CN111786720B - Measurement and control communication system and method for deep space exploration small satellite - Google Patents
Measurement and control communication system and method for deep space exploration small satellite Download PDFInfo
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- CN111786720B CN111786720B CN202010715137.0A CN202010715137A CN111786720B CN 111786720 B CN111786720 B CN 111786720B CN 202010715137 A CN202010715137 A CN 202010715137A CN 111786720 B CN111786720 B CN 111786720B
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Abstract
The invention provides a measurement and control communication system and a method for a deep space exploration small satellite, which are used for an ultra-long-distance communication scene including Mars and Jupiter exploration, and comprise the following steps: 4 pairs of antennas, 1 single-pole triple-throw microwave switch, 1 double-pole double-throw microwave switch, 2 duplexers, 2 power amplifiers, 2 microwave networks and 2 deep space answering machines. Each antenna can be used for transmitting and receiving signals simultaneously; wherein 1 pair of low-gain antennas, 1 pair of medium-gain antennas and 1 pair of high-gain antennas are arranged on the ground, and the other 1 pair of low-gain antennas are arranged on the opposite surface. 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; the middle gain antenna is used for measurement and control communication when the attitude of the remote area slightly deflects; the high-gain antenna is 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, low power is used for near-field communication, and high power is used for far-field communication.
Description
Technical Field
The invention relates to the technical field of deep space exploration, in particular to a measurement and control communication system and a measurement and control communication method for a deep space exploration small satellite.
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;
and 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 miniaturized 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 measurement and control communication system and a measurement and control communication method for a deep space exploration small satellite, and aims to solve the problems that miniaturization, low cost and difficult star body layout cannot be realized due to the fact that the number of antennas and power amplifiers is large in the existing scheme.
The invention also aims to provide a measurement and control communication system and a measurement and control communication method for a deep space exploration small satellite, so as to solve the problems that part of high-gain antennas in the existing scheme can not be used for receiving, the antenna gain is low, so that ultra-long-range communication can not be supported, cross connection backup can not be realized between a transmitting channel and a high-power amplifier, omnidirectional beam coverage can not be formed during emergency communication, and the like.
In order to solve the above technical problems, the present invention provides a measurement and control communication system and method for a deep space exploration small satellite, which is used in an ultra-long range communication scenario including mars and mars exploration, and comprises:
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.
Optionally, in the measurement and control communication system for a deep space exploration small satellite, 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 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.
Optionally, be arranged in the observing and controlling communication system of deep space exploration microsatellite, 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 measurement and control communication system for a deep space exploration microsatellite, the measurement and control communication system 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 separately connected with the first end of the transmitting microwave network.
Optionally, in the measurement and control communication system for a deep space exploration microsatellite, the measurement and control communication system 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 measurement and control communication system for a deep space exploration microsatellite, the measurement and control communication system 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 measurement and control communication system for a deep space exploration small satellite, the multiple-path multiplexing memory a and the multiple-path multiplexing memory B receive, store, compress, and multiplex framing 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 measurement and control communication system for detecting a small satellite in deep space, the deep space transponder a and the deep space transponder B select to send low-speed telemetry data of the whole satellite from a satellite computer in a downlink manner or send 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 default send the low-speed telemetry data from the satellite computer during initial power-on.
Optionally, in the measurement and control communication system for detecting a small satellite in deep space, the deep space transponder a and the deep space transponder B are shaped products, and are used for a deep space detection item of any satellite-ground distance, and adjusting antenna gain and power amplifier transmitting power to adapt to the deep space detection items of different satellite-ground distances.
The invention also provides a measurement and control communication method for the deep space exploration small satellite, which is used for an ultra-long-distance communication scene including Mars and Jupiter exploration 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 measurement and control communication system and the measurement and control communication method for the deep space exploration small satellite provided by the invention comprise 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 normal attitude condition, and 1 pair of antennas are used for emergency communication under the abnormal attitude condition; 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 high integration degree, low power consumption, 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.
According to the measurement and control communication system and method for the deep space exploration small satellite, measurement and control communication in various distance ranges can be 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 exploration are met. The 4 pairs of antennas can be used for transmitting and receiving signals simultaneously, 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 view of a measurement and control communication system for a deep space exploration moonlet according to an embodiment of the present invention.
Detailed Description
The following describes the measurement and control communication system and method for a deep space exploration moonlet according to the present invention in further 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 core idea of the invention is to provide a measurement and control communication system and a measurement and control communication method for a deep space exploration small satellite, so as to solve the problem that the conventional measurement and control communication system for the deep space exploration small satellite is difficult to arrange in a star body.
The invention aims to provide a measurement and control communication system and a measurement and control communication method for a deep space exploration small satellite, so as 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 measurement and control communication system and a measurement and control communication method for a deep space exploration small satellite, so as to solve the problems that part of medium-high gain antennas in the existing scheme can not be used for receiving, the antenna gain is small, ultra-long distance communication can not be supported, cross connection backup can not be realized between a transmitting channel and a high-power amplifier, omnidirectional beam coverage can not be formed during emergency communication, and the like.
In order to realize the thought, the invention provides a measurement and control communication system and a method for detecting a small satellite in deep space, which comprises the following steps: 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 |
| |
1 | |
| |
1 | |
| |
1 | Two-gear transmitting power |
| |
1 | Two-gear transmitting |
| Duplexer A | ||
| 1 | ||
| |
1 | |
| Multiplexing memory A/ |
1 | Having data compression function |
| (receiving) microwave network | 1 | |
| (transmitting) microwave network | ||
| Double-pole double- |
1 | |
| Single-pole three- |
1 | |
| Low gain antenna | 2 | One for each day and one for each earth |
| |
1 | To the ground |
| High gain |
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 large power amplifier, the insertion loss does not influence the final transmitting power and does not influence the 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 which can be 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 Canaus 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)
In summary, the above embodiments have described in detail different configurations of the measurement and control communication system and method for detecting a small satellite in deep space, and it is understood 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 (8)
1. A measurement and control communication system for a deep space exploration small satellite is used for an ultra-long-range communication scene including Mars and Jupiter exploration, and is characterized by comprising the following components:
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;
the two power amplifiers are both provided with high-low two-gear transmitting power, the low-power amplifier is used for near-field communication, and the high-power amplifier is used for far-field communication;
among the 4 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;
the second end of the double-pole double-throw microwave switch is respectively connected with the first end of a duplexer A and the first end of a duplexer B, and the receiving and transmitting isolation degree 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;
the second end of the power amplifier A and the second end of the power amplifier B are connected with the first end of the transmitting microwave network;
the receiving and transmitting gain of the low-gain antenna is more than or equal to-2 dBi within the range of +/-75 DEG
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 9dBi
The receiving and transmitting gain of the high-gain antenna is more than or equal to 37dBi within the range of +/-0.5 degrees.
2. The measurement and control communication system for deep space exploration microsatellites according to claim 1,
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.
3. The measurement and control communication system for a deep space exploration microsatellite according to claim 2 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.
4. The measurement and control communication system for a deep space exploration microsatellite according to claim 3 further comprising:
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.
5. The observing and controlling communication system for a deep space exploration small satellite according to claim 4, wherein the multiplexing storage A and the multiplexing storage B receive, store, compress and multiplex a plurality of 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.
6. The measurement and control communication system for the deep space exploration small satellite according to claim 4, wherein the deep space transponder A and the deep space transponder B select to send the whole satellite low-speed telemetry data from a satellite computer or send the high-speed data from the multiplexing storage A or the multiplexing storage B in a downlink mode according to a 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.
7. The measurement and control communication system for deep space exploration microsatellites according to claim 4, wherein the deep space transponder A and the deep space transponder B are shaped products for deep space exploration items at any satellite-ground distance, and antenna gain and power amplifier transmitting power are adjusted to adapt to the deep space exploration items at different satellite-ground distances.
8. A measurement and control communication method for a deep space exploration small satellite is used for an ultra-long-distance communication scene including Mars and Jupiter exploration, and is characterized by comprising 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;
setting high-low two-gear transmitting power of two power amplifiers, setting low power during near-field communication, and setting high power during far-field communication;
among the 4 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;
the second end of the double-pole double-throw microwave switch is respectively connected with the first end of a duplexer A and the first end of a duplexer B, and the receiving and transmitting isolation degree 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;
the second end of the power amplifier A and the second end of the power amplifier B are separately connected with the first end of the transmitting microwave network;
the receiving and transmitting gain of the low-gain antenna is more than or equal to-2 dBi within the range of +/-75 DEG
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 9dBi
The receiving and transmitting gain of the high-gain antenna is more than or equal to 37dBi within the range of +/-0.5 degrees.
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| 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 |
| CN113782944B (en) * | 2021-08-24 | 2024-09-24 | 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 |
| 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 |
| CN116094579B (en) * | 2023-04-07 | 2023-06-30 | 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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