Carrier rocket measurement and control signal processing method, device and system

Abstract

The invention provides a carrier rocket measurement and control signal processing method, device and system, and relates to the technical field of spaceflight measurement and control, and the method comprises the steps: receiving a first measurement and control signal transmitted by a first air-based platform when a rocket is in a first flight height range; when the rocket is in a second flight height range, receiving a second measurement and control signal sent by a second air-based platform; when the rocket is in a third flight height range, receiving a third measurement and control signal sent by a third air-based platform; analyzing the first measurement and control signal, the second measurement and control signal or the third measurement and control signal to generate a corresponding resource scheduling control signal; and calling a first air-based platform, a second air-based platform and / or a third air-based platform to communicate with a rocket in a flight state according to the resource scheduling control signal. According to the scheme, the problem of a signal coverage blind area is solved, the cost is reduced, and data loss or measurement and control interruption caused by a single-point fault is avoided.

Description

Technical Field

[0001] This invention relates to the field of aerospace telemetry and control technology, and in particular to a method, apparatus and system for processing launch vehicle telemetry and control signals. Background Technology

[0002] Commercial launch vehicles are space transportation tools that, through market-driven operations, send payloads such as artificial satellites and probes into predetermined orbits. They are primarily used for satellite constellation, space science exploration, and commercial space services, and are a core link in the commercial space industry chain. The existing space-based + ground-based tracking and control network system faces numerous challenges in the launch of commercial, low-cost launch vehicles, mainly in the following aspects: 1. Limited coverage and signal interruption: Although existing systems combine ground stations and relay satellites, coverage remains limited. Signal interruption or loss is particularly common during the early stages of rocket flight or high-orbit flight.

[0003] 2. High cost and long deployment cycle: The current space-based + ground-based telemetry and control network requires the construction and maintenance of a large number of ground stations and relay satellites, resulting in high costs and a complex deployment cycle. The construction of ground facilities requires substantial capital and human resources, while satellite launches and their maintenance are also quite expensive. This makes it difficult for small commercial rocket companies with limited resources to afford, limiting the widespread adoption of low-cost commercial rocket launches.

[0004] 3. Insufficient emergency response capabilities and poor system redundancy: The existing telemetry and control system lacks the ability to respond and recover quickly in the face of faults or emergencies. If a ground station or satellite malfunctions, it may cause a prolonged signal interruption, making it impossible to guarantee real-time monitoring throughout the entire process. In addition, the existing system is relatively weak in redundancy design, lacking sufficient backup paths and resource coordination. Once a problem occurs, recovery is difficult and increases the risk. Summary of the Invention

[0005] The technical problems to be solved by this invention are limited signal coverage, signal interruption, high cost, and insufficient emergency response capability during rocket flight.

[0006] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows: In a first aspect, embodiments of the present invention provide a method for processing launch vehicle telemetry and control signals, applied to a cloud control platform, comprising: When the rocket is within the first flight altitude range, it receives the first telemetry and control signal sent by the first air-based platform. The first telemetry and control signal is generated by the first air-based platform monitoring the rocket's flight status. When the rocket is within the second flight altitude range, it receives the second telemetry and control signal sent by the second air-based platform. The second telemetry and control signal is generated by the second air-based platform monitoring the rocket's flight status. When the rocket is within the third flight altitude range, it receives a third telemetry and control signal sent by a third air-based platform. The third telemetry and control signal is generated by the third air-based platform monitoring the rocket's flight status. The lowest altitude of the second flight altitude range is less than or equal to the highest altitude of the first flight altitude range, and the lowest altitude of the third flight altitude range is less than or equal to the highest altitude of the second flight altitude range. The first, second, or third measurement and control signal is analyzed to generate a corresponding resource scheduling control signal. Based on the resource scheduling control signal, the first, second, and / or third air-based platforms are invoked to communicate with the rocket in flight. Optionally, The first flight altitude range is the flight scheduling range for the first air-based platform to monitor the rocket's flight status, and the first flight altitude range is from the first value to the second value; The second flight altitude range is the flight scheduling range for the second air-based platform to monitor the rocket's flight status, and the second flight altitude range is from the second value to the third value; The third flight altitude range is the flight scheduling range for the third air-based platform to monitor the rocket's flight status, and the second flight altitude range is greater than or equal to the third value.

[0007] Optionally, the first, second, or third measurement and control signal is analyzed to generate a corresponding resource scheduling control signal, including: If the rocket does not receive the first telemetry and control signal from the first airborne platform within the first preset time period when it is within the first flight altitude range, the first resource scheduling and control signal will be generated. According to the first resource scheduling control signal, the first air-based platform is controlled to switch to the second or third air-based platform to monitor the rocket's flight status, and data and / or command transmission is performed with the rocket through the second or third air-based platform.

[0008] Optionally, the first, second, or third measurement and control signal is analyzed to generate a corresponding resource scheduling control signal, including: If the rocket does not receive the second telemetry and control signal from the second airborne platform during the second preset time period when it is in the second flight altitude range, a second resource scheduling control signal will be generated. According to the second resource scheduling control signal, the second air-based platform is controlled to switch to the third air-based platform to monitor the rocket's flight status, and data and / or command transmission is performed between the third air-based platform and the rocket.

[0009] Optionally, the transmission of commands to the rocket includes at least one of the following: Commands are transmitted to the rocket via a third air-based platform; Commands are transmitted from the second air-based platform to the third air-based platform, and then from the third air-based platform to the rocket. Commands are transmitted from the first air-based platform to the second air-based platform, then from the second air-based platform to the third air-based platform, and finally from the third air-based platform to the rocket. Commands are transmitted to the rocket via a second airborne platform.

[0010] Optionally, it also includes: Data transmitted with the rocket will be stored in a main database, an off-site disaster recovery center, and / or edge nodes.

[0011] Optionally, it also includes: The first space-based platform is controlled to synchronize the first telemetry and control signal to the second and / or third space-based platforms; and / or The second space-based platform is controlled to synchronize the second measurement and control signal to the third space-based platform.

[0012] Optionally, it also includes: When the rocket is within the first flight altitude range, the first telemetry and control signal is sent from the first airborne platform to the second airborne platform, and then from the second airborne platform to the third airborne platform, and the first telemetry and control signal sent from the third airborne platform is received. When the rocket is within the second flight altitude range, the second telemetry and control signal is sent from the second airborne platform to the third airborne platform, and the second telemetry and control signal sent from the third airborne platform is received.

[0013] Secondly, embodiments of the present invention also provide a processing device for launch vehicle telemetry and control signals, applied to a cloud control platform, comprising: The transceiver module is used to receive a first telemetry and control signal sent by a first air-based platform when the rocket is within a first flight altitude range. The first telemetry and control signal is generated by the first air-based platform monitoring the rocket's flight status. When the rocket is within a second flight altitude range, it receives a second telemetry and control signal sent by a second air-based platform. The second telemetry and control signal is generated by the second air-based platform monitoring the rocket's flight status. When the rocket is within a third flight altitude range, it receives a third telemetry and control signal sent by a third air-based platform. The lowest altitude in the second flight altitude range is less than or equal to the highest altitude in the first flight altitude range, and the lowest altitude in the third flight altitude range is less than or equal to the highest altitude in the second flight altitude range. The control module is used to analyze the first, second, or third measurement and control signal and generate corresponding resource scheduling control signals. The communication module is used to invoke the first air-based platform, the second air-based platform, and / or the third air-based platform to communicate with the rocket in flight, based on the resource scheduling control signal.

[0014] Thirdly, embodiments of the present invention also provide a carrier rocket telemetry and control signal processing system applied to a cloud control platform, comprising: a first air-based platform, a second air-based platform, a third air-based platform, and a cloud control platform that are interconnected; wherein, the cloud control platform comprises: the carrier rocket telemetry and control signal processing device as described above.

[0015] The above-described solution of the present invention has at least the following beneficial effects: The above-described solution of this invention integrates first, second, and third airborne platforms to construct a three-dimensional airborne telemetry and control network with comprehensive coverage and flexible deployment capabilities. This enables collaborative work between different altitudes and platforms, improving the reliability and coverage of data acquisition and transmission. Employing a multi-platform redundancy design, the system automatically switches to a backup platform in case of platform failure, ensuring high reliability and continuity and preventing data loss or telemetry and control interruptions due to single-point failures. Based on the resource scheduling control signal, the first, second, and / or third airborne platforms are invoked to communicate with the rocket in flight. This optimizes data transmission paths and processing methods between platforms, reducing the overall cost of the telemetry and control system while improving real-time data transmission and processing efficiency. Attached Figure Description

[0016] Figure 1 This is a flowchart of an embodiment of the method for processing launch vehicle telemetry and control signals of the present invention; Figure 2 This is a communication diagram of a three-dimensional space-based telemetry and control network; Figure 3 This is a flowchart for verifying data; Figure 4 This is a schematic diagram of an embodiment of the rocket telemetry and control signal processing device of the present invention; Figure 5 This is a schematic diagram of the rocket telemetry and control signal processing system of the present invention. Detailed Implementation

[0017] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0018] like Figure 1 As shown, an embodiment of the present invention proposes a method for processing launch vehicle telemetry and control signals, including: Step 11: When the rocket is within the first flight altitude range, receive the first telemetry and control signal sent by the first air-based platform. The first telemetry and control signal is generated by the first air-based platform monitoring the rocket's flight status. Step 12: When the rocket is within the second flight altitude range, receive the second telemetry and control signal sent by the second air-based platform. The second telemetry and control signal is generated by the second air-based platform monitoring the rocket's flight status. Step 13: When the rocket is within the third flight altitude range, receive the third telemetry and control signal sent by the third air-based platform. The third telemetry and control signal is generated by the third air-based platform monitoring the rocket's flight status. The lowest altitude of the second flight altitude range is less than or equal to the highest altitude of the first flight altitude range, and the lowest altitude of the third flight altitude range is less than or equal to the highest altitude of the second flight altitude range. Step 14: Analyze the first, second, or third telemetry and control signal to generate a corresponding resource scheduling control signal; and according to the resource scheduling control signal, invoke the first, second, and / or third air-based platforms to communicate with the rocket in flight.

[0019] Existing space-based and ground-based tracking and control networks suffer from limited coverage, especially during the initial stages of rocket launch or at high altitudes, where signal interruptions or blind spots are common. To address this issue, this invention constructs a three-dimensional space-based tracking and control network using a first, second, and third space-based platform. By combining the different orbital altitudes of these three platforms, real-time tracking and data transmission across the entire launch and all airspace is achieved, avoiding the signal loss and coverage blind spot problems inherent in traditional systems.

[0020] The core objectives of the telemetry, tracking, and command (TT&C) mission are: 1. Real-time tracking: Determining the rocket's position, velocity, attitude, and other motion parameters. 2. Telemetry monitoring: Receiving operational status data (such as temperature, pressure, and voltage) from various rocket systems (engines, navigation, power supply, etc.). 3. Command control: Sending commands to the rocket when necessary (such as orbit correction, engine shutdown, separation, etc.). 4. Data transmission: Transmitting payload data, images, or communication between the spacecraft and the ground.

[0021] The first / second / third telemetry and control signals may include the identification of the first / second / third air-based platform, the rocket's position, speed, attitude and other motion parameters, the status data of each rocket system, requests for trajectory correction, shutdown, separation and other requests, as well as image data.

[0022] As an example, the first flight altitude range can be from a first preset value to a second preset value, where the first preset value is less than the second preset value; the second flight altitude range can be from a third preset value to a fourth preset value, where the third preset value is less than the fourth preset value; and the third flight altitude range can be above a fifth preset value. Wherein, the third preset value is less than or equal to the second preset value, and the fifth preset value is less than or equal to the fourth preset value.

[0023] As an example, if the rocket is located at the boundary (or boundary point) between the first and second flight altitude ranges, or between the second and third flight altitude ranges, a higher-positioned airborne platform will be preferentially selected. That is, if the rocket is located at the boundary (or boundary point) between the first and second flight altitude ranges, the second telemetry and control signal transmitted by the second airborne platform will be selected; if it is located at the boundary (or boundary point) between the second and third flight altitude ranges, the third telemetry and control signal transmitted by the third airborne platform will be selected.

[0024] In an optional embodiment of the present invention, the first flight altitude range is the flight scheduling range for the first air-based platform to monitor the rocket's flight status, and the first flight altitude range is from a first value to a second value; The second flight altitude range is the flight scheduling range for the second air-based platform to monitor the rocket's flight status, and the second flight altitude range is from the second value to the third value; The third flight altitude range is the flight scheduling range for the third air-based platform to monitor the rocket's flight status, and the second flight altitude range is greater than or equal to the third value.

[0025] As an example, the first flight altitude range is 0 to 200 kilometers, the second flight altitude range is 100 to 600 kilometers, and the third flight altitude range is above 500 kilometers. The rocket is located 150 kilometers from the boundary between the first and second flight altitude ranges, selecting the second telemetry and control signal transmitted from the second air-based platform. At the boundary 550 kilometers between the second and third flight altitude ranges, the third telemetry and control signal transmitted from the third air-based platform is selected.

[0026] As an example, when the rocket reaches 100 kilometers, a second air-based platform is selected to monitor the rocket's flight status; when the rocket reaches 500 kilometers, a third air-based platform is selected to monitor the rocket's flight status.

[0027] As an example, referring to Table 1, the first airborne platform can be a drone (swarm), the second airborne platform can be a balloon platform, and the third airborne platform can be a satellite (swarm).

[0028] Table 1 Deployment status of the first, second, and third space-based platforms

[0029] Traditional telemetry, tracking, and command (TT&C) systems require a large number of ground stations and high-cost satellite resources, resulting in high construction and maintenance costs. This invention utilizes a combination of low-cost small satellites, UAV swarms, balloons, and other aerial platforms to construct a three-dimensional airborne TT&C network, reducing the high cost requirements of traditional TT&C networks. Simultaneously, it provides flexible and dynamic TT&C services, reducing dependence on the number of ground stations and satellites, thereby significantly lowering the overall cost of the TT&C system.

[0030] In an optional embodiment of the present invention, step 11 further includes: Step 111: When the rocket is within the first flight altitude range, the first telemetry and control signal is sent from the first airborne platform to the second airborne platform, and then from the second airborne platform to the third airborne platform. The cloud control platform receives the first telemetry and control signal sent by the third airborne platform.

[0031] As an example, see reference Figure 2 This is a communication diagram of a three-dimensional space-based telemetry and control network. When the rocket is within 0 to 200 kilometers, the first telemetry and control signal is sent from the UAV (first space-based platform) to the balloon platform (second space-based platform), and then from the balloon platform (second space-based platform) to the satellite (third space-based platform), and the first telemetry and control signal is received from the satellite (third space-based platform).

[0032] As an example, when the rocket is within 0 to 200 kilometers, the first telemetry and control signal is sent from the UAV (first air-based platform) to the balloon platform (second air-based platform), and the first telemetry and control signal sent from the balloon platform (second air-based platform) is received.

[0033] As an example, it can also receive the first telemetry and control signal sent by the drone.

[0034] In an optional embodiment of the present invention, step 12 further includes: Step 121: When the rocket is within the second flight altitude range, the second telemetry and control signal is sent from the second airborne platform to the third airborne platform, and the second telemetry and control signal sent from the third airborne platform is received.

[0035] As an example, see reference Figure 2 When the rocket is in the second flight altitude range, that is, when the rocket is between 100 and 600 kilometers, it can send signals to the satellite (third air-based platform) via a balloon platform (second air-based platform) and receive the second telemetry and control signals sent by the satellite (third air-based platform).

[0036] As an example, it can also receive a second telemetry and control signal sent by a balloon platform (second airborne platform).

[0037] In an optional embodiment of the present invention, for step 13: As an example, see reference Figure 2 The third flight altitude range is above 500 kilometers, meaning that when the rocket's altitude is approximately 500 kilometers or higher, it will receive the third telemetry and control signal transmitted by the satellite (third air-based platform). If the satellite (third air-based platform) malfunctions, it can transmit the third telemetry and control signal to the nearest balloon platform (second air-based platform) and receive the third telemetry and control signal from that platform. Alternatively, it can transmit the third telemetry and control signal to the nearest balloon platform (second air-based platform), which will then transmit it to the nearest UAV (first air-based platform) and receive the third telemetry and control signal from that UAV (first air-based platform).

[0038] As an example, generally speaking, the telemetry and control signals sent by the space-based platform located at a higher position (first, second, or third) are selected.

[0039] In an optional embodiment of the present invention, step 14 includes: Step 141: When the rocket is within the first flight altitude range, if the first telemetry and control signal sent by the first air-based platform is not received within the first preset time period, a first resource scheduling control signal is generated. Step 142: According to the first resource scheduling control signal, control the first air-based platform to switch to the second air-based platform or the third air-based platform to monitor the rocket's flight status, and transmit data and / or commands to the rocket through the second air-based platform or the third air-based platform.

[0040] As an example, because real-time rocket control is required, if no first telemetry and control signal is received from the UAV (first airborne platform) within a first preset time period (e.g., 1 second) when the rocket is within the first flight altitude range of 0 to 200 kilometers, a first resource scheduling control signal is generated based on the rocket's current location. Alternatively, the rocket's current location is estimated based on the previously received first / second / third telemetry and control signal. Then, based on the estimated current location (assuming the rocket is currently within the second flight altitude range), the nearest balloon platform (second airborne platform) is determined, and a first resource scheduling control signal is generated. This first resource scheduling control signal controls the balloon platform (second airborne platform) to monitor the rocket and receive second telemetry and control data. Instructions are then generated based on the second telemetry and control data.

[0041] As an example, if the current position of the rocket is estimated to be above 500 kilometers based on the first / second / third telemetry and control signals received previously, the UAV (first airborne platform) is controlled to switch to a satellite (third airborne platform) to monitor the rocket's flight status and receive third telemetry and control data from the satellite (third airborne platform). Instructions are generated based on the third telemetry and control data.

[0042] As an example, the first / second / third telemetry and control signals may include the identification of the first / second / third air-based platform, and motion parameters such as the rocket's position, velocity, and attitude. Therefore, the current position or distance of the rocket can be estimated using the position, velocity, and a first preset time period from the previous telemetry and control signal.

[0043] In an optional embodiment of the present invention, step 14 further includes: Step 143: When the rocket is within the second flight altitude range, if the second telemetry and control signal sent by the second air-based platform is not received during the second preset time period, a second resource scheduling control signal is generated. Step 144: According to the second resource scheduling control signal, control the second air-based platform to switch to the third air-based platform to monitor the rocket's flight status, and transmit data and / or commands to the rocket through the third air-based platform.

[0044] As an example, because real-time rocket control is required, if the rocket is within the second flight altitude range of 100 to 600 kilometers and does not receive the second telemetry and control signal from the balloon platform (second airborne platform) within the second preset time period (e.g., 0.5 seconds), a second resource scheduling control signal is generated based on the rocket's current location. Alternatively, the rocket's current location is estimated based on the previously received first / second / third telemetry and control signal, and then the second resource scheduling control signal is generated based on the estimated current rocket location.

[0045] As an example, if the rocket is within the second flight altitude range of 100 to 600 kilometers, the second resource scheduling control signal controls the balloon platform (second air-based platform) to switch to a satellite (third air-based platform) to monitor the rocket's flight status and receive third telemetry and control data from the satellite (third air-based platform). Instructions are generated based on the third telemetry and control data.

[0046] In an optional embodiment of the present invention, after receiving the first, second, and third measurement and control signals, the cloud control platform generates instructions based on the measurement and control signals. Before generating the instructions, data consistency verification is also required, as described in [reference]. Figure 3 After receiving the first, second, or third measurement and control signal (i.e., the original data), the original data needs to be verified for consistency. If the verification passes, an instruction is generated based on the original data; otherwise, the instruction is generated by selecting a data source with high confidence through the arbitration module.

[0047] As an example, the data validation process is as follows: 1. Determine the validation rules, such as defining data format specifications (data type, length, range, etc.) and establishing data relationships (foreign key constraints, etc.). 2. Select a validation method, such as real-time validation, format validation, range validation, parity validation, etc. Different validation methods yield different types of validated data.

[0048] As an example, the arbitration module can score different types of verification data. If all types of verification data are qualified, all types of verification data will score 1, the data verification will pass, and instructions will be generated based on the original data. If some types of verification data are unqualified, the unqualified verification data will score 0, and the qualified verification data will score 1, the data verification will fail. In this case, the arbitration module will use the verification data with a score greater than 0 as the data source with higher confidence, and will generate instructions based on the data source with higher confidence.

[0049] In an optional embodiment of the present invention, instructions can be generated by analyzing the first, second, or third telemetry and control signals. For example, a first telemetry and control signal is received, which includes the identifier of the first telemetry and control signal, the rocket's position, velocity, and attitude. The rocket's position, velocity, and attitude are compared with the expected received position, velocity, and attitude of the rocket in the database. If the attitude deviation exceeds a preset safety range, an attitude correction instruction is generated (e.g., the motion parameters that need to be adjusted are calculated based on the current position, velocity, and attitude of the rocket, and the motion parameters are sent to the rocket to change the rocket's attitude). The attitude correction instruction is then sent to the rocket through a first / second / third space-based platform to adjust the rocket's attitude.

[0050] In an optional embodiment of the present invention, step 142 or step 144, transmitting commands to the rocket, includes at least one of the following: Step 1421: Transmit commands to the rocket via the third air-based platform; Step 1422: The command is transmitted from the second air-based platform to the third air-based platform, and then from the third air-based platform to the rocket. Step 1423: Transmit commands via the first air-based platform to the second air-based platform, then via the second air-based platform to the third air-based platform, and finally via the third air-based platform to the rocket; and / or, Step 1424: The command is transmitted to the rocket via the second air-based platform.

[0051] As an example, after the cloud control platform generates instructions based on the received first / second / third telemetry and control signals, it can send the instructions to the first air-based platform, which will then transmit them to the rocket; or it can send the instructions to the first air-based platform, which will then transmit them to the second air-based platform, which will then transmit them to the rocket; or it can send the instructions to the first air-based platform, which will then transmit them to the second air-based platform, which will then transmit them to the third air-based platform, which will then transmit them to the rocket.

[0052] As an example, instructions can also be sent to a second air-based platform, which then transmits them to the rocket; or instructions can be sent to a second air-based platform, which then transmits them to a third air-based platform, which in turn transmits them to the rocket.

[0053] As an example, instructions can also be sent to a third air-based platform, which will then transmit them to the rocket.

[0054] As an example, if a platform fails, instructions are sent to a higher-positioned airborne platform first.

[0055] In an optional embodiment of the present invention, the method further includes storing the data transmitted with the rocket in a main database, an off-site disaster recovery center, and / or an edge node.

[0056] This embodiment incorporates an intelligent collaboration mechanism between platforms to enhance emergency response capabilities and system reliability. Different satellites and airborne platforms can schedule and switch resources according to flight phases and real-time needs. If one platform fails, other platforms can automatically take over, avoiding single points of failure in the system. Furthermore, redundancy is incorporated into data processing and command issuance to ensure that the rocket's telemetry and control mission remains unaffected under any abnormal circumstances.

[0057] The master database is the core component of a database system, typically referring to the database instance that serves as the primary data source in a database replication architecture. For example, a database may consist of one master database and multiple slave databases.

[0058] As an example, the cloud control platform can be designed with a master database and multiple slave databases. The master database can be used to store the position information of the first, second, and third air-based platforms. The slave databases can be used to store data sent by the first, second, and third air-based platforms, and / or instructions generated by the cloud control platform, and / or record rocket malfunction data, etc.

[0059] An off-site disaster recovery center refers to a backup data center established at a physical distance to take over business operations in the event of a catastrophic failure of the primary data center.

[0060] As an example, the cloud control platform can replicate data in real-time or near real-time to maintain consistency with the main control center, and back up and store critical rocket data. Off-site disaster recovery centers can also be designed locally for the first, second, and third air-based platforms to prevent data loss.

[0061] Edge nodes are a key component of edge computing architecture. They refer to distributed computing resources deployed near the data source for data processing and analysis at or near the location where the data is generated.

[0062] As an example, the cloud control platform can be used as an edge node. The first, second, and third airborne platforms send measurement and control data to the cloud control platform, which then calculates and generates instructions, saving the local resources of the first, second, and third airborne platforms.

[0063] In an optional embodiment of the present invention, the method further includes: Step 15: Control the first space-based platform to synchronize the first telemetry and control signal to the second space-based platform and / or the third space-based platform; and / or Step 16: Control the second space-based platform to synchronize the second measurement and control signal to the third space-based platform.

[0064] Existing telemetry and control networks lack sufficient redundancy and rapid recovery mechanisms in the face of equipment failures or emergencies, leading to signal interruptions and data loss. This invention enhances the emergency response capability of the telemetry and control network by designing a multi-layered, multi-platform redundant system. If one platform fails, other platforms can be used as backups, ensuring uninterrupted real-time telemetry and control during rocket launches and significantly improving system stability and reliability.

[0065] As an example, the first flight altitude range is 0 to 200 kilometers, the second flight altitude range is 100 to 600 kilometers, and the third flight altitude range is above 500 kilometers. The UAV is in the first flight altitude range, the balloon platform is in the second flight altitude range, and the satellite is in the third flight altitude range. The first telemetry and control signals of the UAVs within the first flight altitude range are synchronized. The second telemetry and control signals of the balloon platforms within the second flight altitude range are synchronized. The third telemetry and control signals of the satellites within the third flight altitude range are synchronized.

[0066] Using the above example, the overlapping area between the first and second flight altitude ranges contains UAVs and balloon platforms. The first telemetry and control signal of the UAVs in the overlapping area is synchronized with the second telemetry and control signal of the balloon platforms in the overlapping area. The overlapping area between the second and third flight altitude ranges contains balloon platforms and satellites. The second telemetry and control signal of the balloon platforms in the overlapping area is synchronized with the third telemetry and control signal of the satellites in the overlapping area.

[0067] After the first, second, and third measurement and control signals are sent to the cloud control platform, the cloud control platform processes and backs them up synchronously.

[0068] As an example, the above method can be implemented using the following code: import random import time import threading # Define satellite class class Satellite: def __init__(self, name, orbit_type, coverage_range): self.name = name self.orbit_type = orbit_type # Low Earth Orbit, Medium Earth Orbit, High Earth Orbit self.coverage_range = coverage_range # Coverage range def transmit_data(self, data): print(f"{self.name} - Transmitting data: {data}") # Simulate data transmission delay time.sleep(random.uniform(0.1, 0.5)) return f"{self.name} data: {data}" # Define aerial platform classes (including drones and balloons) class AirPlatform: def __init__(self, name, altitude, platform_type): self.name = name self.altitude = altitude# Platform flight altitude self.platform_type = platform_type # Platform type (drone, balloon, etc.) def collect_data(self): # Simulate collecting rocket flight data data = f"Flight data from {self.name} at {self.altitude}km({self.platform_type})" return data # Define the drone swarm class (Drone swarm) class DroneSwarm(AirPlatform): def __init__(self, name, altitude, num_drones): super().__init__(name, altitude, "Drone Swarm") self.num_drones = num_drones # Number of drones in the drone swarm def collect_data(self): # Simulate data collection from multiple drones data = f"Flight data from {self.name} ({self.num_drones} drones) at{self.altitude}km" return data # Define the Balloon class class Balloon(AirPlatform): def __init__(self, name, altitude): super().__init__(name, altitude, "Balloon") def collect_data(self): # Simulated balloon data collection data = f"Flight data from {self.name} at {self.altitude}km" return data # Define the control center class class ControlCenter: def __init__(self): self.active_platforms = [] def add_platform(self, platform): self.active_platforms.append(platform) def remove_platform(self, platform): if platform in self.active_platforms: self.active_platforms.remove(platform) def switch_to_backup(self, failed_platform): print(f"Platform {failed_platform.name} failed, switching to backupplatform.") # Select a redundant platform to take over the task backup_platform = next((p for p in air_platforms if p != failed_platform), None) if backup_platform: self.add_platform(backup_platform) print(f"Backup platform {backup_platform.name} activated.") else: print("No backup available, emergency protocol initiated.") # Initialize multiple satellites satellites = [ Satellite("Sat1", "Low", 1000), Satellite("Sat2", "Medium", 2000), Satellite("Sat3", "High", 3000) ] # Initialize aerial platforms (including drone swarms and balloons) air_platforms = [ DroneSwarm("DroneSwarm1", 30, 5), # Drone swarm Balloon("Balloon1", 15), # Balloon AirPlatform("Platform1", 30, "Fixed Wing"),# Fixed-wing platform AirPlatform("Platform2", 10, "Helicopter")# Helicopter ] # Initialize the control center and add the first platform control_center = ControlCenter() control_center.add_platform(air_platforms[0]) # Simulate data collection and transmission across multiple platforms def simulate_data_collection(): while True: # Data collection from simulated aerial platforms platform_data = [platform.collect_data() for platform in air_platforms] for data in platform_data: print(f"Collected from {data}") # Simulated satellite data transmission satellite_data = [satellite.transmit_data(data) for satellite insatellites for data in platform_data] for data in satellite_data: print(f"Data received: {data}") time.sleep(2) # Collects and transmits data every 2 seconds. # Start Data Collection Simulation data_collection_thread = threading.Thread(target=simulate_data_collection) data_collection_thread.start() # Simulation platform failover def simulate_platform_failure(): time.sleep(5) # Simulates a fault after 5 seconds failed_platform = air_platforms[0] print(f"Simulating failure of platform {failed_platform.name}.") control_center.remove_platform(failed_platform) control_center.switch_to_backup(failed_platform) # Enable platform failure simulation platform_failure_thread = threading.Thread(target=simulate_platform_failure) platform_failure_thread.start() Figure 4 This is a schematic diagram of an embodiment of a carrier rocket telemetry and control signal processing device according to the present invention. The device is applied to a cloud control platform and includes: The transceiver module 41 is configured to receive a first telemetry and control signal transmitted by a first air-based platform when the rocket is within a first flight altitude range. The first telemetry and control signal is generated by the first air-based platform monitoring the rocket's flight status. When the rocket is within a second flight altitude range, it receives a second telemetry and control signal transmitted by a second air-based platform. The second telemetry and control signal is generated by the second air-based platform monitoring the rocket's flight status. When the rocket is within a third flight altitude range, it receives a third telemetry and control signal transmitted by a third air-based platform. The lowest altitude in the second flight altitude range is less than or equal to the highest altitude in the first flight altitude range, and the lowest altitude in the third flight altitude range is less than or equal to the highest altitude in the second flight altitude range. Control module 42 is used to analyze the first measurement and control signal, the second measurement and control signal or the third measurement and control signal, and generate corresponding resource scheduling control signals; Communication module 43 is used to invoke the first air-based platform, the second air-based platform, and / or the third air-based platform to communicate with the rocket in flight status according to the resource scheduling control signal.

[0069] Optionally, the first flight altitude range is the flight scheduling range for the first air-based platform to monitor the rocket's flight status, and the first flight altitude range is from a first value to a second value; The second flight altitude range is the flight scheduling range for the second air-based platform to monitor the rocket's flight status, and the second flight altitude range is from the second value to the third value; The third flight altitude range is the flight scheduling range for the third air-based platform to monitor the rocket's flight status, and the second flight altitude range is greater than or equal to the third value.

[0070] Optionally, the control module 42 is configured to: generate a first resource scheduling control signal if the first telemetry and control signal sent by the first airborne platform is not received during a first preset time period when the rocket is within the first flight altitude range; According to the first resource scheduling control signal, the first air-based platform is controlled to switch to the second or third air-based platform to monitor the rocket's flight status, and data and / or command transmission is performed with the rocket through the second or third air-based platform.

[0071] Optionally, the control module 42 is used to generate a second resource scheduling control signal if the second telemetry and control signal sent by the second air-based platform is not received during the second preset time period when the rocket is within the second flight altitude range. According to the second resource scheduling control signal, the second air-based platform is controlled to switch to the third air-based platform to monitor the rocket's flight status, and data and / or command transmission is performed between the third air-based platform and the rocket.

[0072] Optionally, the communication module 43 is used to: transmit commands to the rocket via a third air-based platform; Commands are transmitted from the second air-based platform to the third air-based platform, and then from the third air-based platform to the rocket. Commands are transmitted from the first air-based platform to the second air-based platform, then from the second air-based platform to the third air-based platform, and finally from the third air-based platform to the rocket. Commands are transmitted to the rocket via a second airborne platform.

[0073] Optionally, the data backup module 44 is used to store data transmitted with the rocket in a main database, an off-site disaster recovery center, and / or an edge node.

[0074] Optionally, the data backup module 44 is used to: control the first space-based platform to synchronize the first measurement and control signal to the second space-based platform and / or the third space-based platform; and / or control the second space-based platform to synchronize the second measurement and control signal to the third space-based platform.

[0075] Optionally, the communication module 43 is used to: when the rocket is within the first flight altitude range, send the first telemetry and control signal to the second airborne platform through the first airborne platform, then send the first telemetry and control signal to the third airborne platform through the second airborne platform, and receive the first telemetry and control signal sent by the third airborne platform; When the rocket is within the second flight altitude range, the second telemetry and control signal is sent from the second airborne platform to the third airborne platform, and the second telemetry and control signal sent from the third airborne platform is received.

[0076] Figure 5This is a schematic diagram of a launch vehicle telemetry and control signal processing system according to the present invention. Figure 5 As shown, the system includes: a first air-based platform, a second air-based platform, a third air-based platform, and a cloud control platform that are interconnected; wherein, the cloud control platform includes: a processing device for the launch vehicle telemetry and control signals as described above.

[0077] The device embodiments described above are merely illustrative. The modules described as separate components may or may not be physically separate, and the components shown as modules may or may not be physical modules; that is, they may be located in one place or distributed across multiple network modules. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0078] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., including several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods of various embodiments or some parts of embodiments.

[0079] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for processing launch vehicle telemetry and control signals, characterized in that, Applied to a cloud control platform, the method includes: When the rocket is within the first flight altitude range, it receives the first telemetry and control signal sent by the first air-based platform. The first telemetry and control signal is generated by the first air-based platform monitoring the rocket's flight status. When the rocket is within the second flight altitude range, it receives the second telemetry and control signal sent by the second air-based platform. The second telemetry and control signal is generated by the second air-based platform monitoring the rocket's flight status. When the rocket is within the third flight altitude range, it receives a third telemetry and control signal sent by a third air-based platform. The third telemetry and control signal is generated by the third air-based platform monitoring the rocket's flight status. The lowest altitude of the second flight altitude range is less than or equal to the highest altitude of the first flight altitude range, and the lowest altitude of the third flight altitude range is less than or equal to the highest altitude of the second flight altitude range. The first, second, or third measurement and control signal is analyzed to generate a corresponding resource scheduling control signal. Based on the resource scheduling control signal, the first air-based platform, the second air-based platform, and / or the third air-based platform are invoked to communicate with the rocket in flight.

2. The method for processing launch vehicle telemetry and control signals according to claim 1, characterized in that, The first flight altitude range is the flight scheduling range for the first air-based platform to monitor the rocket's flight status, and the first flight altitude range is from the first value to the second value; The second flight altitude range is the flight scheduling range for the second air-based platform to monitor the rocket's flight status, and the second flight altitude range is from the second value to the third value; The third flight altitude range is the flight scheduling range for the third air-based platform to monitor the rocket's flight status, and the second flight altitude range is greater than or equal to the third value.

3. The method for processing launch vehicle telemetry and control signals according to claim 1, characterized in that, Analyzing the first, second, or third measurement and control signal to generate corresponding resource scheduling control signals, including: If the rocket does not receive the first telemetry and control signal from the first airborne platform within the first preset time period when it is within the first flight altitude range, the first resource scheduling and control signal will be generated. According to the first resource scheduling control signal, the first air-based platform is controlled to switch to the second or third air-based platform to monitor the rocket's flight status, and data and / or command transmission is performed with the rocket through the second or third air-based platform.

4. The method for processing launch vehicle telemetry and control signals according to claim 1, characterized in that, Analyzing the first, second, or third measurement and control signal to generate corresponding resource scheduling control signals, including: If the rocket does not receive the second telemetry and control signal from the second airborne platform during the second preset time period when it is in the second flight altitude range, a second resource scheduling control signal will be generated. According to the second resource scheduling control signal, the second air-based platform is controlled to switch to the third air-based platform to monitor the rocket's flight status, and data and / or command transmission is performed between the third air-based platform and the rocket.

5. The method for processing launch vehicle telemetry and control signals according to claim 3 or 4, characterized in that, The transmission of commands to the rocket includes at least one of the following: Commands are transmitted to the rocket via a third air-based platform; Commands are transmitted from the second air-based platform to the third air-based platform, and then from the third air-based platform to the rocket. Commands are transmitted from the first air-based platform to the second air-based platform, then from the second air-based platform to the third air-based platform, and finally from the third air-based platform to the rocket. Commands are transmitted to the rocket via a second airborne platform.

6. The method for processing launch vehicle telemetry and control signals according to claim 3 or 4, characterized in that, Also includes: Data transmitted with the rocket will be stored in a main database, an off-site disaster recovery center, and / or edge nodes.

7. The method for processing launch vehicle telemetry and control signals according to claim 1, characterized in that, Also includes: The first space-based platform is controlled to synchronize the first telemetry and control signal to the second and / or third space-based platforms; and / or The second space-based platform is controlled to synchronize the second measurement and control signal to the third space-based platform.

8. The method for processing launch vehicle telemetry and control signals according to claim 1, characterized in that, Also includes: When the rocket is within the first flight altitude range, the first telemetry and control signal is sent from the first airborne platform to the second airborne platform, and then from the second airborne platform to the third airborne platform, and the first telemetry and control signal sent from the third airborne platform is received. When the rocket is within the second flight altitude range, the second telemetry and control signal is sent from the second airborne platform to the third airborne platform, and the second telemetry and control signal sent from the third airborne platform is received.

9. A processing device for launch vehicle telemetry and control signals, characterized in that, The device, applied to a cloud control platform, includes: The transceiver module is used to receive a first telemetry and control signal sent by a first air-based platform when the rocket is within a first flight altitude range. The first telemetry and control signal is generated by the first air-based platform monitoring the rocket's flight status. When the rocket is within a second flight altitude range, it receives a second telemetry and control signal sent by a second air-based platform. The second telemetry and control signal is generated by the second air-based platform monitoring the rocket's flight status. When the rocket is within a third flight altitude range, it receives a third telemetry and control signal sent by a third air-based platform. The lowest altitude in the second flight altitude range is less than or equal to the highest altitude in the first flight altitude range, and the lowest altitude in the third flight altitude range is less than or equal to the highest altitude in the second flight altitude range. The control module is used to analyze the first, second, or third measurement and control signal and generate corresponding resource scheduling control signals. The communication module is used to invoke the first air-based platform, the second air-based platform, and / or the third air-based platform to communicate with the rocket in flight, based on the resource scheduling control signal.

10. A processing system for launch vehicle telemetry and control signals, characterized in that, include: The system comprises a first air-based platform, a second air-based platform, a third air-based platform, and a cloud control platform that are interconnected; wherein the cloud control platform includes: a processing device for the launch vehicle telemetry and control signals as described in claim 9.

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