CN113447965A - Spacecraft emergency measurement and control device and method based on Beidou third GSMC/RSMC - Google Patents
Spacecraft emergency measurement and control device and method based on Beidou third GSMC/RSMC Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/32—Multimode operation in a single same satellite system, e.g. GPS L1/L2
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/20—Integrity monitoring, fault detection or fault isolation of space segment
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/243—Demodulation of navigation message
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/29—Acquisition or tracking or demodulation of signals transmitted by the system carrier including Doppler, related
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/30—Acquisition or tracking or demodulation of signals transmitted by the system code related
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/33—Multimode operation in different systems which transmit time stamped messages, e.g. GPS/GLONASS
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Abstract
The invention provides a spacecraft emergency measurement and control device and method based on Beidou No. three GSMC/RSMC, which comprises the following steps: the system comprises a short message antenna, a navigation antenna, a preamplifier module, a baseband processing module and a power amplifier module; transmitting and receiving RDSS signals by a short message antenna; the navigation antenna receives an RNSS signal and a Beidou No. three B2B signal; the baseband processing module captures, tracks and measures the amplified RNSS signals, extracts frame time scale signals according to S frequency point signals and B2B signals of the RDSS, demodulates remote control information sent to a short message terminal by a ground command center according to the frame time scale signals, receives external telemetering data and generates transmitting signals; and the power amplifier module amplifies the transmitting signal into an L frequency point signal of the RDSS and outputs the L frequency point signal to the short message antenna. The invention enriches the measurement and control means of the spacecraft, has the advantages of simple and convenient use and good timeliness for the measurement and control of the spacecraft and the position report, can effectively reduce the load of the traditional measurement and control station, and helps to better develop the measurement and control work of the spacecraft.
Description
Technical Field
The invention relates to the field of spacecraft navigation technology application, in particular to a spacecraft emergency measurement and control device and method based on Beidou No. three GSMC/RSMC (Global Short Message Communication, Global Short Message Communication/Regional Short Message Communication).
Background
Due to the limitation of visible radian, the measurement and control information of various current spacecrafts in the field is difficult to transmit back to China, which causes great obstacles for global measurement and control of the spacecrafts, and with the rapid increase of the number of the spacecrafts in China, the existing ground station network resources obviously cannot meet the measurement and control management requirements of future large-scale constellations, while the traditional measurement and control means such as inter-satellite links have the problems of limited resources, complex application flow and the like.
Disclosure of Invention
Based on the reasons, the embodiment of the invention provides a spacecraft emergency measurement and control device and method based on the Beidou No. three GSMC/RSMC.
In a first aspect of the embodiments of the present invention, a spacecraft emergency measurement and control device based on the third beidou GSMC/RSMC is provided, which includes: the system comprises a short message antenna, a navigation antenna, a preamplifier module, a baseband processing module and a power amplifier module;
the short message antenna is configured to: receiving an S frequency point signal of an RDSS (Radio Determination Satellite Service), and transmitting an L frequency point signal of the RDSS;
the navigation antenna is configured to: receiving an RNSS (Radio Navigation Satellite System) signal and a beidou No. three B2B signal;
the preamplifier module is configured to: amplifying the RNSS signal;
the baseband processing module is configured to: capturing, tracking and measuring the amplified RNSS signal; the baseband processing module is further configured to extract the frame time scale signal according to the S frequency point signal of the RDSS and the B2B signal, demodulate remote control information sent to a short message terminal by a ground command center according to the frame time scale signal, receive external telemetry data, and generate a transmission signal according to the remote control information and the external telemetry data;
the power amplifier module is configured to: and amplifying the transmitting signal into an L frequency point signal of the RDSS and outputting the L frequency point signal to the short message antenna.
Optionally, the short message antenna includes an L-band transmitting antenna with a GSMC/RSMC function and an S-band receiving antenna with a GSMC/RSMC function;
the Navigation antenna comprises a BDS (BeiDou Navigation Satellite Navigation System) B1 waveband receiving antenna, a BDS B2 waveband receiving antenna, a BDS B3 waveband receiving antenna, a GPS (Global Positioning System) L1 waveband receiving antenna and a GPS L2 waveband receiving antenna.
Optionally, the navigation antenna receives the RNSS signal and the beidou three global short message signal in a mode of a frequency-locked loop-assisted phase-locked loop;
when the navigation antenna receives a B2B signal of the Beidou No. three RSMC, frequency offset information output by a second-order frequency-locked loop parallel auxiliary third-order phase-locked loop carrier loop of a receiving end is used as a frequency estimation value of the B2B signal of the Beidou No. three RSMC, and the frequency estimation value is compensated into a B2B signal frequency transmitted to the baseband processing module.
Optionally, the baseband processing module includes: the navigation processing unit and the short message processing unit;
the navigation processing unit is specifically configured to: sequentially filtering, amplifying, down-converting and analog-to-digital converting the amplified RNSS signal to complete de-spreading, demodulating, original observation quantity collecting, navigation resolving and orbit resolving functions of each mode of the RNSS signal;
the short message processing unit is specifically configured to: and capturing and tracking the S frequency point signal and the B2B signal of the RDSS, extracting a frame time scale signal according to the S frequency point signal and the B2B signal of the RDSS, demodulating remote control information sent to a short message terminal by a ground command center according to the frame time scale signal, receiving external telemetering data, and generating a transmitting signal according to the remote control information and the external telemetering data.
Optionally, the method further includes: an interface module and a power supply module; the interface module and the power supply module are both connected with the baseband processing module;
the interface module is configured to interact data of the baseband processing module with data of an external user interface;
the power module is configured to protect a primary power bus, convert primary power to secondary power to power the baseband processing module, and voltage telemetry; the power supply module comprises a DC-DC conversion module, a voltage telemetry circuit module and a switch instruction processing circuit module.
Optionally, the device includes 2 kinds of states of military code and big dipper civilian authorization card, wherein military code possesses short message data encryption and decryption function.
Optionally, the device comprises a Beidou global short message communication function and a regional short message communication function;
in a global range, the Beidou global short message communication function is used for position and health reports and supporting a high-capacity RDSS communication mode in an emergency mode;
in the service range of the Asia-Pacific region, the regional short message communication function comprises a mode that the signal power is-123.8 dBm when the special segment 24kbps information frame is used, a mode that the signal power is-127.5 dBm when the special segment 16kbps information frame is used, and a mode that the signal power is-130.0 dBm when the special segment 8kbps information frame is used.
The second aspect of the embodiment of the invention provides a spacecraft emergency measurement and control method, based on any one of the spacecraft emergency measurement and control devices based on the third Beidou satellite System/GSMC provided by the first aspect of the embodiment, the spacecraft emergency measurement and control device comprises:
receiving a first remote control instruction of a ground emergency measurement and control station, and sending a second remote measurement instruction to a navigation satellite according to the first remote control instruction based on the third Beidou GSMC/RSMC function; wherein the second telemetry command is to cause the navigation satellite to transmit telemetry information;
and receiving the telemetering information, and sending telemetering data to the ground emergency measurement and control station based on the third Beidou GSMC/RSMC function.
Optionally, the method further includes:
and receiving an RDSS signal, an RNSS signal and a Beidou III B2B signal, demodulating the RNSS signal, and acquiring the position information, ephemeris information and time information of the spacecraft.
Optionally, the method further includes:
determining the communication condition of the third Beidou GSMC/RSMC function;
wherein the determined conditions include:
judging whether the navigation satellite is in a regional short message service area or not according to the position information, and/or judging whether the navigation satellite is in the regional short message service area or not according to the position information
Determining a communication rate from the RDSS signal, and/or
Determining the highest communication frequency according to the Beidou authorization card, and/or
And determining the maximum communication capacity of the RDSS signal and the global short message function through information framing.
Compared with the prior art, the spacecraft emergency measurement and control device and method based on the Beidou No. three GSMC/RSMC provided by the embodiment of the invention have the beneficial effects that:
the device can realize spacecraft emergency measurement and control with a ground emergency measurement and control station and a Beidou satellite navigation system, and simultaneously realize the remote measurement information downloading and remote control information receiving of spacecraft position information, health information and the like by adopting a GSMC position report, a short message service and a RSMC large data volume short message communication mode; the method adopts a position and state information reporting mode in the on-orbit running process, adopts a large-data-volume regional short message communication mode for measurement and control in the emergency process, simultaneously supports two working modes of short message dormancy and short message normal working, and can reduce power consumption in the short message dormancy.
Drawings
Fig. 1 is a schematic structural diagram of a spacecraft emergency measurement and control device based on a third Beidou satellite system GSMC/RSMC provided by an embodiment of the invention;
fig. 2 is a schematic structural diagram of a beidou satellite navigation system provided in an embodiment of the present invention;
fig. 3 is a schematic flow chart of an implementation of the spacecraft emergency measurement and control method according to the embodiment of the invention;
fig. 4 is a schematic flow chart illustrating an implementation process of another spacecraft emergency measurement and control method according to an embodiment of the present invention.
Detailed Description
In the following description, for purposes of explanation and not limitation, specific details are set forth, such as particular system structures, techniques, etc. in order to provide a thorough understanding of the embodiments of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
In order to explain the technical means of the present invention, the following description will be given by way of specific examples.
Referring to fig. 1, a schematic structural diagram of the spacecraft emergency measurement and control device based on the third beidou GSMC/RSMC in this embodiment is shown. For convenience of explanation, only the portions related to the present embodiment are shown.
The spacecraft emergency measurement and control device based on the third Beidou GSMC/RSMC mainly comprises: the integrated short message antenna 200, navigation antenna 100, preamplifier module 300, baseband processing module 400 and power amplifier module 500. The navigation antenna 100 is connected to the preamplifier module 300, the preamplifier module 300 is connected to the baseband processing module 400, the baseband processing module 400 is connected to the power amplifier module 500, and the power amplifier module 500 is connected to the short message antenna 200.
Specifically, the short message antenna 200 receives an S frequency point signal of the RDSS, the navigation antenna 100 receives an RNSS signal and a B2B signal of beidou No. three, and the preamplifier module 300 amplifies the RNSS signal and sends the amplified RNSS signal to the baseband processing module 400. Then, the baseband processing module 400 captures, tracks and measures the amplified RNSS signal, further extracts the frame timing signal according to the S frequency point signal of the RDSS and the B2B signal, demodulates remote control information sent to a short message terminal by a ground command center according to the frame timing signal, receives external telemetry data, generates a transmission signal according to the remote control information and the external telemetry data, and sends the transmission signal to the power amplifier module 500; the power amplifier module 500 amplifies the transmission signal into an L frequency point signal of the RDSS and outputs the L frequency point signal to the short message antenna 200, and finally the short message antenna 200 transmits the L frequency point signal of the RDSS, thereby realizing communication with the ground emergency measurement and control station and the satellite platform.
The Beidou I system is an important space infrastructure in China, can provide various services such as global RNSS navigation positioning, global short message communication, large-capacity RDSS short message communication in Asia-Pacific region and the like for the region below 3000km height, and provides effective resources and platform support for spacecraft measurement and control. The Beidou short message system is adopted, the characteristics of global short message communication and high-capacity RDSS short message communication in Asia-Pacific areas are comprehensively utilized, and the Beidou short message system has the advantages of convenience in use, global coverage and high-capacity data transmission. Therefore, according to the emergency measurement and control application requirements of the spacecraft, the design of the device is developed, and the real-time information return and emergency measurement and control of the spacecraft are realized through the Beidou global short message communication and regional short message communication functions.
The device of the embodiment can be installed on a target spacecraft, wherein the target spacecraft is located in a space below 1000km of the earth surface and is separated from a ground emergency measurement and control station and a navigation satellite. The spacecraft provided with the device forms a navigation system with a navigation satellite and a ground emergency measurement and control station, as shown in fig. 2, the device receives measurement and control data of the spacecraft, transmits and receives spacecraft measurement and control information through the Beidou No. three GSMC/RSMC function, and communicates with the ground emergency measurement and control station through the Beidou No. three GSMC/RSMC function, so that the spacecraft emergency measurement and control function is realized, measurement and control means of the spacecraft are enriched, measurement and control and position reporting of the spacecraft have the advantages of simplicity and convenience in use and good timeliness, the load of the traditional measurement and control station can be effectively reduced, and measurement and control work of the spacecraft is better developed.
In one embodiment, the short message antenna 200 has a transceiving function, and may include an L-band transmitting antenna of the GSMC/RSMC function and an S-band receiving antenna of the GSMC/RSMC function.
The navigation antenna 100 of the present embodiment includes 5 frequency points, which may include a BDS B1 band receiving antenna, a BDS B2 band receiving antenna, a BDS B3 band receiving antenna, a GPS L1 band receiving antenna, and a GPS L2 band receiving antenna.
In an embodiment, the navigation antenna 100 of the present embodiment receives the RNSS signal and the beidou three global short message signal by a frequency-locked loop assisted phase-locked loop.
When the navigation antenna 100 receives the B2B signal of the beidou three-number RSMC, the frequency offset information output by the second-order frequency-locked loop parallel auxiliary third-order phase-locked loop carrier loop of the receiving end is used as the frequency estimation value of the B2B signal of the beidou three-number RSMC, and the frequency estimation value is compensated to the B2B signal frequency transmitted to the baseband processing module 400.
Specifically, for meeting the requirement of high dynamic motion of the spacecraft, for capturing the RNSS signal and the RSMC signal, stable tracking under a large dynamic condition is ensured by using a frequency-locked loop to assist the phase-locked loop, for example, by setting a proper bandwidth, a second-order frequency-locked loop is used to assist a third-order phase-locked loop to meet the requirement. In the aspect of RSMC inbound signal transmission, in order to enable inbound signals to be normally inbound for demodulation, frequency offset information output by a second-order frequency-locked loop parallel auxiliary third-order phase-locked loop carrier loop of an outbound signal receiving end is used as frequency estimation of received signals, the frequency offset information is compensated to the transmission frequency of the signals, and the compensated transmission signal frequency offset meets the inbound signal requirement of a Beidou ground master station. The dynamic performance index of the spacecraft is met, the flying speed is not less than 10km/s, and the acceleration is not less than 10 g.
In one embodiment, the baseband processing module 400 may include: a navigation processing unit 410 and a short message processing unit 420. The navigation processing unit 410 is connected to the preamplifier module 300, and the short message processing unit 420 is connected to the preamplifier module 300, the short message antenna 200, and the power amplifier module 500. The navigation processing unit 410 and the short message processing unit 420 of this embodiment can be implemented in a dedicated navigation processing chip, which is beneficial to the miniaturization design of the device.
Specifically, the navigation processing unit 410 sequentially performs filtering, amplification, down-conversion and analog-to-digital conversion on the amplified RNSS signal, and completes functions of despreading, demodulation, original observed quantity acquisition, navigation resolving in each mode and orbit resolving of the RNSS signal; the short message processing unit 420 captures and tracks the S frequency point signal of the RDSS and the B2B signal, extracts a frame timing signal according to the S frequency point signal of the RDSS and the B2B signal, demodulates remote control information sent by the ground command center to the short message terminal according to the frame timing signal, receives external telemetry data, and generates a transmission signal according to the remote control information and the external telemetry data.
In one embodiment, the apparatus may further comprise: an interface module and a power supply module; the interface module and the power module are both connected with the baseband processing module 400; the interface module interacts the data of the baseband processing module 400 with the data of the external user interface, i.e. the data interaction function between the whole machine and each external user interface is completed; the power supply module protects the primary power supply bus, converts the primary power supply into a secondary power supply to supply power to the baseband processing module 400 and performs voltage telemetering, namely, the functions of primary power supply bus protection, conversion from the primary power supply to the secondary power supply and voltage telemetering are completed; the power supply module comprises a DC-DC conversion module, a voltage telemetry circuit module and a switch instruction processing circuit module.
Optionally, the communication device of the device may include 2 states of a military code and a big dipper civil authorization card, and the function is set through software, wherein the military code has a short message data encryption and decryption function.
Optionally, the device can also have a Beidou global short message communication function and a regional short message communication function at the same time. Specifically, the method comprises the following steps:
in a global range, the Beidou global short message communication function is used for position and health reports, namely the global short message function is used for position and health reports; and supporting a high capacity RDSS communication mode in an emergency mode.
In the service range of the asia-pacific region, the regional short message communication function comprises a mode that the signal power is-123.8 dBm when the special section 24kbps information frame is provided, a mode that the signal power is-127.5 dBm when the special section 16kbps information frame is provided, and a mode that the signal power is-130.0 dBm when the special section 8kbps information frame is provided, namely, in the service range of the asia-pacific region, the signal power of the special section 24kbps information frame is supported, the bit error rate: less than or equal to 1X 10-5(signal power-123.8 dBm); for a dedicated segment 16kbps information frame, error rate: less than or equal to 1X 10-5(signal power-127.5 dBm); for a dedicated segment 8kbps information frame, error rate: less than or equal to 1X 10-5(signal power-130.0 dBm) three modes.
The integrated short message antenna 200 completes the RDSS L frequency point signal transmission and the RDSS S frequency point signal reception; the navigation antenna 100 completes RNSS signal receiving and receives Beidou No. three B2B global short message outbound signals; the power amplifier module completes the amplification of RDSS and global short message transmission signal power; the baseband processing module 400 is designed based on a radio frequency dedicated for navigation and a baseband SOC, and comprises a navigation processing unit 410 and a short message processing unit 420, wherein the navigation processing unit 410 performs filtering, amplification and down-conversion on a navigation signal passing through a preamplifier module, converts the navigation signal to an intermediate frequency, performs analog-to-digital conversion, completes capturing, tracking and measuring of the navigation signal in a digital domain, and realizes functions of despreading and demodulating the navigation signal, collecting original observed quantity, navigation resolving in each mode, orbit resolving and the like; the short message processing unit 420 completes the capturing and tracking functions of B2B signals and S frequency point intermediate frequency signals, extracts frame time scale signals, demodulates remote control information sent to a short message terminal by a ground command center, receives remote measurement data output by an interface module, completes channel coding, spread spectrum, digital modulation and up-conversion, generates a transmitting signal, realizes the emergency measurement and control function of the spacecraft, enriches the measurement and control means of the spacecraft, has the advantages of simple and convenient use and good timeliness for measurement and control and position reporting of the spacecraft, can effectively reduce the load of the traditional measurement and control station, and helps to better develop the measurement and control work of the spacecraft.
The spacecraft emergency measurement and control device based on the Beidou third GSMC/RSMC can realize spacecraft emergency measurement and control with a ground emergency measurement and control station and a Beidou satellite navigation system, and simultaneously adopts a GSMC position report, a short message service and a RSMC large data volume short message communication mode to realize the remote measurement information downloading and remote control information receiving of spacecraft position information, health information and the like; the method adopts a position and state information reporting mode in the on-orbit running process, adopts a large-data-volume regional short message communication mode for measurement and control in the emergency process, simultaneously supports two working modes of short message dormancy and short message normal working, and can reduce power consumption in the short message dormancy.
Corresponding to the spacecraft emergency measurement and control device based on the third beidou GSMC/RSMC in the above embodiment, the embodiment provides a spacecraft emergency measurement and control method. Referring to fig. 3, an implementation flow diagram of an embodiment of the spacecraft emergency measurement and control method provided in this embodiment is detailed as follows:
step S101, receiving a first remote control instruction of a ground emergency measurement and control station, and sending a second remote measurement instruction to a navigation satellite according to the first remote control instruction based on the third Beidou satellite navigation/satellite navigation module (GSMC/RSMC) function; wherein the second telemetry command is to cause the navigation satellite to transmit telemetry information.
And S102, receiving the telemetering information, and sending telemetering data to the ground emergency measurement and control station based on the third Beidou GSMC/RSMC function.
The spacecraft carries out measurement and control communication to a spacecraft emergency measurement and control device based on the Beidou No. three GSMC/RSMC; the device receives measurement and control data through a spacecraft bus, and transmits and receives spacecraft measurement and control information through the Beidou third GSMC/RSMC function; the ground emergency measurement and control station realizes the emergency measurement and control of the spacecraft through the third Beidou GSMC/RSMC function.
Specifically, the spacecraft emergency measurement and control device based on the Beidou No. three GSMC/RSMC is arranged on a spacecraft, and the spacecraft sends telemetering information including spacecraft position information, health information and the like to an interface module of the device through a bus and receives remote control information sent by the device; as shown in fig. 1, the ranging signal is received from the navigation satellite through the navigation antenna 100, amplified by the preamplifier module 300, and then input to the baseband processing module 400 for resolving, so as to obtain the position of the spacecraft, and predict the position of the navigation satellite. And receiving S frequency point downlink signals through the integrated short message antenna 200, capturing and tracking the signals in the short message baseband module, and establishing RDSS communication connection with the Beidou navigation system.
Further, referring to fig. 4, in step 202, a spacecraft satellite computer is received through the interface module or a global short message ground remote control instruction is received, and whether to enter an emergency response mode is determined. In a normal mode, the device adopts a global short message working mode and a low-frequency working mode to report the position and the basic state information of the spacecraft; entering an emergency response mode, opening an RDSS communication function by a short message baseband module, and realizing a starting report; in step 203, the ground emergency measurement and control station has a GSMC/RSMC communication function and a beidou short message command function, and performs grouping communication and management on a plurality of devices, thereby further improving multi-satellite measurement and control capability. The ground emergency measurement and control station has the function of GSMC/RSMC of Beidou III, and is configured with functions of commanding, broadcasting and the like according to emergency measurement and control requirements.
Optionally, according to the communication conditions and the needs of the device, two data types of the Beidou third GSMC/RSMC communication can be selected, one is an ASCII code adopted by common Chinese character communication, and the other is a BCD code mode. GSMC can transmit 40 Chinese characters or 560 bits, and the transmission frequency is configurable at 1, 2, 5, 10 and 15 minutes according to different authorization level limits. The RSMC can transmit 1000 Chinese characters or 14000 bits at the maximum, the transmission frequency is generally 1 minute and the fastest transmission frequency is 1 second according to different authorization level limits.
Optionally, the method further includes: the device receives the RDSS signal, the RNSS signal and the B2B signal of the Beidou III, demodulates the RNSS signal and acquires the position information, the ephemeris information and the time information of the spacecraft, namely the device receives the S, B2B frequency point downlink signal and the navigation signal and demodulates the navigation signal to acquire the position, the ephemeris and the time information of the spacecraft, and has the capability of forecasting the position of the navigation satellite.
Optionally, the method further includes: and performing a starting report before starting to obtain Beidou system authentication, and determining the communication condition of the Beidou No. three GSMC/RSMC function.
Wherein the determined conditions include:
judging whether the navigation satellite is in a regional short message service area or not according to the position information, and/or judging whether the navigation satellite is in the regional short message service area or not according to the position information
Determining a communication rate from the RDSS signal, and/or
Determining the highest communication frequency according to the Beidou authorization card, and/or
And determining the maximum communication capacity of the RDSS signal and the global short message function through information framing.
Referring to fig. 1, the baseband processing module 400 performs comprehensive judgment on the short message communication conditions, specifically includes notifying RNSS positioning information to judge whether the short message communication conditions are in the RSMC service area, selecting a communication rate according to S-frequency point signal reception, selecting the highest communication frequency according to the beidou authorization card, framing through information, and transmitting and receiving spacecraft measurement and control information by using the RDSS and the maximum communication capability of the global short message function.
The spacecraft emergency measurement and control method enriches measurement and control means for the spacecraft, has the advantages of simplicity and convenience in use and good timeliness for measurement and control and position reporting of the spacecraft, can effectively reduce the load of a traditional measurement and control station, and helps to better develop measurement and control work of the spacecraft.
It should be understood by those skilled in the art that the sequence numbers of the steps in the foregoing embodiments do not imply an execution sequence, and the execution sequence of each process should be determined by its function and inherent logic, and should not constitute any limitation to the implementation process of the embodiments of the present invention.
The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present invention, and are intended to be included within the scope of the present invention.
Claims (10)
1. The utility model provides an emergent measurement and control device of spacecraft based on three numbers GSMC of big dipper RSMC, its characterized in that includes: the system comprises a short message antenna, a navigation antenna, a preamplifier module, a baseband processing module and a power amplifier module;
the short message antenna is configured to: receiving an S frequency point signal of the RDSS and transmitting an L frequency point signal of the RDSS;
the navigation antenna is configured to: receiving an RNSS signal and a Beidou No. three B2B signal;
the preamplifier module is configured to: amplifying the RNSS signal;
the baseband processing module is configured to: capturing, tracking and measuring the amplified RNSS signal; the baseband processing module is further configured to extract the frame time scale signal according to the S frequency point signal of the RDSS and the B2B signal, demodulate remote control information sent to a short message terminal by a ground command center according to the frame time scale signal, receive external telemetry data, and generate a transmission signal according to the remote control information and the external telemetry data;
the power amplifier module is configured to: and amplifying the transmitting signal into an L frequency point signal of the RDSS and outputting the L frequency point signal to the short message antenna.
2. The Beidou I-III GSMC/RSMC-based spacecraft emergency measurement and control device of claim 1, wherein the short message antenna comprises an L-band transmitting antenna with a GSMC/RSMC function and an S-band receiving antenna with the GSMC/RSMC function;
the navigation antenna comprises a BDS B1 waveband receiving antenna, a BDS B2 waveband receiving antenna, a BDS B3 waveband receiving antenna, a GPS L1 waveband receiving antenna and a GPS L2 waveband receiving antenna.
3. The Beidou third GSMC/RSMC-based spacecraft emergency measurement and control device of claim 1, wherein the navigation antenna receives the RNSS signal and the Beidou third global short message signal in a mode of a frequency locking loop auxiliary phase locking loop;
when the navigation antenna receives a B2B signal of the Beidou No. three RSMC, frequency offset information output by a second-order frequency-locked loop parallel auxiliary third-order phase-locked loop carrier loop of a receiving end is used as a frequency estimation value of the B2B signal of the Beidou No. three RSMC, and the frequency estimation value is compensated into a B2B signal frequency transmitted to the baseband processing module.
4. The Beidou III GSMC/RSMC-based spacecraft emergency measurement and control device of claim 1, wherein the baseband processing module comprises: the navigation processing unit and the short message processing unit;
the navigation processing unit is specifically configured to: sequentially filtering, amplifying, down-converting and analog-to-digital converting the amplified RNSS signal to complete de-spreading, demodulating, original observation quantity collecting, navigation resolving and orbit resolving functions of each mode of the RNSS signal;
the short message processing unit is specifically configured to: and capturing and tracking the S frequency point signal and the B2B signal of the RDSS, extracting a frame time scale signal according to the S frequency point signal and the B2B signal of the RDSS, demodulating remote control information sent to a short message terminal by a ground command center according to the frame time scale signal, receiving external telemetering data, and generating a transmitting signal according to the remote control information and the external telemetering data.
5. The Beidou III GSMC/RSMC-based spacecraft emergency measurement and control device of claim 1, further comprising: an interface module and a power supply module; the interface module and the power supply module are both connected with the baseband processing module;
the interface module is configured to interact data of the baseband processing module with data of an external user interface;
the power module is configured to protect a primary power bus, convert primary power to secondary power to power the baseband processing module, and voltage telemetry; the power supply module comprises a DC-DC conversion module, a voltage telemetry circuit module and a switch instruction processing circuit module.
6. The Beidou three-number GSMC/RSMC-based spacecraft emergency measurement and control device of claim 1, wherein the device comprises 2 states of military codes and Beidou civil authorization cards, wherein the military codes have short message data encryption and decryption functions.
7. The Beidou third GSMC/RSMC-based spacecraft emergency measurement and control device according to claim 1, wherein the device comprises a Beidou global short message communication function and a regional short message communication function;
in a global range, the Beidou global short message communication function is used for position and health reports and supporting a high-capacity RDSS communication mode in an emergency mode;
in the service range of the Asia-Pacific region, the regional short message communication function comprises a mode that the signal power is-123.8 dBm when the special segment 24kbps information frame is used, a mode that the signal power is-127.5 dBm when the special segment 16kbps information frame is used, and a mode that the signal power is-130.0 dBm when the special segment 8kbps information frame is used.
8. A spacecraft emergency measurement and control method based on the Beidou third GSMC/RSMC-based spacecraft emergency measurement and control device of any one of claims 1 to 7, and the method is characterized by comprising the following steps of:
receiving a first remote control instruction of a ground emergency measurement and control station, and sending a second remote measurement instruction to a navigation satellite according to the first remote control instruction based on the third Beidou GSMC/RSMC function; wherein the second telemetry command is to cause the navigation satellite to transmit telemetry information;
and receiving the telemetering information, and sending telemetering data to the ground emergency measurement and control station based on the third Beidou GSMC/RSMC function.
9. A spacecraft emergency measurement and control method according to claim 8, further comprising:
and receiving an RDSS signal, an RNSS signal and a Beidou III B2B signal, demodulating the RNSS signal, and acquiring the position information, ephemeris information and time information of the spacecraft.
10. A spacecraft emergency measurement and control method according to claim 9, further comprising:
determining the communication condition of the third Beidou GSMC/RSMC function;
wherein the determined conditions include:
judging whether the navigation satellite is in a regional short message service area or not according to the position information, and/or judging whether the navigation satellite is in the regional short message service area or not according to the position information
Determining a communication rate from the RDSS signal, and/or
Determining the highest communication frequency according to the Beidou authorization card, and/or
And determining the maximum communication capacity of the RDSS signal and the global short message function through information framing.
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