CN114499647A - Planetary detection measurement and control communication system - Google Patents
Planetary detection measurement and control communication system Download PDFInfo
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- CN114499647A CN114499647A CN202210224180.6A CN202210224180A CN114499647A CN 114499647 A CN114499647 A CN 114499647A CN 202210224180 A CN202210224180 A CN 202210224180A CN 114499647 A CN114499647 A CN 114499647A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
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- 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
- H04B7/18515—Transmission equipment in satellites or space-based relays
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention provides a planet detection measurement and control communication system, which is used for an ultra-long-distance communication scene including Mars and Mars detection, and comprises the following components: the two power amplifiers are configured to be respectively provided with high-level and low-level transmitting power, wherein low power is used for near-field communication to protect ground deep space measurement and control system equipment, and high power is used for far-field communication to ensure enough EIRP (equivalent interference rejection ratio); 4 antennas, each configured to be capable of simultaneously transmitting and receiving a signal; a high isolation duplexer configured to ensure that each of the secondary antennas can be used for transmitting and receiving signals simultaneously; wherein, the selection is carried out in 4 pairs of antennas, and the output power of the two power amplifiers is selected, so as to respectively carry out the measurement and control communication in various distance ranges.
Description
Technical Field
The invention relates to the technical field of deep space exploration, in particular to a planetary exploration measurement and control communication system.
Background
The measurement and control communication system is applied to deep space exploration satellites such as asteroid exploration and mars exploration, is a transmission channel of remote control instructions, remote control information and load exploration data between the satellites and the ground, and is matched with a ground measurement and control network to realize the tracking, remote control, orbit measurement and load data transmission of the satellites.
The existing measurement and control communication system scheme for the deep space exploration spacecraft has some defects, such as:
the staged multi-code-rate self-adaptive measurement and control system of a certain Mars detection deep space spacecraft has 3 defects:
one is that the number of antennas is large, and 6 antennas are required in total, including 4 low-gain (wide-beam) antennas. The satellite surface usually needs to be provided with various devices such as communication antennas, satellite sensors, solar sailboards, propellers, various loading instruments and the like. The surface area of the satellite body of the small satellite is small, and the low-gain wide-beam antenna needs a wide field of view, which brings great difficulty to the satellite body layout of the small satellite;
secondly, the medium gain antenna is designed to be only used for transmitting and not used for receiving, and is not beneficial to measurement and control communication in attitude lateral deviation modes at a medium distance stage and a long distance stage;
thirdly, the number of power amplifiers is large, 4 power amplifiers are needed totally, and the small satellite platform is not suitable for pursuing low-cost miniaturization design.
The scheme only uses a low-gain wide-beam antenna, is only suitable for application scenes with the satellite-ground distance below ten-million km magnitude and cannot be applied to ultra-long-distance communication scenes including Mars detection; in addition, no microwave network exists between the transmitters of the two answering machines and the two high-power amplifiers, cross connection backup cannot be realized, and double-point faults between the transmitters and the high-power amplifiers cannot be dealt with.
A receiving antenna in a certain scheme only has a pair of low-gain wide-beam antennas, and if the posture of the receiving antenna is in failure, for example, the receiving antenna faces away from the earth, remote control communication cannot be achieved. In addition, the high-gain antenna of the scheme is only used for transmitting, and even if the posture is normal, the high-gain antenna cannot be used for carrying out data injection with relatively high code rate.
Disclosure of Invention
The invention aims to provide a planetary detection, measurement and control communication system to solve the problems that the existing scheme cannot realize miniaturization and low cost due to the fact that the number of antennas and power amplifiers is large, and the star body layout is difficult.
The invention also aims to provide a planetary detection measurement and control communication system to solve the problems that part of medium and high gain antennas cannot be used for receiving, the antenna gain is low so that ultra-long distance communication cannot be supported, cross connection backup cannot be realized between a transmitting channel and a high-power amplifier, omnidirectional beam coverage cannot be formed during emergency communication and the like in the existing scheme.
In order to solve the above technical problems, the present invention provides a planetary detection measurement and control communication system, which is used in an ultra-long range communication scenario including mars and mars detection, and comprises:
the two power amplifiers are configured to be respectively provided with high-level and low-level transmitting power, wherein low power is used for near-field communication to protect ground deep space measurement and control system equipment, and high power is used for far-field communication to ensure enough EIRP (equivalent interference rejection ratio);
4 antennas, each configured to be capable of simultaneously transmitting and receiving a signal;
a high isolation duplexer configured to ensure that each of the secondary antennas can be used for transmitting and receiving signals simultaneously;
wherein, the selection is carried out in 4 pairs of antennas, and the output power of the two power amplifiers is selected, so as to respectively carry out the measurement and control communication in various distance ranges.
Optionally, in the planetary detection measurement and control communication system, the method further includes:
a transmitting microwave network is arranged between the transmitting channels of the two answering machines and the two large power amplifiers to provide a cross connecting channel to resist double-point faults of any one transmitting channel and any one large power amplifier, and the insertion loss of the microwave network does not influence the final transmitting power before the large power amplifiers;
a receiving microwave network is arranged between the receiving channels and the antennas of the two answering machines, and remote control signals received by any pair of antennas enter the receiving channels of the two answering machines, so that the situation of posture overturning or the fault of the receiving channel of one answering machine is effectively dealt with.
Optionally, in the planetary detection measurement and control communication system, the two transponders are deep space transponders based on software radio, and both the remote measurement and control support multi-gear speed and are used for supporting measurement and control communication under different satellite-ground distances;
the remote control receives the transmission rate of the self-adaptive ground station, the remote control transmission rate is switched according to the instruction information planned by the spaceborne computer or sent by the ground, and the remote control both adopt a channel error correction coding technology;
the receiving sensitivity of the responder is-155 dBm to-157 dBm, the transmitting power is 0dBm, and the antenna gain and the power amplifier transmitting power are adaptively adjusted according to different deep space detection items;
the deep space responder adopts a sidetone ranging system and has the function of sending DOR beacon signals, and the DOR beacon signals are modulated on a telemetering main carrier as subcarrier signals; whether the DOR beacon signal is sent is controlled by a ground control instruction;
the deep space transponder has a telemetry transmission function supporting ranging, and is also provided with a data transmission function, so that high-speed satellite-ground transmission of payload data is realized.
Optionally, in the planetary detection measurement and control communication system, the method further includes:
the first end of the deep space transponder A and the first end of the deep space transponder B are both connected with the second end of the receiving microwave network;
the first end of the deep space transponder A and the first end of the deep space transponder B are both connected with the second end of the transmitting microwave network;
the second end of the deep space transponder A and the second end of the deep space transponder B are both connected with a house-keeping computer;
and the second end of the deep space transponder A and the second end of the deep space transponder B are both connected with a multiplexing memory A and a multiplexing memory B.
Optionally, in the planetary detection measurement and control communication system, the deep space transponder a and the deep space transponder B can adopt a plurality of remote measurement and control rates, and are used for supporting measurement and control communication at a plurality of satellite-to-ground distances;
and the deep space transponder A and the deep space transponder B carry out high-speed satellite-ground transmission of payload data in a data transmission mode.
Optionally, in the planetary detection measurement and control communication system, the multiple-path multiplexing memory a and the multiple-path multiplexing memory B receive, store, compress, multiplex and frame multiple load data;
and the multiplex memory A and the multiplex memory B select whether the whole satellite low-speed telemetering data is multiplexed into the high-speed data transmission data according to the ground remote control instruction so as to independently transmit the load data or perform mixed transmission of the load data and the telemetering data.
Optionally, in the planetary probing, measurement and control communication system, the deep space transponder a and the deep space transponder B select to send the whole satellite low-speed telemetry data from the satellite computer in a downlink manner or send the high-speed data from the multiplexing memory a or the multiplexing memory B in a downlink manner according to a ground remote control instruction, and the low-speed telemetry data from the satellite computer is sent by default when the satellite system is initially powered up.
Optionally, in the planetary detection measurement and control communication system, in 4 pairs of antennas,
the 3 pairs of antennas are used for satellite-ground communication under the condition of normal attitude, and the 1 pair of antennas are used for emergency communication under the condition of abnormal attitude;
2 of the 4 pairs of antennas are low-gain antennas, 1 of the 4 pairs of antennas are medium-gain antennas, and 1 of the 4 pairs of antennas are high-gain antennas, so that measurement and control communication in various distance ranges is supported.
Optionally, the planetary detection, measurement and control communication system further includes a double-pole double-throw microwave switch and a single-pole triple-throw microwave switch, wherein:
the ground high-gain antenna, the ground medium-gain antenna and the ground low-gain antenna are respectively connected with the first end of the single-pole triple-throw microwave switch;
the ground low-gain antenna and the second end of the single-pole three-throw microwave switch are respectively connected with the first end of the double-pole double-throw microwave switch;
in the near field, the single-pole triple-throw microwave switch is switched to the ground low-gain antenna, the ground low-gain antenna and the antenna form an omnidirectional covering beam together, and ground measurement and control communication is realized under the condition of any posture;
in a remote section, the single-pole three-throw microwave switch is switched to the gain antenna in the ground or the high gain antenna in the ground, and the single-pole three-throw microwave switch is respectively used for measurement and control communication when the attitude deflection is smaller than the beam width of the gain antenna in the ground and accurate ground; if the attitude deflection is larger than the beam width of the gain antenna in the ground, the antenna is completely inverted or even rolled, the single-pole three-throw microwave switch is switched to the antenna with low gain to form an omnidirectional covering beam, and the low-code-rate emergency communication is carried out.
Optionally, in the planetary detection, measurement and control communication system, a second end of the double-pole double-throw microwave switch is connected to a first end of a duplexer a and a first end of a duplexer B, respectively, and a transmit-receive isolation between the duplexer a and the duplexer B is up to 120 dBc;
the second end of the duplexer A is respectively connected with the first end of the power amplifier A and the first end of the receiving microwave network;
the second end of the duplexer B is respectively connected with the first end of the power amplifier B and the first end of the receiving microwave network;
and the second end of the power amplifier A and the second end of the power amplifier B are respectively connected with the first end of the transmitting microwave network.
Optionally, in the planetary detection measurement and control communication system, 1 pair of low-gain antennas is arranged on the ground, and 1 pair of low-gain antennas is arranged on the sky; the two pairs of low-gain antennas are used for near-field communication and emergency communication under the condition of abnormal attitude of a far-field;
1 pair of middle gain antennas are arranged on the ground, and the middle gain antennas are used for measurement and control communication when the attitude of a remote area slightly deflects;
1 pair of high-gain antennas are arranged on the ground, and the high-gain antennas are used for measurement and control communication when the attitude of a remote area is accurate to the ground;
two power amplifiers are both provided with high-low transmission power, a low-power amplifier is used for near-field communication, and a high-power amplifier is used for far-field communication.
Optionally, in the planetary detection measurement and control communication system, in 4 pairs of antennas:
the ground high-gain antenna, the ground medium-gain antenna and the ground low-gain antenna are respectively connected with the first end of the single-pole triple-throw microwave switch;
the ground low-gain antenna and the second end of the single-pole three-throw microwave switch are respectively connected with the first end of the double-pole double-throw microwave switch;
in the near field, the single-pole triple-throw microwave switch is switched to the ground low-gain antenna, the ground low-gain antenna and the antenna form an omnidirectional covering beam together, and ground measurement and control communication is realized under the condition of any posture;
in a remote section, the single-pole three-throw microwave switch is switched to the gain antenna in the ground or the high gain antenna in the ground, and the single-pole three-throw microwave switch is respectively used for measurement and control communication when the attitude deflection is smaller than the beam width of the gain antenna in the ground and accurate ground; if the attitude deflection is larger than the beam width of the gain antenna in the ground, the antenna is completely inverted or even rolled, the single-pole three-throw microwave switch is switched to the antenna with low gain to form an omnidirectional covering beam, and the low-code-rate emergency communication is carried out.
Optionally, the planet survey observe and control communication system in, duplexer A's first end and duplexer B's first end are connected respectively to the second end of double-pole double-throw microwave switch, duplexer A with duplexer B's receiving and dispatching isolation is up to 120 dBc.
Optionally, in the planetary detection measurement and control communication system, the method further includes:
the second end of the duplexer A is respectively connected with the first end of the power amplifier A and the first end of the receiving microwave network;
the second end of the duplexer B is respectively connected with the first end of the power amplifier B and the first end of the receiving microwave network;
and the second end of the power amplifier A and the second end of the power amplifier B are respectively connected with the first end of the transmitting microwave network.
Optionally, in the planetary detection measurement and control communication system, the method further includes:
the first end of the deep space transponder A and the first end of the deep space transponder B are both connected with the second end of the receiving microwave network;
the first end of the deep space transponder A and the first end of the deep space transponder B are both connected with the second end of the transmitting microwave network;
the second end of the deep space transponder A and the second end of the deep space transponder B are both connected with a house service computer;
and the second end of the deep space transponder A and the second end of the deep space transponder B are both connected with a multiplexing memory A and a multiplexing memory B.
Optionally, in the planetary detection measurement and control communication system, the method further includes:
the deep space responder A and the deep space responder B can adopt a plurality of remote measuring and control rates and are used for supporting measurement and control communication at various satellite-ground distances;
and the deep space transponder A and the deep space transponder B carry out high-speed satellite-ground transmission of payload data in a data transmission mode.
Optionally, in the planetary detection measurement and control communication system, the multiple-path multiplexing memory a and the multiple-path multiplexing memory B receive, store, compress, multiplex and frame multiple load data;
and the multiplex memory A and the multiplex memory B select whether the whole satellite low-speed telemetering data is multiplexed into the high-speed data transmission data according to the ground remote control instruction so as to independently transmit the load data or perform mixed transmission of the load data and the telemetering data.
Optionally, in the planetary probing, measurement and control communication system, the deep space transponder a and the deep space transponder B select to send the whole satellite low-speed telemetry data from the satellite computer in a downlink manner or send the high-speed data from the multiplexing memory a or the multiplexing memory B in a downlink manner according to a ground remote control instruction, and the low-speed telemetry data from the satellite computer is sent by default when the satellite system is initially powered up.
Optionally, in the planetary exploration measurement and control communication system, the deep space transponder a and the deep space transponder B are shaped products, and are used for deep space exploration items of any satellite-ground distance, and adjusting antenna gain and power amplifier transmitting power to adapt to deep space exploration items of different satellite-ground distances.
The invention also provides a planet detection measurement and control communication method, which is used for ultra-long-distance communication scenes including Mars and Mars detection and comprises the following steps:
arranging 1 pair of low-gain antennas on the ground, and carrying out near-field communication and emergency communication under the condition of abnormal attitude of a far-field by the two pairs of low-gain antennas;
arranging 1 pair of middle gain antennas on the ground, and carrying out measurement and control communication when the attitude of a remote area slightly deflects by the middle gain antennas;
arranging 1 pair of high-gain antennas on the ground, and carrying out measurement and control communication on the high-gain antennas when the attitude of a remote area is accurate to the ground;
the high-low two-gear transmitting power of the two power amplifiers is set, low power is set during near-field communication, and high power is set during far-field communication.
The planet detection measurement and control communication system provided by the invention comprises 4 pairs of antennas, wherein each pair of antennas can be used for transmitting and receiving signals at the same time, 3 pairs of antennas are used for satellite-ground communication under the condition of normal posture, and 1 pair of antennas are used for emergency communication under the condition of abnormal posture; 2 pairs of antennas in the 4 pairs of antennas are low-gain antennas, 1 pair of antennas are medium-gain antennas, and 1 pair of antennas are high-gain antennas, so that the system can support measurement and control communication in various distance ranges respectively, and meets ultra-long-distance communication scenes including Mars and Mars detection. The invention completes the improved design aiming at the defects at present, can meet the measurement and control communication requirements of a deep space exploration task on the premise of meeting the requirements of a small satellite on high integration, low power consumption, miniaturization and light weight of a platform, simplifies the system complexity to the maximum extent, has the function of backup switching of a measurement and control channel, and ensures the reliability of a measurement and control system. The invention and the idea have reference significance for other deep space exploration spacecrafts.
In the planetary detection measurement and control communication system provided by the invention, measurement and control communication in various distance ranges can be respectively supported through selection of 4 pairs of antennas and selection of output power of two power amplifiers, and ultra-long-distance communication scenes including Mars and Mars detection are met. And 4 pairs of antennas can be simultaneously used for transmitting and receiving signals, wherein 3 pairs of antennas are used for satellite-ground communication under the normal attitude condition, and 1 pair of antennas are used for emergency communication under the abnormal attitude condition. 2 of the 4 pairs of antennas are low-gain antennas, 1 is a medium-gain antenna, and 1 is a high-gain antenna. The high isolation duplexer ensures that each antenna can be used for both transmitting and receiving signals. Two power amplifiers all set up two grades of transmission power of height: the low power is used for near-field communication to protect ground deep space measurement and control system equipment; high power is used for remote communications to ensure adequate transmission EIRP. The invention completes the improved design aiming at the defects at present, can meet the measurement and control communication requirements of a deep space exploration task on the premise of meeting the requirements of high integration, miniaturization and light weight of a small satellite on a platform, simplifies the system complexity to the maximum extent, has the function of backup switching of a measurement and control channel, and ensures the reliability of a measurement and control system. The invention and the idea have reference significance for other deep space exploration spacecrafts.
Drawings
FIG. 1 is a schematic diagram of a satellite sounding measurement and control communication system in accordance with an embodiment of the present invention.
Detailed Description
The planetary detection, measurement and control communication system provided by the invention is further described in detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
The invention provides a planetary exploration measurement and control communication system, which aims to solve the problem that the existing deep space exploration small satellite measurement and control communication system is difficult in satellite body layout.
The invention aims to provide a planetary detection measurement and control communication system to solve the problems that the existing scheme cannot realize miniaturization and low cost due to the fact that the number of antennas and power amplifiers is large, and the star body layout is difficult.
The invention also aims to provide a planetary detection measurement and control communication system to solve the problems that part of medium-high gain antennas cannot be used for receiving, the antenna gain is small, ultra-long distance communication cannot be supported, cross connection backup cannot be realized between a transmitting channel and a high-power amplifier, omnidirectional beam coverage cannot be formed during emergency communication and the like in the existing scheme.
In order to realize the idea, the invention provides a planetary detection measurement and control communication system, which comprises: 4 pairs of antennas, each antenna being operable to transmit and receive signals simultaneously; 1 pair of low-gain antennas are arranged on the ground, and 1 pair of low-gain antennas are arranged on the opposite sky; the two pairs of low-gain antennas are used for near-field communication and emergency communication under the condition of abnormal attitude of a far-field; 1 pair of middle gain antennas are arranged on the ground, and the middle gain antennas are used for measurement and control communication when the attitude of a remote area slightly deflects; 1 pair of high-gain antennas are arranged on the ground, and the high-gain antennas are used for measurement and control communication when the attitude of a remote area is accurate to the ground; two power amplifiers are both provided with high-low transmission power, a low-power amplifier is used for near-field communication, and a high-power amplifier is used for far-field communication.
The composition of the deep space exploration small satellite measurement and control communication system is shown in figure 1, and the product matching is shown in table 1. The measurement and control communication system is composed of a deep space transponder A29, a deep space transponder B30, a transmitting microwave network 28, a power amplifier A (25), a power amplifier B (26), a duplexer A (23), a duplexer B (24), a multiplexing memory A/B (31), a receiving microwave network 27, a double-pole double-throw microwave switch 22, a single-pole triple-throw microwave switch 21, 2 pairs of low-gain antennas (including an earth low-gain antenna 11 and an earth low-gain antenna 12), 1 pair of earth medium-gain antennas 13 and 1 pair of earth high-gain antennas 14.
TABLE 1 corollary table for measurement and control communication system products
| Name of single machine | Number of | Remarks for note |
| UXB Transponder A | 1 | |
| UXB Transponder B | 1 | |
| Power amplifier A | 1 | Two-gear transmitting power |
| Power amplifier B | 1 | Two-gear transmitting power |
| Duplexer A | 1 | |
| Duplexer B | 1 | |
| Multiplexing memory A/B | 1 | With data pressureShrinking function |
| (receiving) microwave network | 1 | |
| (transmitting) microwave network | ||
| Double-pole double-throw microwave switch | 1 | |
| Single-pole three-throw microwave switch | 1 | |
| Low gain antenna | 2 | One for each day and one for each earth |
| Medium gain antenna | 1 | To the ground |
| High gain directional antenna | 1 | To the ground |
The invention has 4 pairs of antennas in total, each pair of antennas can be used for both transmission and reception; the system comprises a ground plane, a pair of antennas and a plurality of communication modules, wherein the pair of antennas 3 is arranged on the ground plane and used for satellite-ground communication under the normal attitude condition, and the pair of antennas 1 is arranged on the ground plane and used for emergency communication under the abnormal attitude condition; the antenna is provided with low, medium and high three-gear gains which are respectively used for supporting measurement and control communication in different distance ranges.
The duplexer has the transmitting-receiving isolation as high as 120dBc, the weight is basically equivalent to that of a pair of low-gain antennas, the transmitting-receiving sharing of all the antennas can be realized, the number of the antennas is reduced, and the surface layout pressure of the star is reduced. The duplexer is widely applied to foreign deep space detectors, including a Juno of a NASA (national advanced satellite System architecture) Mars detector, a Mars detector Phoenix and the like.
In combination with the conventional practical situation of emission and the foreign development trend, the emission section of the emission organ is not provided with a low-power (0.5W/1W) emission mode, so that only two high-power amplifiers are arranged, and the system cost and the volume weight are reduced.
A transmitting microwave network 28 is arranged between the transmitting channels of the two answering machines and the two large power amplifiers, and can provide a cross connecting channel. The double-point fault of any transmitting channel (including the digital baseband part) and any large power amplifier can be resisted, and the whole system can work as long as any transmitting channel and large power amplifier can work. Because the microwave network is before the big power amplifier, its insertion loss does not influence the final transmission power, can not influence system transmission EIRP.
A receiving microwave network 27 is arranged between the receiving channels and the antennae of the two answering machines, remote control signals received by any pair of antennae can enter the receiving channels of the two answering machines, namely, any answering machine can receive the signals of any pair of antennae, the situation of posture overturning or the fault of the receiving channel of one answering machine can be effectively coped with, and the reliability of a remote control link is improved. The ground transmission EIRP is generally very large, and the ability to continue increasing the transmission power under emergency conditions (the satellite has only a low-gain antenna facing the earth) is reserved, which can effectively make up for the uplink insertion loss caused by the receiving microwave network 27.
The deep space transponder is based on the concept of software radio, and the remote measurement and control support multi-gear speed and are used for supporting measurement and control communication under the conditions of different satellite-ground distances. And remotely receiving the transmission rate of the self-adaptive ground station, and switching the remote transmission rate according to instruction information planned by the spaceborne computer or sent by the ground. The telemetering and remote control adopts a channel error correction coding technology, and the link margin is further improved.
The deep space transponder is a shaped product and is suitable for deep space exploration projects with any satellite-ground distance, such as asteroid exploration, mars exploration, wooden star exploration and the like. The receiving sensitivity of the responder is up to-155 dBm to-157 dBm, and the transmitting power is 0 dBm. Different deep space exploration items only need to adaptively adjust the antenna gain and the power amplifier transmitting power of the scheme.
The deep space transponder adopts a sidetone ranging system and simultaneously has the function of sending DOR beacon signals, and the DOR beacon signals are modulated on a telemetering main carrier as subcarrier signals. Whether the DOR beacon signal is sent or not is controlled by a ground control command.
The deep space transponder has a data transmission function besides a telemetering transmission function supporting ranging, and can realize high-speed satellite-ground transmission of payload data.
The multiplexing memory is connected with the load 50 to complete the functions of receiving, storing and multiplexing and framing a plurality of load data, and meanwhile, the multiplexing memory has a data compression function and reduces the satellite-ground data transmission pressure. The multi-path multiplexing memory can select whether to multiplex the whole satellite telemetering data into the data transmission data according to the ground remote control instruction, and the function of single transmission load data or the mixed transmission of the load data and the telemetering data is realized. The deep space transponder selects to send the low-speed telemetering data (needing channel coding) from the satellite computer 40 or the high-speed data transmission data from the multiplexing memory 31 in a downlink mode according to the ground remote control instruction, and the low-speed telemetering data from the satellite computer 40 is sent by default when the deep space transponder is powered on initially.
The operation modes supported by the measurement and control communication system are shown in table 2.
TABLE 2 measurement and control communication system working mode table
Wherein, TC: remote control; TM: UXB telemetry (rate adjustable); r: and (6) ranging.
In one embodiment of the present invention, the main technical indicators of the communication system are as follows (the following technical indicators can be adjusted according to the requirements):
remote control information rate: 7.8125bps, 50bps, 500bps, 1000bps, 2000bps
Remote control channel coding mode: (7,1/2) convolutional code
Telemetry information rate: 8bps, 64bps, 128bps, 512bps, 2048bps
Telemetry channel coding mode: RS + (7,1/2) convolutional code
Data transfer information rate: 30kbps, 100kbps, 200kbps
Data transmission channel coding mode: RS + (7,1/2) convolutional code
Power amplifier output power 10W/70W (10W for near field and cruise early stage)
Low-gain antenna: the receiving gain is more than or equal to-2 dBi within the range of +/-75 DEG
The medium gain antenna: the receiving gain is more than or equal to 8dBi within the range of +/-20 degrees, and the transmitting gain is more than or equal to 9dBi
High gain antenna: the receiving and sending gain is more than or equal to 37dBi within the range of +/-0.5 DEG
The satellite-ground communication distances supported by different types of antennas are shown in tables 3-8, and a ground measurement and control station adopted by link calculation is a 66m Canius station;
TABLE 3 remote control Link Performance budget (Low gain antenna)
TABLE 4 remote control Link Performance budget (middle gain antenna)
TABLE 5 telemetry Link Performance (Low gain antenna)
| Distance/km | 1200 | 2500 | 5000 | 7000 | 20000 |
| Telemetry code rate/bps | 2048 | 512 | 128 | 64 | 8 |
TABLE 6 telemetry Link Performance (middle gain antenna)
| Distance/km | 4500 | 9000 | 18000 | 25000 | 70000 |
| Telemetry code rate/bps | 2048 | 512 | 128 | 64 | 8 |
TABLE 7 telemetry Link Performance (high gain antenna)
| Distance/km | 100000 (wooden star) |
| Telemetry code rate/bps | 2048 |
Table 8 data transmission link performance (high gain antenna)
| Distance/km | 15000 | 20000 | 40000 (Mars) |
| Data transfer code rate/kbps | 200 | 100 | 30 |
In summary, the above embodiments describe in detail different configurations of the planetary probing, measurement and control communication system, and it goes without saying that the present invention includes but is not limited to the configurations listed in the above embodiments, and any modifications made on the configurations provided in the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (10)
1. A planetary detection measurement and control communication system is characterized by comprising:
the two power amplifiers are configured to be respectively provided with high-level and low-level transmitting power, wherein the low power is used for near-field communication to protect ground deep space measurement and control system equipment, and the high power is used for far-field communication to ensure enough EIRP (equivalent interference rejection ratio);
4 antennas, each configured to be capable of simultaneously transmitting and receiving a signal;
a high isolation duplexer configured to ensure that each of the secondary antennas can be used for transmitting and receiving signals simultaneously;
wherein, the selection is carried out in 4 pairs of antennas, and the output power of the two power amplifiers is selected, so as to respectively carry out the measurement and control communication in various distance ranges.
2. The planetary detection, measurement and control communication system of claim 1, further comprising:
a transmitting microwave network is arranged between the transmitting channels of the two answering machines and the two large power amplifiers to provide a cross connecting channel to resist double-point faults of any one transmitting channel and any one large power amplifier, and the insertion loss of the microwave network does not influence the final transmitting power before the large power amplifiers;
a receiving microwave network is arranged between the receiving channels and the antennas of the two answering machines, and remote control signals received by any pair of antennas enter the receiving channels of the two answering machines, so that the situation of posture overturning or the fault of the receiving channel of one answering machine is effectively dealt with.
3. The planetary detection, measurement and control communication system according to claim 2, wherein the two transponders are deep space transponders based on software radio, and both the remote measurement and control support multi-gear speed for supporting measurement and control communication under different satellite-to-ground distances;
the remote control receives the transmission rate of the self-adaptive ground station, the remote control transmission rate is switched according to the instruction information planned by the spaceborne computer or sent by the ground, and the remote control both adopt a channel error correction coding technology;
the receiving sensitivity of the responder is-155 dBm to-157 dBm, the transmitting power is 0dBm, and the antenna gain and the power amplifier transmitting power are adaptively adjusted according to different deep space detection items;
the deep space responder adopts a sidetone ranging system and has the function of sending DOR beacon signals, and the DOR beacon signals are modulated on a telemetering main carrier as subcarrier signals; whether the DOR beacon signal is sent is controlled by a ground control instruction;
the deep space transponder has a telemetry transmission function supporting ranging, and is also provided with a data transmission function, so that high-speed satellite-ground transmission of payload data is realized.
4. The planetary detection, measurement and control communication system of claim 3, further comprising:
the first end of the deep space transponder A and the first end of the deep space transponder B are both connected with the second end of the receiving microwave network;
the first end of the deep space transponder A and the first end of the deep space transponder B are both connected with the second end of the transmitting microwave network;
the second end of the deep space transponder A and the second end of the deep space transponder B are both connected with a house service computer;
and the second end of the deep space transponder A and the second end of the deep space transponder B are both connected with a multiplexing memory A and a multiplexing memory B.
5. The planetary exploration measurement and control communication system according to claim 4, wherein the deep space transponder A and the deep space transponder B are capable of employing a plurality of telemetry and remote control rates for supporting measurement and control communication at a plurality of satellite-to-ground distances;
and the deep space transponder A and the deep space transponder B carry out high-speed satellite-ground transmission of payload data in a data transmission mode.
6. The planetary probing, measurement and control communication system according to claim 5 wherein the multiplexing storage A and the multiplexing storage B receive, store, compress and frame multiple payload data;
and the multi-path multiplexing memory A and the multi-path multiplexing memory B select whether the whole-satellite low-speed telemetering data is multiplexed into the high-speed data transmission data according to the ground remote control instruction so as to carry out independent transmission of load data or carry out mixed transmission of the load data and the telemetering data.
7. The planetary probing, measuring and controlling communication system according to claim 6, wherein the deep space transponder A and the deep space transponder B selectively send the whole satellite low-speed telemetry data from the satellite computer or send the high-speed data from the multi-way multiplexing storage A or the multi-way multiplexing storage B in a downlink manner according to the ground remote control command, and the low-speed telemetry data from the satellite computer is sent by default when the system is initially powered on.
8. The planetary probe measurement and control communication system of claim 1, wherein in 4 antennas,
the 3 pairs of antennas are used for satellite-ground communication under the condition of normal attitude, and the 1 pair of antennas are used for emergency communication under the condition of abnormal attitude;
2 of the 4 pairs of antennas are low-gain antennas, 1 of the 4 pairs of antennas are medium-gain antennas, and 1 of the 4 pairs of antennas are high-gain antennas, so as to support measurement and control communication in various distance ranges respectively;
the receiving and transmitting gain of the low-gain antenna within the range of +/-75 degrees is more than or equal to-2 dBi;
the receiving gain of the medium gain antenna is more than or equal to 8dBi within the range of +/-20 degrees, and the transmitting gain is more than or equal to 9 dBi;
the receiving and transmitting gain of the high-gain antenna is more than or equal to 37dBi within the range of +/-0.5 degrees.
9. The planetary detection, measurement and control communication system of claim 8, further comprising a double-pole double-throw microwave switch and a single-pole triple-throw microwave switch, wherein:
the ground high-gain antenna, the ground medium-gain antenna and the ground low-gain antenna are respectively connected with the first end of the single-pole triple-throw microwave switch;
the ground low-gain antenna and the second end of the single-pole three-throw microwave switch are respectively connected with the first end of the double-pole double-throw microwave switch;
in the near field, the single-pole triple-throw microwave switch is switched to the ground low-gain antenna, the ground low-gain antenna and the antenna form an omnidirectional covering beam together, and ground measurement and control communication is realized under the condition of any posture;
in a remote section, the single-pole triple-throw microwave switch is switched to a gain antenna in the ground or a high gain antenna in the ground, and the single-pole triple-throw microwave switch is respectively used for measurement and control communication when the attitude deflection is smaller than the beam width of the gain antenna in the ground and accurate ground; if the attitude deflection is larger than the beam width of the gain antenna in the ground, the antenna is completely inverted or even rolled, the single-pole three-throw microwave switch is switched to the antenna with low gain to form an omnidirectional covering beam, and the low-code-rate emergency communication is carried out.
10. The planetary detection, measurement and control communication system according to claim 9, wherein a second end of the double-pole double-throw microwave switch is connected to a first end of a duplexer a and a first end of a duplexer B, respectively, and the transmit-receive isolation of the duplexer a and the duplexer B is up to 120 dBc;
the second end of the duplexer A is respectively connected with the first end of the power amplifier A and the first end of the receiving microwave network;
the second end of the duplexer B is respectively connected with the first end of the power amplifier B and the first end of the receiving microwave network;
and the second end of the power amplifier A and the second end of the power amplifier B are respectively connected with the first end of the transmitting microwave network.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115314066A (en) * | 2022-07-20 | 2022-11-08 | 中国科学院微小卫星创新研究院 | Measurement and control communication device and method for deep space exploration spacecraft |
| CN116094579A (en) * | 2023-04-07 | 2023-05-09 | 湖南鲸瓴智联信息技术有限公司 | High-low speed cooperative low-orbit satellite communication system and method |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113341368B (en) * | 2021-05-10 | 2022-09-27 | 上海航天电子有限公司 | DOR beacon generation method suitable for deep space exploration |
| CN113782944A (en) * | 2021-08-24 | 2021-12-10 | 上海卫星工程研究所 | Mars detector measurement and control communication antenna configuration system |
| CN113794501B (en) * | 2021-08-31 | 2023-08-08 | 上海卫星工程研究所 | Mars surrounding device microwave network device |
| CN113676247B (en) * | 2021-09-03 | 2022-08-12 | 上海卫星工程研究所 | Near-earth and far-earth power amplifier switching method and system adapting to deep space detection |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6020845A (en) * | 1993-11-19 | 2000-02-01 | Stanford Telecommunications, Inc. | Satellite for increasing the utility of satellite communication systems |
| CN102723982A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Full-coverage multi-channel multi-frequency band measuring and control system of deep space electric propulsion asteroid spacecraft |
| CN103490808A (en) * | 2013-08-12 | 2014-01-01 | 上海卫星工程研究所 | Satellite-borne S frequency band relay user terminal system and application method based on spread spectrum system |
| CN107328310A (en) * | 2017-06-26 | 2017-11-07 | 南京长峰航天电子科技有限公司 | Multiple target target ship TT＆C system |
| US20170373754A1 (en) * | 2016-06-27 | 2017-12-28 | Espacesynergy | System and method for communicating with deep space spacecraft using spaced based communications system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050063706A1 (en) * | 2003-09-22 | 2005-03-24 | Lockheed Martin Corporation | Deep space communications network |
| JP5659905B2 (en) * | 2011-03-29 | 2015-01-28 | 日本電気株式会社 | Microwave transmission apparatus for satellite installation, target area tracking method using the apparatus, and control program |
| CN103368638B (en) * | 2012-03-29 | 2016-08-24 | 中国科学院空间科学与应用研究中心 | A kind of TTC & DT Systems for deep space probe and method |
| CN112398506B (en) * | 2019-01-31 | 2022-09-02 | 上海微小卫星工程中心 | Satellite-ground/relay integrated measurement and control system |
-
2020
- 2020-07-23 CN CN202210224180.6A patent/CN114499647B/en active Active
- 2020-07-23 CN CN202010715137.0A patent/CN111786720B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6020845A (en) * | 1993-11-19 | 2000-02-01 | Stanford Telecommunications, Inc. | Satellite for increasing the utility of satellite communication systems |
| CN102723982A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Full-coverage multi-channel multi-frequency band measuring and control system of deep space electric propulsion asteroid spacecraft |
| CN103490808A (en) * | 2013-08-12 | 2014-01-01 | 上海卫星工程研究所 | Satellite-borne S frequency band relay user terminal system and application method based on spread spectrum system |
| US20170373754A1 (en) * | 2016-06-27 | 2017-12-28 | Espacesynergy | System and method for communicating with deep space spacecraft using spaced based communications system |
| CN107328310A (en) * | 2017-06-26 | 2017-11-07 | 南京长峰航天电子科技有限公司 | Multiple target target ship TT＆C system |
Non-Patent Citations (1)
| Title |
|---|
| 石雷;熊亮;宁金枝;窦骄;: "应用于深空探测的小卫星测控系统方案研究", 航天器工程, no. 06 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115314066A (en) * | 2022-07-20 | 2022-11-08 | 中国科学院微小卫星创新研究院 | Measurement and control communication device and method for deep space exploration spacecraft |
| CN115314066B (en) * | 2022-07-20 | 2023-10-27 | 中国科学院微小卫星创新研究院 | Measurement and control communication device and method for deep space exploration spacecraft |
| CN116094579A (en) * | 2023-04-07 | 2023-05-09 | 湖南鲸瓴智联信息技术有限公司 | High-low speed cooperative low-orbit satellite communication system and method |
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