compared with the prior art, the invention has the following beneficial effects:
1. the relay measurement and control method reduces the resource overhead such as the relay measurement and control weight and power consumption of the geostationary orbit satellite, and improves the use efficiency of the relay measurement and control of the geostationary orbit satellite;
2. the invention switches and multiplexes the ground measurement and control antenna and the relay measurement and control antenna, and realizes quasi-omnidirectional coverage of the ground measurement and control antenna and the relay measurement and control antenna;
3. the invention simultaneously realizes the quasi-omnidirectional coverage of satellite-ground measurement and control and relay measurement and control, and is a measurement and control scheme suitable for a static orbit satellite.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a diagram of a quasi-omnidirectional communication working mode of a relay satellite (a relay measurement and control functional diagram of a space-ground integrated measurement and control system);
FIG. 2 is a diagram of a communication operation mode of a-Z-direction to relay satellite and a + Z-direction to ground system;
FIG. 3 is a diagram of a-Z-direction ground-to-ground system and + Z-direction relay satellite communication operation mode;
FIG. 4 is a diagram of quasi-omnidirectional communication of a ground system (a diagram of a ground measurement and control function of a space-ground integrated measurement and control system) for space-ground integrated measurement and control;
fig. 5 is a communication diagram for reducing power consumption of a ground system.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will aid those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any manner. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The embodiment of the invention discloses a geostationary orbit satellite space-ground integrated measurement and control system, which comprises a space-ground integrated measurement and control device and is used for carrying out measurement and control communication through the adjusted space-ground integrated measurement and control device, as shown in figure 1. The modes of the measurement and control communication comprise quasi-omnidirectional communication to the relay satellite, quasi-omnidirectional communication to the ground system, power consumption reduction communication to the ground system, or communication to the relay satellite and the ground system at the same time.
The heaven-earth integrated measurement and control device comprises a heaven-earth integrated responder A (a first responder), a heaven-earth integrated responder B (a second responder), an R combining power divider, a T microwave switch A (a first transmitting microwave switch), a T microwave switch B (a second transmitting microwave switch), an R microwave switch A (a first receiving microwave switch), an R microwave switch B (a second receiving microwave switch), a power amplifier A (a first power amplifier), a power amplifier B (a second power amplifier), a position switch, a first transmitting antenna (Tant 1), a second transmitting antenna (Tant 2), a first receiving antenna (Rant 1) and a second receiving antenna (Rant 2).
Tant1 represents a satellite-Z-direction measurement and control transmitting antenna; tant2 represents a satellite + Z-direction measurement and control transmitting antenna; the Rant1 represents a satellite-Z-direction measurement and control receiving antenna; the Rant2 represents a satellite + Z-direction measurement and control receiving antenna; ADT represents a ground measurement and control transmitting channel (ground transmitting channel) of the heaven-earth integrated transponder A; ADR represents a ground measurement and control receiving channel (ground receiving channel) of the heaven-earth integrated transponder A; AZT represents a relay measurement and control return channel (relay transmitting channel) of the heaven-earth integrated transponder A; AZR represents a relay measurement and control forward channel (relay receiving channel) of a heaven-earth integrated transponder A; the BDT represents a space-ground integrated transponder B to ground measurement and control transmitting channel (a ground transmitting channel); the BDR represents a space-ground integrated transponder B to ground measurement and control receiving channel (ground receiving channel); BZT represents a relay measurement and control return channel (relay transmitting channel) of a heaven-earth integrated responder B; the BZR represents a relay measurement and control forward channel (relay receiving channel) of a heaven-earth integrated responder B; r microwave switch denotes a receiving microwave switch; t microwave switch denotes a transmitting microwave switch; the R-combiner power divider represents a receiving-combiner power divider.
A relay receiving channel of the first responder is connected with a first control position of a first microwave receiving switch; a relay transmitting channel of the first transponder is connected with a first control position of the first microwave transmitting switch; the ground transmitting channel of the first transponder is connected with the second control position of the first microwave transmitting switch; the ground receiving channel of the first transponder is connected with a third port of the receiving combiner power divider; the second control position of the first microwave receiving switch is connected with the first port of the receiving combiner power divider; the master control position of the first microwave receiving switch is connected with a first receiving antenna; the master control position of the first transmitting microwave switch is connected with the input port of the first power amplifier; the output port of the first power amplifier is connected with the fourth port of the position switch; a second port of the receiving combined power divider is connected with a second control position of a second receiving microwave switch; the fourth port of the receiving combiner power divider is connected with a ground receiving channel of the second transponder; the third port of the position switch is connected with the first transmitting antenna; the first port of the position switch is connected with the second transmitting antenna; the second port of the position switch is connected with the output port of the second power amplifier; the input port of the second power amplifier is connected with the master control position of the second transmitting microwave switch; the first control position of the second microwave transmitting switch is connected with a relay transmitting channel of the second transponder; the second control position of the second microwave transmitting switch is connected with the earth transmitting switch of the second transponder; the master control position of the second microwave receiving switch is connected with a second receiving antenna; the first control position of the second microwave receiving switch is connected with the relay receiving channel of the second transponder.
Namely: the first receiving antenna is connected with the master control position of the first receiving microwave switch; the first control position of the first microwave receiving switch is connected with a relay receiving channel of the first transponder; the relay transmitting channel of the first transponder is connected with the first control position of the first microwave transmitting switch; the master control position of the first transmitting microwave switch is connected with the input port of the first power amplifier; the output port of the first power amplifier is connected with the fourth port of the position switch; and the third port of the position switch is connected with the first transmitting antenna.
The first port of the position switch is connected with the second transmitting antenna.
The second receiving antenna is connected with the master control position of the second receiving microwave switch; the first control position of the second microwave receiving switch is connected with a relay receiving channel of the second transponder; the relay transmitting channel of the second transponder is connected with the first control position of the second microwave transmitting switch; the master control position of the second transmitting microwave switch is connected with the input port of the second power amplifier; the output port of the second power amplifier is connected with the second port of the position switch.
The second control position of the first microwave receiving switch is connected with the first port of the receiving combiner power divider; a third port of the receiving combined power divider is connected with a ground receiving channel of the first responder; the fourth port of the receiving combined power divider is connected with a ground receiving channel of the second responder; the ground transmitting channel of the first transponder is connected with the second control position of the first microwave transmitting switch; the ground transmission channel of the second transponder is connected to the second control position of the second transmitting microwave switch.
And the second control position of the second microwave receiving switch is connected with the second port of the receiving combiner power divider.
The all-in-one transponder configuration: a geostationary orbit satellite earth-ground integrated measurement and control system is provided with two earth-ground integrated transponders, adopts an incoherent spread spectrum system, and meets the standard requirements of earth measurement and control and relay measurement and control. The relay receiving sensitivity and the ground receiving sensitivity meet the requirements of the uplink on the satellite and the forward link between the satellites; the relay transmit power and the ground transmit power are both 0dBm ± 2dB.
The relay measurement and control pseudo code rate is 3.069Mcps, and the relay measurement and control pseudo code rate has the functions of forward remote control receiving and backward remote control sending; both the remote control code rate and the telemetry code rate can be set according to the link condition with the relay satellite. The ground measurement and control pseudo code rates of 3.069Mcps and 10.23Mcps can be set, the ground measurement and control pseudo code rate can be set, the functions of ground remote control, remote measurement and distance measurement are realized, the remote control code rate and the remote measurement code rate can be set according to the link condition with a ground station, and the distance measurement code rate is fixed to 1000bps; the ground measurement and control has a high-speed upper injection function.
Microwave switch and position switch configuration: the T microwave switch is used for realizing the switching of relay transmission and ground transmission, and has two position switching states: position I and position II. The position I is connected with the relay transmitting channel of the integrated transponder, and the position II is connected with the ground transmitting channel of the integrated transponder. The input of the T microwave switch is 0dBm +/-2 dB low-power signals, the switching function is realized by adopting a common microwave switch, and the channel difference loss is less than 0.5dB. The R microwave switch is used for realizing the switch switching of relay receiving and ground receiving, and has two position switching states: position I and position II. The position I is connected with the relay receiving channel of the integrated responder, and the position II is connected with the ground receiving channel of the integrated responder. The input of the T microwave switch is a low-power signal, the switching function is realized by adopting a common microwave switch, and the channel difference loss is less than 0.5dB.
The position switch is used for realizing the cross switching of the integrated transponder A and the integrated transponder B and the coverage of the satellite in the Z direction and the Z direction, and has two position switching states: positions J1-J2& J3-J4 and positions J1-J4& J2-J3. Positions J1-J2& J3-J4: the transmitting channel of the integrated transponder A is connected with a-Z-direction transmitting antenna Tant1, and the transmitting channel of the integrated transponder B is connected with a + Z-direction transmitting antenna Tant2. Positions J1-J4& J2-J3: the transmitting channel of the integrated transponder A is connected with a + Z-direction transmitting antenna Tant2, and the transmitting channel of the integrated transponder B is connected with a-Z-direction transmitting antenna Tant 1. The input of the position switch is a 43dBm high-power signal, the switching function is realized by adopting a coaxial high-power microwave switch, and the channel difference loss is less than 0.5dB.
20W power amplifier configuration: a geostationary orbit satellite space-ground integrated measurement and control system adopts an S frequency band, and a power amplifier configuration frequency band simultaneously meets the requirements of relay measurement and control and ground measurement and control, so that the 20W power amplifier bandwidth requirement covers 2200 MHz-2300 MHz, the in-band gain change is less than 1dB, and harmonic wave and clutter suppression meet the system design requirement. According to the resource overhead conditions of measuring and controlling system power consumption, heat consumption and the like, a GaN power tube and a GaAs power tube can be selected.
Configuring a combining power divider: because the relay measurement and control link margin is insufficient, the relay transmitting channel and the relay receiving channel are not provided with the combined path power divider.
The R combining power divider is used for realizing the combining and power dividing functions of a-Z-direction receiving antenna Rant1 and a + Z-direction receiving antenna Rant2, so that the integrated transponder A and the integrated transponder B can simultaneously receive uplink signals of the + Z-direction antenna and the-Z-direction antenna, and finally quasi-omnidirectional coverage of the ground system by the dual heat engines on the uplink signals is realized.
The R-path power divider may be eliminated according to the complexity of the system configuration.
Configuration of a measurement and control antenna: according to the requirement of relay specifications, forward left-handed circular polarized signals and backward right-handed circular polarized signals of a generation of relay system; the measurement and control of the ground support the left-right circular polarization at the same time. A geostationary orbit satellite earth-earth integrated measurement and control system combines functions of an earth antenna and a relay antenna, so that a left-hand circularly polarized receiving antenna and a right-hand circularly polarized transmitting antenna are configured, and meanwhile, in order to meet the requirement of quasi-omnidirectional coverage, receiving antennas Rant1 and Rant2 and transmitting antennas Tant1 and Tant2 are distributed in the Z direction and the + Z direction of a satellite. The frequency range of the measurement and control receiving antenna is 2025 MHz-2100 MHz, the gain within the wave beam width +/-86 degrees is more than or equal to-5 dBi, and the axial ratio is less than or equal to 5.2dB; the frequency range of the measurement and control transmitting antenna is 2200-2300 MHz, the internal gain of the wave beam width +/-86 degrees is more than or equal to-5 dBi, the internal gain of +/-70 degrees is more than or equal to 1dBi, and the axial ratio is less than or equal to 5.2dB.
A geostationary orbit satellite space-ground integrated measurement and control system is characterized in that a relay measurement and control forward channel is switched with a ground measurement and control receiving channel, and a relay measurement and control return channel is switched with a ground measurement and control transmitting channel. The relay measurement and control has the capability of quasi-omnidirectional coverage. The relay measurement and control function and the ground measurement and control function adopt a time sharing and transmitting and receiving separated mode so as to reduce the weight of the system. The relay measurement and control return channel power amplifier and the ground measurement and control transmitting channel power amplifier adopt a time-sharing mode so as to reduce the power consumption of the system. The power amplifier A is connected with the satellite-Z direction measurement and control transmitting antenna Tant1, and the power amplifier B is connected with the satellite + Z direction measurement and control transmitting antenna Tant2, and the connection relation can be switched through the position switch. The satellite + Z-direction relay measurement and control coverage is realized by combining the space-ground integrated transponder A and the measurement and control antenna, and the satellite-Z-direction relay measurement and control coverage is realized by combining the space-ground integrated transponder B and the measurement and control antenna. Switching a relay measurement and control forward channel and a ground measurement and control receiving channel by adopting an R microwave switch, and switching a relay measurement and control return channel and a ground measurement and control telemetering transmitting channel by adopting a T microwave switch; the relay measurement and control adopts a position switch to switch the connection relation between the integrated transponder A and the integrated transponder B and the + Z-direction transmitting antenna and the-Z-direction transmitting antenna. And the R combined path power divider is adopted to realize quasi-omnidirectional signal receiving of the single integrated transponder to the ground system in the satellite + Z direction and the-Z direction.
The embodiment of the invention also provides a geostationary orbit satellite space-ground integrated measurement and control method, as shown in fig. 1, comprising the following steps: the construction steps are as follows: and constructing a space-ground integrated measurement and control device. Measurement and control steps: and adjusting the heaven-earth integrated measurement and control device, and carrying out measurement and control communication according to the adjusted heaven-earth integrated measurement and control device. The modes of the measurement and control communication comprise quasi-omnidirectional communication to a relay satellite, quasi-omnidirectional communication to a ground system or power consumption reduction communication to the ground system. The mode of measurement and control communication also includes simultaneous communication to relay satellites and ground systems.
The invention can realize 5 typical measurement and control communication modes on the premise of not reducing the reliability of the system.
As shown in fig. 1, mode 1: quasi-omni communication to a relay satellite.
Step 1.1, open-day and open-place integrated responder: the heaven and earth integrated responder A is started and the heaven and earth integrated responder B is started.
Step 1.2, switching the-Z direction into a relay transmitting channel: t microwave switch a switches position J1.
Step 1.3, switching the + Z direction into a relay transmitting channel: t microwave switch B switches position J1.
Step 1.4, switching to-Z-direction relay and + Z-direction relay transmission: the position switch is switched from J1-J2 to J3-J4; -represents a connection, & represents a sum.
Step 1.5, starting up a power amplifier: the 20W power amplifier A is started, and the 20W power amplifier B is started.
Step 1.6, the transponder transmitter: the transmitter of the heaven and earth integrated transponder A is started, and the transmitter of the heaven and earth integrated transponder B is started.
Step 1.7, switching to a relay receiving channel from-Z direction: r microwave switch a cuts position J1.
Step 1.8: switching to the relay receiving channel from the + Z direction: r microwave switch B cuts position J1.
As shown in fig. 2, mode 2: -Z-direction to relay satellite and + Z-direction to ground system communication.
Step 2.1, starting up the answering machine: the heaven and earth integrated responder A is started and the heaven and earth integrated responder B is started.
Step 2.2, switching to a relay transmitting channel from the-Z direction: t microwave switch a switches position J1.
Step 2.3, + Z to switch to the earth transmission channel: t microwave switch B cuts position J2.
Step 2.4, switching to-Z-direction relay and + Z-direction ground transmission: the position switch switches J1-J2& J3-J4.
Step 2.5, starting the power amplifier: the 20W power amplifier A is started, and the 20W power amplifier B is started.
Step 2.6, the transponder transmitter: the transmitter of the heaven and earth integrated transponder A is started, and the transmitter of the heaven and earth integrated transponder B is started.
Step 2.7: -switching to relay receive channel in Z direction: r microwave switch a cuts position J1.
Step 2.8: the + Z direction is switched to the ground receiving channel: r microwave switch B cuts position J2.
As shown in fig. 3, mode 3: -Z-to-ground system and + Z-to-relay satellite communications.
Step 3.1, starting up the answering machine: the heaven and earth integrated responder A is started, and the heaven and earth integrated responder B is started.
Step 3.2, -Z direction switching to a ground transmitting channel: t microwave switch a switches position J2.
Step 3.3, switching the + Z direction into a relay transmitting channel: t microwave switch B cuts position J1.
And 3.4, switching to-Z direction ground and + Z direction relay transmission: the position switch switches J1-J2& J3-J4.
Step 3.5, starting the power amplifier: the 20W power amplifier A is started, and the 20W power amplifier B is started.
Step 3.6, the transponder transmitter: the transmitter of the heaven and earth integrated transponder A is started, and the transmitter of the heaven and earth integrated transponder B is started.
Step 3.7: -switching to the ground reception channel in the Z direction: r microwave switch a switches position J2.
Step 3.8: switching to the relay receiving channel from the + Z direction: r microwave switch B cuts position J1.
As shown in fig. 4, mode 4: and carrying out quasi-omnidirectional communication on the ground system.
Step 4.1, starting up the answering machine: the heaven and earth integrated responder A is started and the heaven and earth integrated responder B is started.
Step 4.2, switching the-Z direction into a ground transmitting channel: t microwave switch a switches position J2.
Step 4.3, + Z to switch to the ground transmission channel: t microwave switch B cuts position J2.
And 4.4, switching to-Z direction ground and + Z direction ground transmission: the position switch switches J1-J2& J3-J4.
Step 4.5, starting the power amplifier: the 20W power amplifier A is started, and the 20W power amplifier B is started.
Step 4.6, the transponder transmitter: the transmitter of the heaven and earth integrated transponder A is started, and the transmitter of the heaven and earth integrated transponder B is started.
Step 4.7: -switching to the ground reception channel in the Z direction: r microwave switch a switches position J2.
Step 4.8: the + Z direction is switched to the ground receiving channel: r microwave switch B cuts position J2.
As shown in fig. 5, mode 5: and reducing power consumption of the ground system for communication.
Step 5.1, starting up the answering machine: the heaven and earth integrated responder A is started and the heaven and earth integrated responder B is started.
Step 5.2, -Z direction is switched into a ground transmitting channel: t microwave switch a switches position J2.
Step 5.3, + Z to switch to the ground transmission channel: t microwave switch B switches position J2.
And 5.4, switching to-Z direction ground and + Z direction ground transmission: the position switch switches J1-J2& J3-J4. There are only two switching modes, adjacent switching: 1. J1-J2& J3-J4; 2. J1-J4& J2-J3.
Step 5.5, the power amplifier A is powered off, and the power amplifier B is powered on: and the 20W power amplifier A is powered off, and the 20W power amplifier B is powered on. Or the power amplifier A is started and the power amplifier B is shut down by matching with a position switch.
Step 5.6, opening the transponder transmitter: the heaven and earth integrated transponder A transmitter is closed, and the heaven and earth integrated transponder B transmitter is opened.
Step 5.7: -switching to the ground reception channel in the Z direction: r microwave switch a switches position J2.
Step 5.8: the + Z direction is switched to the ground receiving channel: r microwave switch B cuts position J2.
The relay measurement and control method solves the problems of high resource overhead such as weight, power consumption and the like of relay measurement and control of the geostationary orbit satellite, and solves the problem of low use efficiency of relay measurement and control of the geostationary orbit satellite. Therefore, the geostationary orbit satellite provides a task requirement of a space-ground integrated measurement and control system, and requires to combine the radio frequency front ends of the measurement and control channel and the ground measurement and control channel, and reduce resource overhead such as system weight, power consumption and the like.
A geostationary orbit satellite space-ground integrated measurement and control system carries out fusion design on relay measurement and control and ground measurement and control. According to the satellite flight orbit and the tracking condition of the ground measurement and control station, the satellite affair software judges the invisible arc section of the ground measurement and control station, and sends a program control instruction to switch the microwave switch to a relay measurement and control channel; the space-ground integrated transponder A realizes the functions of satellite-Z plane relay satellite remote control receiving and remote measurement sending; the space-ground integrated transponder B realizes the functions of satellite + Z-oriented relay satellite remote control receiving and remote measurement sending; the relay measurement and control channel combination of the antenna integrated transponder A and the sky-ground integrated transponder B realizes the quasi-omnidirectional relay measurement and control function of the satellite. When the satellite affair software judges that the ground measurement and control arc section is in, a geostationary orbit satellite heaven-earth integrated measurement and control system is switched to earth measurement and control communication, and a heaven-earth integrated transponder A and a heaven-earth integrated transponder B can receive remote control instructions through a dual-channel hot standby; the heaven-earth integrated transponder A and the heaven-earth integrated transponder B can send telemetering data through two channels.
A geostationary orbit satellite sky-ground integrated measurement and control system uses a high-reliability microwave switch, a position switch and the like to switch channels. The relay measurement and control forward channel and the ground measurement and control remote receiving channel share a receiving antenna, and the microwave switch switching mode is used for time sharing. The relay measurement and control return channel and the ground measurement and control remote measurement sending channel share a power amplifier and a transmitting antenna, and a microwave switch switching mode is used for time sharing.
Under normal working conditions, the power amplifier A and the power amplifier B are respectively connected with a satellite-Z-direction transmitting antenna and a + Z-phase transmitting antenna. In the active section and the track transfer section, the power amplifier A and the power amplifier B work as double heat engines, and the measurement and control system can realize quasi-omnidirectional coverage to the ground or a relay. After the fixed point is reached and under the condition of + Z direction to the ground, the power amplifier A can be powered off to reduce the power consumption of the system, and the power amplifier B keeps the power-on state and sends telemetering data to the ground. Under the condition that one power amplifier fails, the measurement and control system can switch the position switch and the microwave switch to realize + Z direction ground or relay and-Z direction ground or relay, and ensure the normal communication between the measurement and control system and a ground system and a relay satellite.
The invention relates to a space-ground integrated measurement and control system of a static orbit satellite, which is derived from relay measurement and control requirements of an active section of the static orbit satellite and on-orbit section ground measurement and control requirements, designs a measurement and control system with high reliability and high integration, realizes quasi-omnidirectional and high-code-rate relay measurement and control of the active section, and ensures high-reliability ground measurement and control of on-orbit section dual-channel hot backup.
A geostationary orbit satellite heaven-earth integrated measurement and control system is composed of a heaven-earth integrated transponder, a microwave switch, a position switch, a combined power divider, a power amplifier, a measurement and control receiving antenna, a transmitting antenna and a high-frequency cable. The relay measurement and control and the ground measurement and control share the necessary single machine such as an antenna, a power amplifier, a responder and the like, and a microwave switch is used for switching the functions of the relay measurement and control and the ground measurement and control. When the microwave switch is switched to the relay measurement and control channel, a transponder A relay measurement and control channel is used for the ground; using a transponder B relay measurement and control channel on the sky; the two are combined into a quasi-omnidirectional relay measurement and control channel without backup. When the microwave component is switched to the ground measurement and control channel, the transponder A forms a quasi-omnidirectional ground measurement and control main channel by the sky antenna and the ground antenna; the responder B forms a quasi-omnidirectional ground measurement and control backup channel for the sky and the ground antenna; the two are combined into a quasi-omnidirectional and double-backup ground measurement and control channel. In the active section, a ground measurement and control channel is set during the satellite takeoff, and the ground measurement and control channel and the invisible arc section of the ground station are switched into a relay measurement and control channel; in the orbit transfer section, a ground measurement and control channel is arranged before the satellite is ignited, and the extraterrestrial arc section is switched into a relay measurement and control arc section; after the fixed point is determined, the satellite is set as a ground measurement and control channel, and the state is maintained until the service life is over.
When the microwave switch can not be switched normally, the measurement and control system can always keep a quasi-omnidirectional measurement and control function, and the reliability of the satellite measurement and control function can be ensured.
Description of the attached tables:
attached table 1 status settings and channel status table corresponding to different modes
Remarks 1: the position switch maintains the design result of the J1-J2& J3-J4 state; when the position switch is switched to J1-J4& J2-J3, the above satellite-Z coverage and + Z coverage are interchanged.
Remarks 2: the Z direction represents the radiation coverage of the measurement and control beam in the Z direction of the satellite in a hemispherical mode; the + Z direction indicates that the measurement and control beam radiates and covers in the + Z direction of the satellite in a hemispherical mode; the combination of the-Z direction and the + Z direction can realize quasi-omnidirectional radiation coverage of the measurement and control beam in a spherical form.
The measurement and control communication is suitable for quasi-omnidirectional coverage, and the satellite can communicate under any attitude. The Z direction is a hemisphere cover, the + Z direction is a hemisphere cover, two hemispheres are spliced to form a sphere, and each direction can be used.
The invention uses the microwave switch, the position switch and the power dividing combiner to realize the quasi-omnidirectional measurement and control communication of the relay, the quasi-omnidirectional measurement and control communication of a ground system and the semi-spherical measurement and control communication of the relay ground.
Aiming at relay and aiming at omnidirectional reception: rant 1-R microwave switch A-J1-responder A-AZR (-Z direction covering); rant 2-R microwave switch B-J1-responder B-BZR (+ Z direction coverage).
For relay quasi-omni transmission: tant 1-position switch-J3-J4-power amplifier A-T microwave switch A-J1-responder A-AZT (-Z direction covering); tant 2-position switch-J1-J2-power amplifier B-T microwave switch B-J1-responder B-BZT (+ Z direction covering).
Quasi-omnidirectional reception for a terrestrial system: rant 1-R microwave switch A-J2-responder A-ADR (-Z direction cover); rant 2-R microwave switch B-J2-responder B-BDR (+ Z direction covering).
Quasi-omnidirectional emission to a ground system: tant 1-position switch-J3-J4-power amplifier A-T microwave switch A-J2-responder A-ADT (-Z direction covering); tant 2-position switch-J1-J2-power amplifier B-T microwave switch B-J2-responder B-BDT (+ Z direction covering).
The position switch acts as follows: and the connection relations of the Tant1 and the Tant2, the responder A and the responder B are interchanged.
Receiving the combined power divider: after the Rant1 and the Rant2 are combined and then divided, the Rant1 and the Rant2 can be simultaneously connected with the responder A and the responder B.
It is well within the knowledge of a person skilled in the art to implement the system and its various devices, modules, units provided by the present invention in a purely computer readable program code means that the same functionality can be implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the present invention can be regarded as a hardware component, and the devices, modules and units included therein for implementing various functions can also be regarded as structures within the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A geostationary orbit satellite space-ground integrated measurement and control system is characterized by comprising a space-ground integrated measurement and control device; the measurement and control communication is carried out by adjusting the space-ground integrated measurement and control device, and the measurement and control communication mode comprises quasi-omnidirectional communication to a relay satellite, quasi-omnidirectional communication to a ground system or power consumption reduction communication to the ground system.
2. The geostationary orbit satellite space-ground integrated measurement and control system of claim 1, wherein the space-ground integrated measurement and control device comprises a first receiving antenna, a first receiving microwave switch, a first transponder, a first transmitting microwave switch, a first power amplifier, a position switch and a first transmitting antenna;
the first receiving antenna is connected with the master control position of the first receiving microwave switch;
the first control position of the first microwave receiving switch is connected with a relay receiving channel of a first transponder;
the relay transmitting channel of the first transponder is connected with the first control position of the first microwave transmitting switch;
the master control position of the first transmitting microwave switch is connected with the input port of the first power amplifier;
the output port of the first power amplifier is connected with the fourth port of the position switch;
and the third port of the position switch is connected with the first transmitting antenna.
3. The geostationary orbit satellite space-ground integrated measurement and control system of claim 2, wherein the space-ground integrated measurement and control device further comprises a second transmitting antenna;
and the first port of the position switch is connected with the second transmitting antenna.
4. The geostationary orbit satellite space-ground integrated measurement and control system of claim 3, wherein the space-ground integrated measurement and control device further comprises a second receiving antenna, a second receiving microwave switch, a second transponder, a second transmitting microwave switch and a second power amplifier;
the second receiving antenna is connected with the master control position of the second receiving microwave switch;
the first control position of the second microwave receiving switch is connected with a relay receiving channel of a second transponder;
the relay transmitting channel of the second transponder is connected with the first control position of the second microwave transmitting switch;
the master control position of the second transmitting microwave switch is connected with the input port of the second power amplifier;
and the output port of the second power amplifier is connected with the second port of the position switch.
5. The geostationary orbit satellite space-ground integrated measurement and control system of claim 4, wherein the space-ground integrated measurement and control device further comprises a receiving combiner power divider;
the second control position of the first microwave receiving switch is connected with the first port of the receiving combiner power divider;
the third port of the receiving combined power divider is connected with a ground receiving channel of the first responder;
the fourth port of the receiving combined circuit power divider is connected with a ground receiving channel of the second responder;
the ground transmitting channel of the first transponder is connected with the second control position of the first microwave transmitting switch; (ii) a
The ground transmitting channel of the second transponder is connected with the second control position of the second transmitting microwave switch.
6. The geostationary orbit satellite space-ground integrated measurement and control system of claim 5, wherein the second control position of the second receiving microwave switch is connected with the second port of the receiving combiner power divider.
7. The geostationary orbit satellite sky-ground integrated measurement and control system of claim 1, wherein the mode of measurement and control communication further comprises communicating to both the relay satellite and to the ground system.
8. An geostationary orbit satellite space-ground integrated measurement and control method is characterized in that the geostationary orbit satellite space-ground integrated measurement and control system of any one of claims 1 to 7 is applied, and the method comprises the following steps:
the construction steps are as follows: constructing a space-ground integrated measurement and control device;
the measurement and control steps are as follows: and adjusting the heaven-earth integrated measurement and control device, and carrying out measurement and control communication according to the adjusted heaven-earth integrated measurement and control device.
9. The geostationary orbit satellite space-ground integrated measurement and control method of claim 8, wherein in the measurement and control step, the measurement and control communication mode comprises quasi-omnidirectional communication to a relay satellite, quasi-omnidirectional communication to a ground system or power consumption reduction communication to the ground system.
10. The geostationary orbit satellite space-ground integrated measurement and control method of claim 9, wherein in the measurement and control step, the measurement and control communication mode further comprises communicating to a relay satellite and to a ground system simultaneously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211109583.2A CN115580333A (en) | 2022-09-13 | 2022-09-13 | Geostationary orbit satellite space-ground integrated measurement and control system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211109583.2A CN115580333A (en) | 2022-09-13 | 2022-09-13 | Geostationary orbit satellite space-ground integrated measurement and control system and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115580333A true CN115580333A (en) | 2023-01-06 |
Family
ID=84581296
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211109583.2A Pending CN115580333A (en) | 2022-09-13 | 2022-09-13 | Geostationary orbit satellite space-ground integrated measurement and control system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115580333A (en) |
-
2022
- 2022-09-13 CN CN202211109583.2A patent/CN115580333A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105449362B (en) | A kind of double star dualbeam S band satellite communication phased array antenna | |
| US7071873B2 (en) | T/R module for satellite TT and C ground link | |
| CN109245833B (en) | Universal comprehensive radio frequency measurement and control system for spacecraft | |
| CN114499647B (en) | Planetary detection measurement and control communication system | |
| CN105607081A (en) | Air-traffic control emergency rescue Beidou communication and navigation integrated system | |
| CN102717902B (en) | Phased multi-rate self-adaptive measurement and control system of mars exploration deep space spacecraft | |
| US10566683B1 (en) | System and method for an aircraft communicating with multiple satellite constellations | |
| CN105738929A (en) | Beido communication navigation integrated airborne terminal | |
| KR101860012B1 (en) | Transmit/receive unit of satellite having structure simplification with redundancy | |
| CN111934747A (en) | System and method for realizing unified measurement and control of low-orbit formation satellites and transponder | |
| CN108736955A (en) | A kind of full duplex inter-satellite link system and method that transmitting-receiving frequency is changeable | |
| CN105530042A (en) | Measurement and control relay terminal system with low power consumption and wide range | |
| US11211695B1 (en) | Dual beam transmit system for analog beamforming airborne satellite communications | |
| CN115580333A (en) | Geostationary orbit satellite space-ground integrated measurement and control system and method | |
| CN109037968B (en) | Low-orbit satellite access antenna system with combination of wide and narrow beams | |
| KR20130068673A (en) | Satellite rf transmitting/receiving signal distribution unit | |
| CN111679300B (en) | LEO-HEO multi-orbit satellite measurement and control system and method | |
| RU191165U1 (en) | UNMANNED AIRCRAFT RADIO COMMUNICATION TERMINAL | |
| Arun et al. | An effective downlink budget for 2.24 GHz s-band LEO satellites | |
| CN103746732A (en) | Maritime satellite active antenna module | |
| Reis et al. | An overview of the alfa crux cubesat mission for narrowband communication | |
| JPH047853B2 (en) | ||
| Kondo et al. | Development of aeronautical maritime experimental transponder on engineering test satellite-V | |
| Liu et al. | The Ka-band phased array antenna system of the highly elliptical orbit communication satellite | |
| CN203466817U (en) | Maritime satellite active antenna module |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |