Signal enhancement method and device based on low earth orbit satellite and satellite

Abstract

The embodiment of the invention relates to the technical field of satellite communication, and provides a signal enhancement method and device based on a low earth orbit satellite, and the satellite, and the method comprises the steps: receiving a first inbound signal sent by a terminal; obtaining an inbound message based on the first inbound signal; generating a second inbound signal based on the inbound message; the signal power of the second inbound signal is greater than that of the first inbound signal; and sending the second inbound signal to the high-orbit satellite. Therefore, the signal transmitted by the terminal at the lower transmitting power can also be indirectly transmitted to the high-orbit satellite, so that the requirement on the transmitting power of the terminal is reduced, and the power-limited terminal can also use the service provided by the high-orbit satellite. In the process of regenerating the inbound signal, the symbol rate and the coding rate can be improved, so that the spectrum efficiency and the user experience are improved.

Description

A signal enhancement method, device, and satellite based on low-Earth orbit satellites Technical Field

[0001] The embodiments in this specification relate to the field of satellite communication technology, and in particular to a signal enhancement method, apparatus and satellite based on low-Earth orbit satellites. Background Technology

[0002] BeiDou short message service is a unique feature of the BeiDou Navigation Satellite System that distinguishes it from other satellite navigation systems. It provides functions such as short message communication, location reporting, and emergency search and rescue. During the large-scale application of BeiDou, a significant number of terminals, such as IoT data acquisition devices and short message wristwatches, have strict power consumption constraints. This prevents these low-power devices from using the BeiDou short message service, thus hindering its widespread adoption. Summary of the Invention

[0003] The purpose of the embodiments in this specification is to provide a signal enhancement method, apparatus and satellite based on low-Earth orbit satellites, so that the information carried by the signal transmitted by a power-limited terminal at a lower transmission power can also be indirectly transmitted to a high-Earth orbit satellite, so that the power-limited terminal can also use the services provided by the high-Earth orbit satellite.

[0004] To achieve the above objectives, in one aspect, embodiments of this specification provide a signal enhancement method based on low-Earth orbit (LEO) satellites, applied to LEO satellites, the method comprising:

[0005] The first inbound signal sent by the receiving terminal;

[0006] Based on the first inbound signal, obtain the inbound message;

[0007] Based on the inbound message, a second inbound signal is generated; the signal power of the second inbound signal is greater than the signal power of the first inbound signal.

[0008] The second arrival signal is sent to the high-orbit satellite.

[0009] In the signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification, the coding code rate of the second incoming signal is higher than the initial coding code rate of the first incoming signal, and / or the symbol rate of the second incoming signal is higher than the symbol rate of the first incoming signal.

[0010] In the signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification, before generating the second inbound signal based on the inbound message, the method further includes:

[0011] Determine whether the inbound message meets the redundancy condition; wherein, the redundancy condition includes that the sender identifier of the inbound message is consistent with the sender identifier of at least one other low-orbit satellite received message, and the difference in receiving satellite time is less than the time window threshold.

[0012] If it is determined that the inbound message does not meet the redundancy condition, the step of generating the second inbound signal based on the inbound message is executed.

[0013] The signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification also includes:

[0014] If the inbound message meets the redundancy conditions, determine whether to select this satellite as the relay satellite according to the predetermined satellite selection strategy.

[0015] If the satellite is determined to be a relay satellite, the step of generating the second inbound signal based on the inbound message is performed.

[0016] In the signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification, the step of determining whether to select the local satellite as a relay satellite according to a predetermined satellite selection strategy includes:

[0017] Low-Earth orbit satellites that meet the aforementioned redundancy conditions will be used to form a candidate satellite set.

[0018] Determine the first link quality parameters of this satellite relative to the high-orbit satellite, and the second link quality parameters of each candidate satellite relative to the high-orbit satellite;

[0019] If the first link quality parameter is better than the second link quality parameter, the satellite is determined to be a relay satellite.

[0020] In the signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification, the first link quality parameter includes the first visible elevation angle of each beam of the local satellite relative to the high-Earth orbit satellite;

[0021] The second link quality parameter includes the second visible elevation angle of each candidate satellite relative to each beam of the high-orbit satellite;

[0022] The first link quality parameter being superior to the second link quality parameter indicates that the minimum value of the first visible elevation angle is less than the minimum value of the second visible elevation angle.

[0023] In the signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification, the step of determining whether to select the local satellite as a relay satellite according to a predetermined satellite selection strategy includes:

[0024] Low-Earth orbit satellites that meet the aforementioned redundancy conditions will be used to form a candidate satellite set.

[0025] Determine whether the satellite meets the optimal link establishment timing condition; the optimal link establishment timing condition is characterized by: relative to each of the candidate satellites, the satellite has the earliest link establishment start time or the longest remaining link maintenance time with the high-orbit satellite;

[0026] If the satellite meets the optimal timing conditions for link establishment, it will be selected as the relay satellite.

[0027] In the signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification, the step of generating a second inbound signal based on the inbound message includes:

[0028] The inbound message is parsed to obtain message data;

[0029] The message data is re-encoded based on a first encoding code rate to obtain a regenerated inbound message; the regenerated inbound message is encapsulated according to a target information format; the first encoding code rate is higher than the original encoding code rate of the inbound message;

[0030] Generate the basic signal for the target frequency band based on the regenerated inbound message;

[0031] The base signal is amplified by a power amplifier to obtain the second incoming signal.

[0032] The signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification further includes, before determining whether the inbound message meets the redundancy condition:

[0033] Determine the message type of the inbound message;

[0034] If the message type is an emergency message, skip the step of determining whether the inbound message meets the redundancy condition;

[0035] If the message type is not an emergency message, perform the step of determining whether the inbound message meets the redundancy condition.

[0036] In the signal enhancement method based on low-Earth orbit satellites provided in the embodiments of this specification, the terminal is a power-limited terminal, and the first incoming signal is a power-limited signal.

[0037] On the other hand, embodiments of this specification also provide a signal enhancement device based on low-Earth orbit satellites, applied to low-Earth orbit satellites, including:

[0038] The receiving module is used to receive the first inbound signal sent by the terminal;

[0039] The acquisition module is used to acquire the inbound message based on the first inbound signal;

[0040] A generation module is used to generate a second inbound signal based on the inbound message; the signal power of the second inbound signal is greater than the signal power of the first inbound signal.

[0041] The transmitting module is used to send the second arrival signal to the high-orbit satellite.

[0042] On the other hand, embodiments of this specification also provide a satellite, including:

[0043] At least one processor; and

[0044] At least one memory storing instructions that, when executed individually or jointly by the at least one processor, cause the satellite to perform the aforementioned low-Earth orbit satellite-based signal enhancement method.

[0045] On the other hand, embodiments of this specification also provide a computer storage medium storing instructions that, when executed individually or jointly by at least one processor of a computer device, cause the computer device to perform the aforementioned signal enhancement method based on low-Earth orbit satellites.

[0046] On the other hand, embodiments of this specification also provide a computer program product, which includes a computer program that, when executed by a processor, implements the above-described signal enhancement method based on low-Earth orbit satellites.

[0047] As can be seen from the technical solutions provided in the embodiments of this specification above, low-orbit satellites can capture power-limited signals sent by power-limited terminals to high-orbit satellites, regenerate and enhance them, and then send the regenerated signals to the high-orbit satellites.

[0048] This significantly reduces the requirements for transmission power, allowing signals transmitted by power-limited terminals at lower transmission power to be indirectly sent to high-orbit satellites, enabling power-limited terminals to use the services provided by high-orbit satellites. Attached Figure Description

[0049] To more clearly illustrate the technical solutions in the embodiments or prior art of this specification, the drawings used in the description of the embodiments or prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this specification. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In the drawings:

[0050] Figure 1 shows a flowchart of a signal enhancement method based on a low-Earth orbit satellite in some embodiments of this specification;

[0051] Figure 2 shows a system architecture diagram of the signal enhancement system in some embodiments of this specification;

[0052] Figure 3 shows a flowchart of a signal enhancement method based on a low-Earth orbit satellite in some other embodiments of this specification;

[0053] Figure 4 shows a flowchart of a signal enhancement method based on a low-Earth orbit satellite in some other embodiments of this specification;

[0054] Figure 5 shows a flowchart of a signal enhancement method based on a low-Earth orbit satellite in some other embodiments of this specification;

[0055] Figure 6 shows a structural block diagram of a satellite in some embodiments of this application.

[0056] [Explanation of Labels in the Attached Images]

[0057] 600, Satellite;

[0058] 610. Processor;

[0059] 620. Memory;

[0060] 630. Program;

[0061] 640. Transceiver;

[0062] 650. Antenna. Detailed Implementation

[0063] To enable those skilled in the art to better understand the technical solutions in this specification, the technical solutions in the embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this specification, and not all embodiments. Based on the embodiments in this specification, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of this specification.

[0064] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, data stored, data displayed, etc.) involved in the embodiments of this specification are all information and data that have been authorized and agreed upon by the user and have been fully authorized by all parties. That is, the acquisition, transmission, storage, use, and processing of data in the technical solution of this specification all comply with the relevant provisions of national laws and regulations.

[0065] In this specification, unless otherwise stated, "and / or" describes an association between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A alone, A and B simultaneously, or B alone, where A and B can be singular or plural. Furthermore, in this disclosure, unless otherwise stated, "multiple" means two or more. "At least one of the following" or similar expressions refer to any combination of these items, including any combination of single or plural items. For example, at least one of a, b, or c can represent: a, b, c, ab, ac, bc, or abc, where a, b, and c can be single or multiple.

[0066] In this specification, the expressions "greater than" or "less than" may be used to determine whether a specific condition is met. However, this is only for illustrative purposes and is not intended to exclude statements of "above" or "below". A condition described as "above" may be replaced by "greater than", a condition described as "below" may be replaced by "less than", and a condition described as "above and less than" may be replaced by "greater than and below". Furthermore, hereinafter, "A" to "B" represent at least one of the elements from A (inclusive) to B (inclusive).

[0067] In the embodiments of this specification, the singular forms "a," "the," etc., including the plural forms, should be broadly understood as "a kind" or "a class" rather than limited to the meaning of "an." Furthermore, the term "described" should be understood to include both the singular and plural forms, unless the context clearly indicates otherwise. Additionally, the term "according to" should be understood as "at least partially based on…," and the term "based on" should be understood as "at least partially based on…," unless the context clearly indicates otherwise.

[0068] This specification provides the operational steps of the methods described in the embodiments or flowcharts, but based on conventional or non-inventive labor, more or fewer operational steps may be included. The order of steps listed in the embodiments is merely one possible execution order among many and does not represent the only possible execution order. In actual system or device products, the methods shown in the embodiments or drawings can be executed sequentially or in parallel.

[0069] It should be noted that in the embodiments of this specification, certain software, components, models and other existing solutions in the industry may be mentioned. These should be regarded as exemplary and are only intended to illustrate the feasibility of implementing the technical solutions in this specification. However, they do not mean that the applicant has used or necessarily used such solutions.

[0070] This application uses terminology used in some communication specifications (such as 3GPP, the European Telecommunications Standards Institute (ETSI), Extensible Radio Access Network (ERAN), and Open Radio Access Network (ORAN)) to describe various embodiments, but this is merely illustrative. The various embodiments of this application can also be readily modified and applied in other communication systems.

[0071] In the embodiments of this application, communication between devices in the communication system can be carried out according to communication protocols at any stage, such as including but not limited to the following communication protocols: 1G (generation), 2G, 2.5G, 2.75G, 3G, 4G, 4.5G and 5G, New Radio (NR) and / or other currently known or future communication protocols.

[0072] For ease of understanding, the technical terms involved in the embodiments of this application will be explained below.

[0073] Terminal device: refers to a device with wireless transceiver capabilities that can cooperate with network-side equipment to provide communication services to users. Terminal devices can also be called terminals, user equipment (UE), user terminals, mobile terminals (MT), or user agents, etc. For example, terminal devices can be mobile phones, tablets, laptops, wearable devices, virtual reality (VR) devices, augmented reality (AR) devices, wireless communication devices, wireless terminals in industrial control, wireless terminals in self-driving, wireless terminals in remote medical surgery, wireless terminals in smart grids, wireless terminals in transportation safety, wireless terminals in smart cities, wireless terminals in smart homes, Internet of Things (IoT) devices, narrowband Internet of Things (NB IoT) devices, vehicle-to-everything (V2X) devices, devices in device-to-device communication (D2D), enhanced machine-type communication (eMTC) devices, reduced capability (RedCap) devices, cellular phones, cordless phones, and session initiation protocols. Protocol (SIP) phones, Wireless Local Loop (WLL) stations, Personal Digital Assistants (PDAs), clients, handheld devices with wireless communication capabilities, in-vehicle devices, or shipboard devices, etc.

[0074] In scenarios such as the Internet of Things (IoT), terminal devices can also be machines or devices used for monitoring or measurement, including but not limited to: machine-type communication (MTC) terminals, vehicle-mounted communication terminals, device-to-device terminals, machine-to-machine (M2M) terminals, and so on.

[0075] In related technologies, methods such as adopting low communication levels, low communication frequencies, and designing new inbound signal systems are used to balance performance indicators such as power consumption, inbound rate, and inbound success rate, in order to meet the requirements of miniaturization and long-term reliable operation of low-power short message communication terminals.

[0076] However, existing technical solutions that can meet the requirements of miniaturization and long-term reliable operation of low-power short message terminals have the following drawbacks: First, due to the inherent free space decay caused by the orbital altitude of Beidou satellites, the power consumption of the terminal cannot be significantly reduced; second, the low communication level and low communication frequency limit the system efficiency and cannot meet the needs of high-performance communication scenarios; third, the new communication system can only be technically optimized under the current design state of the Beidou short message system, and it is difficult to break through the existing limitations.

[0077] To address the problems existing in the prior art, this specification provides a signal enhancement method based on low-Earth orbit (LEO) satellites. Figure 1 shows a flowchart of the LEO satellite-based signal enhancement method in this specification. The order of steps listed in the embodiment is merely one possible execution order among many steps and does not represent the only possible execution order. In actual system or device products, the methods shown in the embodiment or the accompanying drawings can be executed sequentially or in parallel.

[0078] Specifically, as shown in Figure 1, the following steps may be included:

[0079] Step 101: Receive the first inbound signal sent by the receiving terminal.

[0080] Step 102: Based on the first inbound signal, obtain the inbound message.

[0081] Step 103: Based on the inbound message, generate a second inbound signal; the signal power of the second inbound signal is greater than the signal power of the first inbound signal.

[0082] Step 104: Send the second arrival signal to the high-orbit satellite.

[0083] In the embodiments of this specification, step 103 regenerates the second inbound signal based on the inbound message. During this process, the signal power of the second inbound signal is increased so that the signal power of the second inbound signal is increased to a level suitable for reception by high-orbit satellites.

[0084] Therefore, using the embodiments of this specification, the signal transmitted by the terminal only needs to be captured by a low-Earth orbit (LEO) satellite. After capturing the signal, the LEO satellite does not simply amplify the signal power, but instead uses a regenerative enhancement method. That is, it obtains the inbound message from the incoming signal (including demodulation and decoding steps), and then generates a new signal based on the inbound message (including re-encoding and modulation steps) to generate a signal that can be received by a high-Earth orbit (HEO) satellite, and eliminates the accumulated errors generated during signal transmission. Thus, the terminal can indirectly send signals to HEO satellites by transmitting signals with lower transmission power, which helps power-constrained terminals access the services provided by HEO satellites.

[0085] In some embodiments of this specification, the terminal is a power-limited terminal, and the first inbound signal is a power-limited signal.

[0086] Specifically, the signal enhancement method based on low-Earth orbit satellites provided in this specification is well-suited for communication service scenarios between power-constrained terminals and high-Earth orbit satellites. For example, the BeiDou short message service. The above application scenarios are for illustrative purposes only, and the embodiments in this specification do not limit the scope of the application.

[0087] Taking the BeiDou short message service as an example, the BeiDou short message service is a communication service provided by the BeiDou satellite navigation system, which allows users to send and receive short messages in areas where traditional mobile communication networks cannot be used via BeiDou satellites.

[0088] For BeiDou short message service, the inherent free space decay caused by the orbital altitude of BeiDou geostationary Earth Orbitsatellite (GEO) satellites prevents a significant reduction in terminal power consumption.

[0089] Power-constrained terminals (such as smartwatches / bands, smart glasses, ocean buoys, environmental monitoring devices, etc.) may not be able to meet the minimum transmission power requirements, thus making it impossible to use the BeiDou short message service. Alternatively, they may barely meet the minimum transmission power requirements, but can only compensate for the increased bit error rate caused by the low signal-to-noise ratio by reducing the symbol rate and using low code rate encoding.

[0090] By using the signal enhancement method based on low-Earth orbit satellites provided in this specification, low-Earth orbit satellites can capture power-limited signals sent by power-limited terminals to high-Earth orbit satellites, regeneratively enhance them, and then send the regenerated signals to high-Earth orbit satellites.

[0091] This significantly reduces the requirements for transmission power, allowing power-limited terminals to transmit signals at lower power, and the information they carry can still be indirectly sent to high-orbit satellites, enabling power-limited terminals to use services provided by high-orbit satellites, such as the BeiDou short message service.

[0092] Furthermore, for terminals that already meet the minimum transmission power requirements, i.e., terminals that already meet the transmission power requirements for direct connection to high-orbit satellites, after applying the method provided in this manual, they only need to directly connect to low-orbit satellites. Therefore, under the same transmission power, the symbol rate can be increased and high code rate encoding can be used, thereby improving spectrum efficiency and user experience.

[0093] The following describes the signal reception and new signal generation process in conjunction with the system architecture diagram. For example, refer to Figure 2, which is the system architecture diagram of the signal enhancement system provided in the embodiments of this specification. As shown in Figure 2, it includes a terminal, low-Earth orbit (LEO) satellites, high-Earth orbit (HEO) satellites, and a ground control station. LEO satellites can be connected via inter-satellite links (ISL). Incoming signal enhancement payloads are deployed in the LEO satellites. Specifically, the incoming signal enhancement payloads may include: a service control subsystem, an incoming signal reception and processing subsystem, and a regenerative transmission subsystem.

[0094] The inbound signal enhancement payload receives low-power inbound signals from the receiving terminal, performs signal acquisition, tracking, despreading, demodulation, and other processing, and obtains inbound messages.

[0095] For example, the inbound signal receiving and processing subsystem receives and processes signals transmitted by the terminal under the control of the service control subsystem. The inbound signal receiving and processing subsystem may specifically include an L-band receiving antenna, an L-band low-noise amplifier, a downconverter, a signal acquisition module, a signal capture module, and a signal processor, etc.

[0096] For example, the L-band receiving antenna receives the first incoming signal and sends it to the L-band low-noise amplifier; the L-band low-noise amplifier amplifies the signal and sends it to the downconverter; the downconverter downconverts the signal to the intermediate frequency and sends it to the signal acquisition module; the signal acquisition module converts the analog signal into a digital signal and sends it to the signal acquisition module and the signal processor in sequence; the signal acquisition module and the signal processor complete the acquisition, tracking, demodulation and decoding of the signal to obtain the incoming message.

[0097] After acquiring the inbound message, a second inbound signal is regenerated based on the inbound message. During the generation process, the signal power of the second inbound signal is increased to a level suitable for reception by high-orbit satellites.

[0098] As can be seen, by parsing the inbound and outbound messages and regenerating signals that can be received by high-orbit satellites, the terminal can indirectly send signals to high-orbit satellites by transmitting signals at a lower power. Furthermore, by parsing the inbound and outbound messages and regenerating the signals, the accumulated errors generated during signal transmission are eliminated.

[0099] In some embodiments of this specification, in the process of generating the second inbound signal, in addition to increasing the signal power, the coding code rate and / or symbol rate can also be increased. That is, the coding code rate of the second inbound signal is higher than the initial coding code rate of the first inbound signal, and / or, the symbol rate of the second inbound signal is higher than the symbol rate of the first inbound signal.

[0100] The first incoming signal, due to its low power, requires a low coding rate. The coding rate represents the ratio of the number of valid information bits transmitted per unit time to the total number of transmitted bits (valid information bits + redundancy check bits). Using a low coding rate provides stronger error correction capabilities, thus improving anti-interference ability; however, the increased number of redundant bits limits data transmission efficiency.

[0101] During the generation of the second incoming signal, due to the increase in signal power, the channel quality between the low-Earth orbit satellite and the high-Earth orbit satellite is higher than that between the power-limited terminal and the low-Earth orbit satellite. This can increase the coding rate, and by using a high coding rate, there are fewer redundant bits, thus improving data transmission efficiency.

[0102] Symbol rate, also known as symbol percentage, refers to the number of symbols transmitted per unit time. Power-constrained terminals, due to limited transmission power, use a lower symbol rate to transmit, that is, lengthening the transmission time of a single symbol and increasing the energy of each symbol to combat interference. Low-Earth orbit satellites, after parsing and correcting messages, obtain error-free information bits, and can subsequently use a higher symbol rate to further improve data transmission efficiency.

[0103] The steps for generating the second inbound signal are described below with reference to the accompanying diagram, Figure 3, and include:

[0104] Step 301: Parse the inbound message to obtain message data.

[0105] In this step, channel decoding is performed first. The decoding process uses redundancy check bits to correct bit errors generated during transmission, thereby obtaining error-free message data.

[0106] Step 302: Re-encode the message data based on the first encoding code rate to obtain a regenerated inbound message; the regenerated inbound message is encapsulated according to the target information format; the first encoding code rate is higher than the original encoding code rate of the inbound message.

[0107] In some embodiments of this specification, although the first inbound signal sent by the low-orbit satellite receiving terminal is directed to the high-orbit satellite, the information carried by the first inbound signal is directed to the high-orbit satellite. Therefore, the information format of the inbound message can follow the air interface protocol specification defined by the high-orbit satellite for inbound services.

[0108] Understandably, the information format of the inbound message may not follow the air interface protocol specification defined by the high-orbit satellite for inbound services. In this case, the low-orbit satellite can repackage the inbound message according to the target information format, so that the high-orbit satellite can normally receive the regenerated inbound message carried by the second inbound signal; the target information format follows the air interface protocol specification defined by the high-orbit satellite for inbound services.

[0109] Step 303: Generate the basic signal of the target frequency band based on the regenerated inbound message.

[0110] Step 304: Amplify the basic signal using a power amplifier to obtain the second incoming signal.

[0111] After channel coding is completed, the regenerated inbound message can be converted into an RF signal. In this process, the signal transmission power and / or transmission rate can be increased.

[0112] In some embodiments of this specification, the service control subsystem regenerates and arranges the parsed inbound messages, and increases the transmission rate and enhances the transmission power.

[0113] The specific steps include:

[0114] 1) Inbound information arrangement. Inbound messages to be sent are queued according to the order of receipt time or priority level.

[0115] 2) Signal regeneration. The service control subsystem completes the settings for high code rate encoding and high power transmission, and at the same time completes the calculation of Doppler frequency offset compensation based on the ephemeris of low-Earth orbit and high-Earth orbit satellites.

[0116] 3) Signal Transmission. The regenerative transmission subsystem completes signal encoding and spread spectrum modulation processing as described above, and transmits the second incoming signal to the high-orbit satellite. The specific steps are as follows: the regenerative transmission subsystem completes encoding and spread spectrum processing to form an intermediate frequency (IF) signal, which is then sent to an upconverter; the upconverter upconverts the IF signal to the L-band radio frequency (RF) band and sends it to a power amplifier; the power amplifier amplifies the L-band RF signal and sends it to the L-band transmitting antenna; the L-band transmitting antenna transmits the RF signal to the high-orbit satellite.

[0117] As shown in Figure 2, the high-orbit satellite receives the second incoming signal and can generate a downlink incoming signal to the ground control station via an L / C band transponder. If the ground control station needs to transmit a signal to the high-orbit satellite, it can also send an outgoing uplink signal to the high-orbit satellite via a C / S band outgoing link.

[0118] As can be seen from the embodiments in this specification, a high-low orbit coordinated signal enhancement system is proposed, which significantly reduces the power consumption requirements of the terminal, promotes the large-scale application of power-limited terminals to services provided by high-orbit satellites, meets the requirements of terminal miniaturization and long-term reliable operation, and can significantly improve the communication performance of power-limited terminals. Because the inbound and outbound messages are parsed and the signals are regenerated, the accumulated errors generated during the transmission of signals sent by the terminal through the ground-to-satellite link are eliminated.

[0119] Furthermore, it can be designed based on the existing technical status of each segment of the system to the greatest extent possible, without requiring complex changes on the terminal side. The terminal can reduce the transmission power or increase the coding rate and symbol rate as needed, and no other adaptation is required, thus having good system compatibility.

[0120] In addition, the signal enhancement system of low-orbit satellites has no downlink transmission link, avoiding complex frequency interference problems and further ensuring the reception of power-limited signals.

[0121] In addition, reducing the terminal's transmission power can further alleviate the frequency interference problem of current satellite communication systems in the same frequency band.

[0122] In some embodiments of this specification, in beam overlap regions, signals transmitted by the same ground terminal may be received by multiple low-Earth orbit (LEO) satellites. If all LEO satellites receiving the same message send messages to high-Earth orbit (HEO) satellites, inbound message redundancy will occur. Therefore, redundancy processing is performed on inbound messages.

[0123] In some embodiments, after acquiring the inbound message based on the first inbound signal, the inbound message is parsed to obtain the sender identifier, which can be a user identifier or a device identifier. For example, the inbound message header carries the sender identifier, which is obtained by parsing the header.

[0124] The low-orbit satellite generates message identification information, including its own satellite number, the receiving time of the incoming signal, and the sender's identifier. Further redundancy processing of the incoming message is performed based on the message identification information.

[0125] In some embodiments, a low-Earth orbit (LEO) satellite transmits message identification information to neighboring LEO satellites via inter-satellite links. Correspondingly, the current LEO satellite also receives message identification information from other LEO satellites.

[0126] For example, a low-Earth orbit satellite determines whether the incoming messages it receives meet the redundancy conditions based on the message identification information corresponding to the incoming messages it receives and the message identification information from other low-Earth orbit satellites.

[0127] In the embodiments described in this specification, after receiving an inbound message, the current low-Earth orbit (LEO) satellite can determine whether the inbound message meets the redundancy conditions based on the currently received message identification information. Alternatively, it can wait for a preset interval period, during which message identification information from other LEO satellites is received. After the preset interval period has elapsed, the system can determine whether the inbound message meets the redundancy conditions. By introducing a preset interval period, a buffer time is provided for receiving message identification information, enabling a more accurate determination of whether the inbound message meets the redundancy conditions.

[0128] For example, redundancy conditions include the sender identifier of the inbound message being identical to the sender identifier of a message received by at least one other low-Earth orbit satellite, and the difference in reception time being less than a time window threshold. The time window threshold can be related to the message reception and processing delay, for example, it can be set to 500 ms.

[0129] If it is determined that the inbound message does not meet the redundancy conditions, then there is no need to process the redundant message; instead, the step of generating a second inbound signal based on the inbound message is directly executed.

[0130] Those skilled in the art will understand that when judging redundant messages in related technologies, the method is usually to identify the unique identifier in the message (such as the identifier field, the five-tuple information, etc.). That is, when multiple receivers receive messages carrying the same unique identifier field, it is determined that the message meets the redundancy condition.

[0131] In this embodiment, the redundancy condition is determined jointly based on the sender's identifier and the receiver's receiving satellite time difference. The redundancy condition includes: the sender's identifier of the incoming message is consistent with the sender's identifier of a message received by at least one other low-Earth orbit satellite, and the difference in receiving satellite time is less than a time window threshold. Using the redundancy judgment method provided in this embodiment has at least the following beneficial effects: 1) For some satellite service scenarios (e.g., BeiDou short message service), the message carries a user identifier but not a unique identifier. Therefore, using the redundancy judgment condition provided in this embodiment does not require adding extra fields to the existing design and does not increase communication overhead. 2) For some satellite service scenarios (e.g., BeiDou short message service), the sender's signal transmission interval is limited; the sender will not continuously transmit signals in a short period. Therefore, messages received by different low-Earth orbit satellites with the same sender identifier but a small difference in receiving satellite time can be judged as the same message, rather than different messages sent by the sender at small intervals, thus ensuring the accuracy of message redundancy judgment.

[0132] For example, for the BeiDou short message service, the sending interval of the sender is limited to more than 1 minute. If low-orbit satellite A receives message a1 and low-orbit satellite B receives message a2, and the sender identifiers of messages a1 and a2 are the same, and the difference in receiving satellite time is less than 100 milliseconds, then messages a1 and a2 must belong to the same message sent by the sender. Otherwise, the difference in receiving satellite time between the two is at least about one minute.

[0133] As can be seen, the embodiments in this specification fully consider the characteristics of long transmission intervals and limited communication resources in satellite service scenarios (such as BeiDou short message service). They adopt a method of redundancy condition judgment based on the sender's identifier and the receiver's receiving satellite time difference. Without increasing communication overhead and using the design framework of the existing system, it can also ensure accurate judgment of whether the message is redundant.

[0134] In some embodiments of this specification, if it is determined that the inbound message meets the redundancy condition, a predetermined satellite selection strategy is used to determine whether to select the local satellite as a relay satellite; if the local satellite is determined to be a relay satellite, the step of generating a second inbound signal based on the inbound message is performed.

[0135] For example, the satellite selection strategy is determined based on the link quality parameters or link establishment timing between low-Earth orbit satellites and high-Earth orbit satellites.

[0136] Referring to Figure 4, based on the predetermined satellite selection strategy, it is determined whether to select this satellite as a relay satellite, including:

[0137] Step 401: Form a candidate satellite set from the low-orbit satellites that meet the redundancy conditions.

[0138] In this step, for the incoming messages received by the current low-Earth orbit satellite (this satellite), a set of candidate satellites is determined. The set of candidate satellites includes candidate satellites that have received messages that are redundant with the incoming message.

[0139] Specifically, when the signal transmitted by the terminal is received by multiple low-Earth orbit satellites, these satellites identify the information through inter-satellite link messages. Based on predefined redundancy conditions, these multiple low-Earth orbit satellites that have received the same message are formed into a candidate satellite set. Each satellite in this set has the potential to generate a second inbound signal based on the message and forward it to a high-Earth orbit satellite.

[0140] Step 402: Determine the first link quality parameters of this satellite relative to the high-orbit satellite and the second link quality parameters of each candidate satellite relative to the high-orbit satellite.

[0141] For example, since both low-Earth orbit (LEO) and high-Earth orbit (HEO) satellites are constantly moving, changes in their relative positions can affect the link quality parameters between them.

[0142] Step 403: If the first link quality parameters are better than the second link quality parameters, determine this satellite as a relay satellite.

[0143] In some embodiments of this specification, each low-Earth orbit (LEO) satellite can synchronously transmit its link quality parameters with each high-Earth orbit (HEO) satellite to other LEO satellites via inter-satellite links. For the current satellite, the second link quality parameters of each candidate satellite relative to the HEO satellites can be obtained and compared with the first link quality parameters of the current satellite relative to the HEO satellites. If the first link quality parameters are superior to all the second link quality parameters, then the current satellite is determined to be a relay satellite.

[0144] In some embodiments of this specification, the link quality parameters between a low-Earth orbit (LEO) satellite and a high-Earth orbit (HEO) satellite can be measured by the visible elevation angle of each beam of the LEO satellite relative to the HEO satellite.

[0145] For example, based on its own ephemeris and the ephemeris and beam pointing information of high-orbit satellites (such as BeiDou GEO satellites), the satellite can calculate in real time the visibility and visible elevation angle of each beam relative to each high-orbit satellite.

[0146] For example, it can be used The visibility of the j-beam of a low-Earth orbit satellite k relative to a high-Earth orbit satellite i is represented by... This represents the visible elevation angle of the low-Earth orbit (LEO) satellite k relative to the high-Earth orbit (HEO) satellite i's j-beam. k represents the LEO satellite's designation; the designation of the LEO satellite itself is 0, and adjacent LEO satellites are numbered sequentially from smallest to largest relative to the LEO satellite's azimuth angle. i represents the HEO satellite's designation, and j represents the HEO satellite's beam designation.

[0147] For example, a visibility value of 0 indicates that the satellite is not visible, and a visibility value of 1 indicates that the satellite is visible. If the satellite is visible relative to a certain beam of a high-orbit satellite, the visible elevation angle of the satellite relative to that beam of the high-orbit satellite can be further calculated.

[0148] In some embodiments of this specification, the visible elevation angle measures the link quality parameter of the beam of a low-Earth orbit satellite relative to a high-Earth orbit satellite.

[0149] For this satellite, ephemeris information of other low-Earth orbit (LEO) satellites can be stored in advance. By combining the ephemeris information of other LEO satellites, the ephemeris information of high-Earth orbit (HEO) satellites, and the beam pointing information, the visibility and visible elevation angle of other LEO satellites relative to each HEO satellite can be calculated.

[0150] Then, by comparing the visible elevation angles, it is determined whether the local satellite possesses a communication link with the best link quality relative to high-orbit satellites. For example, the first link quality parameter includes the first visible elevation angle of the local satellite relative to each beam of the high-orbit satellite; the second link quality parameter includes the second visible elevation angle of each candidate satellite relative to each beam of the high-orbit satellite; the first link quality parameter being superior to the second link quality parameter indicates that the minimum value of the first visible elevation angle is less than the minimum value of the second visible elevation angle.

[0151] In some embodiments of this specification, to facilitate determining whether the local satellite possesses a communication link with the best link quality relative to high-orbit satellites, the local satellite can calculate the visible elevation angle of each low-orbit satellite relative to each beam of each high-orbit satellite in real time based on the low-orbit satellite ephemeris, high-orbit satellite ephemeris, and beam pointing information. Based on the calculated visible elevation angles, an inbound redundancy information decision table is maintained, which includes the visible elevation angle of low-orbit satellite k relative to the j beam of high-orbit satellite i. .

[0152] When determining whether a satellite possesses a communication link with the best quality relative to high-orbit satellites, the inbound redundancy information decision table can be retrieved based on the satellite's identification number and the identification numbers of each candidate satellite. The minimum visible elevation angle corresponding to the satellite and the minimum visible elevation angle corresponding to each candidate satellite can be determined. If the minimum visible elevation angle corresponding to the satellite is less than the minimum visible elevation angle corresponding to other candidate satellites, then the satellite is determined to possess a communication link with the best quality relative to high-orbit satellites, and thus the satellite is determined to be a relay satellite.

[0153] In the embodiments described in this specification, inbound messages are redundantly processed to ensure that for any given inbound message, only one low-Earth orbit satellite sends the corresponding second inbound signal to the high-Earth orbit satellite, avoiding duplicate message arrivals and wasting communication resources. Furthermore, based on the link quality of the communication link relative to the high-Earth orbit satellite, a suitable satellite is selected for signal transmission, ensuring that signals are always sent to the high-Earth orbit satellite via the path with the best quality, thus ensuring optimal signal transmission path.

[0154] By using ephemeris information, the visible elevation angle of each beam of a low-Earth orbit (LEO) satellite relative to a high-Earth orbit (HEO) satellite can be calculated, thereby assessing the communication link quality between LEO and HEO satellites. This eliminates the need for LEO satellites to transmit link quality information via inter-satellite links, which helps improve the efficiency of the local satellite's decision on whether to act as a relay satellite.

[0155] In some embodiments of this specification, referring to Figure 5, determining whether to select this satellite as a relay satellite according to a predetermined satellite selection strategy may include the following steps:

[0156] Step 501: Form a candidate satellite set from the low-orbit satellites that meet the redundancy conditions.

[0157] Step 501 is the same as step 401, and will not be repeated here.

[0158] Step 502: Determine whether the local satellite meets the optimal link establishment timing condition; the optimal link establishment timing condition is characterized by: relative to each of the candidate satellites, the local satellite has the earliest link establishment start time or the longest remaining link maintenance time with the high-orbit satellite.

[0159] For example, the earliest link establishment start time means that, relative to other low-Earth orbit satellites in the candidate set, the satellite is able to successfully establish an effective communication link with a high-Earth orbit satellite at the earliest start time.

[0160] Based on its own and neighboring satellites' ephemeris, the ephemeris of high-orbit satellites, and beam pointing, this satellite predicts the link establishment time between each low-orbit satellite and a high-orbit satellite, and then determines whether the satellite meets the requirements.

[0161] The longest remaining link duration indicates the longest remaining time that effective communication can be maintained between the satellite and the high-orbit satellite from the current decision time. The satellite predicts the link disconnection time between itself and its neighbors and the high-orbit satellite based on its own and its neighbors' ephemeris, the high-orbit satellite's ephemeris, and beam pointing, calculates the remaining duration, and then determines whether the satellite meets the condition.

[0162] Step 503: If the local satellite meets the optimal timing conditions for link establishment, determine the local satellite as the relay satellite.

[0163] After evaluation, if this satellite meets either of the two optimal link establishment timing conditions mentioned above, it will be designated as the relay satellite responsible for forwarding the message. Subsequently, this satellite will execute the inbound signal regeneration and transmission process.

[0164] For other candidate satellites in the candidate set, the same judgment logic is used to determine whether the satellite meets either of the two optimal link establishment timing conditions. If not, the message is discarded or temporarily stored to avoid duplicate transmission.

[0165] In the embodiments described in this specification, the low-Earth orbit satellite that can establish a link earliest is selected as the relay satellite, which means that the terminal's data packets can be uploaded to the high-Earth orbit satellite as quickly as possible. This is suitable for short messages that transmit only a small amount of data, as well as message transmissions that are extremely time-sensitive, such as emergency communications, emergency search and rescue, and real-time commands, and helps to improve the timeliness of message transmission.

[0166] In the embodiments described in this specification, the low-Earth orbit satellite with the longest remaining link duration is selected as the relay satellite to provide a more stable and generous time window for data transmission, thereby reducing the risk of failure due to sudden link interruption during data transmission.

[0167] In some embodiments of this specification, before determining whether an inbound message meets the redundancy condition, the method further includes: determining the message type of the inbound message; skipping the step of determining whether the inbound message meets the redundancy condition if the message type is an emergency message; and performing the step of determining whether the inbound message meets the redundancy condition if the message type is not an emergency message.

[0168] For example, the header of an inbound message may carry a message type indication field. The low-Earth orbit satellite determines the message type of the inbound message based on this indication field. If it is an emergency message, the redundant judgment steps are skipped.

[0169] This directly eliminates the processing latency caused by inter-satellite link interactions and decision table calculations. For scenarios such as emergency search and rescue, the saved time is crucial, enabling emergency information to be transmitted to high-orbit satellites with minimal latency.

[0170] Corresponding to the signal enhancement method based on low-Earth orbit satellites shown in Figure 1 above, this specification also provides a signal enhancement device based on low-Earth orbit satellites, which may include: a receiving module for receiving a first arrival signal sent by a terminal; an acquisition module for acquiring an arrival message based on the first arrival signal; a generation module for generating a second arrival signal based on the arrival message; the signal power of the second arrival signal is greater than the signal power of the first arrival signal; and a sending module for sending the second arrival signal to a high-Earth orbit satellite.

[0171] This specification also provides a satellite, as shown in FIG6. The satellite 600 may include a processor 610 (e.g., a central processing unit CPU) and a memory 620; the memory 620 is coupled to the processor 610. The memory 620 can store various data; in addition, it also stores an information processing program 630, and executes the program 630 under the control of the processor 610.

[0172] For example, processor 610 can be configured to execute a program to implement the signal enhancement method as described in the previous embodiment. For example, processor 610 can be configured to perform the following control: receive a first arrival signal sent by a terminal; perform signal enhancement processing on the first arrival signal to obtain a second arrival signal; and send the second arrival signal to a high-orbit satellite.

[0173] In addition, as shown in Figure 6, satellite 600 may also include a transceiver 640 and an antenna 650, etc.; the functions of the above components are similar to those in the prior art, and will not be described in detail here. It is worth noting that satellite 600 does not necessarily include all the components shown in Figure 6; in addition, satellite 600 may also include components not shown in Figure 6, which can be referred to in the prior art.

[0174] For ease of description, the above devices are described separately by function as various units. Of course, in implementing this application, the functions of each unit can be implemented in one or more software and / or hardware.

[0175] This specification also provides a computer storage medium storing instructions, wherein the instructions, when executed individually or jointly by at least one processor of a computer device, cause the computer device to perform the above-described signal enhancement method based on low-Earth orbit satellites.

[0176] This specification is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), computer-readable storage media, and computer program products of some embodiments. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processor to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processor, create means for implementing the functions specified in one or more blocks of the flowchart illustrations and / or one or more blocks of the block diagrams.

[0177] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processor to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means that implement the functions specified in one or more flowcharts and / or one or more block diagrams.

[0178] These computer program instructions may also be loaded onto a computer or other programmable data processor to cause a series of operational steps to be performed on the computer or other programmable device to produce a computer-implemented process, such that the instructions, which execute on the computer or other programmable device, provide steps for implementing the functions specified in one or more flowcharts and / or one or more block diagrams.

[0179] In a typical configuration, a computer device includes one or more processors (CPU), input / output interfaces, network interfaces, and memory.

[0180] Memory may include non-persistent storage in computer-readable media, such as random access memory (RAM) and / or non-volatile memory, such as read-only memory (ROM) or flash RAM. Memory is an example of computer-readable media.

[0181] Computer-readable media, including both permanent and non-permanent, removable and non-removable media, can store information using any method or technology. Information can be computer-readable instructions, data structures, program modules, or other data. Examples of computer storage media include, but are not limited to, phase-change memory (PRAM), static random-access memory (SRAM), dynamic random-access memory (DRAM), other types of random-access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, disk storage or other magnetic storage devices, or any other non-transferable medium that can be used to store information accessible by computer equipment. As defined in this specification, computer-readable media does not include transient media, such as modulated data signals and carrier waves.

[0182] Those skilled in the art will understand that the embodiments of this specification can be provided as methods, systems, or computer program products. Therefore, the embodiments of this specification can take the form of entirely hardware embodiments, entirely software embodiments, or embodiments combining software and hardware aspects. Furthermore, the embodiments of this specification can take the form of computer program products implemented on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0183] The embodiments described in this specification can be described in the general context of computer-executable instructions, such as program modules, that are executed by a computer. Generally, program modules include routines, programs, objects, components, data structures, etc., that perform a specific task or implement a specific abstract data type. The embodiments of this specification can also be practiced in distributed computing environments where tasks are performed by remote processors connected via a communication network. In distributed computing environments, program modules can reside in local and remote computer storage media, including storage devices.

[0184] It should also be understood that, in the embodiments of this specification, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this document generally indicates that the preceding and following related objects have an "or" relationship.

[0185] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments.

[0186] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the embodiments of this specification. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0187] The above description is merely an embodiment of this specification and is not intended to limit this specification. Various modifications and variations can be made to this specification by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this specification should be included within the scope of the claims of this specification.

Claims

1. A signal enhancement method based on low-Earth orbit satellites, applied to low-Earth orbit satellites, characterized in that, The method includes: receiving a first inbound signal sent by a terminal; obtaining an inbound message based on the first inbound signal; generating a second inbound signal based on the inbound message; the signal power of the second inbound signal being greater than the signal power of the first inbound signal; and sending the second inbound signal to a high-orbit satellite.

2. The method according to claim 1, characterized in that, The coding rate of the second inbound signal is higher than the initial coding rate of the first inbound signal, and / or the symbol rate of the second inbound signal is higher than the symbol rate of the first inbound signal.

3. The method according to claim 1, characterized in that, Before generating the second inbound signal based on the inbound message, the method further includes: determining whether the inbound message meets redundancy conditions; wherein, the redundancy conditions include that the sender identifier of the inbound message is consistent with the sender identifier of a message received by at least one other low-orbit satellite, and the difference in receiving satellite time is less than a time window threshold; if it is determined that the inbound message does not meet the redundancy conditions, the step of generating the second inbound signal based on the inbound message is performed.

4. The method according to claim 3, characterized in that, The method further includes: if it is determined that the inbound message meets the redundancy condition, determining whether to select the local satellite as a relay satellite according to a predetermined satellite selection strategy; if it is determined that the local satellite is selected as a relay satellite, performing the step of generating the second inbound signal based on the inbound message.

5. The method according to claim 4, characterized in that, The step of determining whether to select the local satellite as a relay satellite according to a predetermined satellite selection strategy includes: forming a candidate satellite set from low-orbit satellites that meet the redundancy conditions; determining the first link quality parameter of the local satellite relative to the high-orbit satellite and the second link quality parameter of each candidate satellite relative to the high-orbit satellite; and determining the local satellite as a relay satellite if the first link quality parameter is better than the second link quality parameter.

6. The method according to claim 5, characterized in that, The first link quality parameter includes the first visible elevation angle of the local satellite relative to each beam of the high-orbit satellite; the second link quality parameter includes the second visible elevation angle of each candidate satellite relative to each beam of the high-orbit satellite. The first link quality parameter being superior to the second link quality parameter indicates that the minimum value of the first visible elevation angle is less than the minimum value of the second visible elevation angle.

7. The method according to claim 4, characterized in that, The step of determining whether to select the local satellite as a relay satellite according to a predetermined satellite selection strategy includes: forming a candidate satellite set from low-orbit satellites that meet the redundancy conditions; determining whether the local satellite meets the optimal link establishment timing condition; the optimal link establishment timing condition is characterized by: the local satellite having the earliest link establishment start time or the longest remaining link maintenance time with the high-orbit satellite relative to each of the candidate satellites; and determining the local satellite as a relay satellite if it meets the optimal link establishment timing condition.

8. The method according to claim 1, characterized in that, The step of generating a second inbound signal based on the inbound message includes: parsing the inbound message to obtain message data; recoding the message data based on a first coding rate to obtain a regenerated inbound message; encapsulating the regenerated inbound message according to a target information format; the first coding rate being higher than the original coding rate of the inbound message; generating a base signal for a target frequency band based on the regenerated inbound message; and amplifying the base signal using a power amplifier to obtain the second inbound signal.

9. The method according to claim 3, characterized in that, Before determining whether the inbound message meets the redundancy condition, the method further includes: determining the message type of the inbound message; if the message type is an emergency message, skipping the step of determining whether the inbound message meets the redundancy condition; if the message type is not an emergency message, performing the step of determining whether the inbound message meets the redundancy condition.

10. The method according to any one of claims 1-9, characterized in that, The terminal is a power-limited terminal, and the first inbound signal is a power-limited signal.

11. A signal enhancement device based on low-Earth orbit satellites, applied to low-Earth orbit satellites, characterized in that, include: The receiving module is used to receive the first inbound signal sent by the terminal; The acquisition module is used to acquire the inbound message based on the first inbound signal; A generation module is used to generate a second inbound signal based on the inbound message; the signal power of the second inbound signal is greater than the signal power of the first inbound signal. The transmitting module is used to send the second arrival signal to the high-orbit satellite.

12. A satellite, characterized in that, include: At least one processor; And at least one memory storing instructions that, when executed individually or jointly by the at least one processor, cause the satellite to perform the method according to any one of claims 1 to 10.

13. A computer storage medium storing instructions thereon, characterized in that, When the instructions are executed individually or jointly by at least one processor of a computer device, the computer device performs the method according to any one of claims 1 to 10.

14. A computer program product, characterized in that, The computer program product includes a computer program that, when executed by a processor, implements the method of any one of claims 1 to 10.

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