Satellite telemetering method, satellite equipment and medium

Abstract

The invention provides a satellite telemetering method, satellite equipment and a medium, and relates to the technical field of satellite telemetering. The satellite telemetering method provided by the invention comprises the following steps: in a satellite launching process, collecting an injection-dedicated telemetering packet within time t (t is greater than 0) after a sailboard is unfolded, counting key telemetering data according to the injection-dedicated telemetering packet, and subsequently, issuing the injection-dedicated telemetering packet and the key telemetering data to ground equipment, therefore, the ground equipment can determine the operation condition of the satellite in the injection period according to the special telemetry packet and the key telemetry data. By adopting the mode, the telemetering recording during the satellite orbit injection period can be efficiently realized, and the measurement and control support of other equipment (such as the orbit injection measurement and control support of a relay or an ocean vessel) is not needed.

Description

Technical Field

[0001] The present application relates to the field of satellite telemetry technology, and in particular to a satellite telemetry method, satellite equipment, and medium. Background Art

[0002] With the rapid development of aerospace technology, satellite systems are taking on increasingly complex tasks such as communications, navigation, and remote sensing. However, the entire satellite lifecycle from launch to stable orbit involves multiple dynamic processes, and the technical challenges and risk factors involved pose a significant threat to satellite safety. Currently, telemetry support for satellite launch and orbit insertion typically uses the following solutions:

[0003] Option 1: Use ground system support to achieve measurement and control support during the orbit insertion through relays, ocean-going ships, etc., and use ordinary transmission methods for telemetry.

[0004] Option 2: By formulating a complex fault contingency plan, ground experts will make a judgment during the first orbital entry and take the best possible approach if a fault occurs.

[0005] Option 3: For satellites of low value, there is no risk of telemetry when they are put into orbit, and post-telemetry data analysis methods are usually used for review.

[0006] For commercial satellites, it is difficult to obtain orbital measurement and control support from relays or ocean-going ships, and there is an urgent need for telemetry during the initial orbital phase. Summary of the Invention

[0007] In view of this, the present application provides a satellite telemetry method, satellite equipment and medium, which can realize telemetry recording during the satellite orbiting phase without relying on relays or orbital measurement and control support from ocean-going ships.

[0008] In a first aspect, the present application provides a satellite telemetry method, comprising:

[0009] During satellite launch, within time t (t greater than 0) after the sailboard is deployed, a dedicated orbital telemetry package is collected. The dedicated orbital telemetry package includes one or more of the following information: energy system orbital telemetry, attitude and orbit control subsystem orbital telemetry, and attitude and orbit control stand-alone orbital telemetry;

[0010] Count key telemetry data based on the collected orbit-entry telemetry packages;

[0011] The dedicated telemetry package for orbit entry and the key telemetry data are sent to ground equipment so that the ground equipment can determine the operating status of the satellite during orbit entry based on the dedicated telemetry package and the key telemetry data.

[0012] In one embodiment, the key telemetry data includes any one or more of the following: satellite angular velocity data, satellite angular momentum data, battery pack voltage data, bus voltage data, load current data, and charge and discharge current data.

[0013] In one embodiment, the key telemetry data also includes the suspected collision time and the angular momentum change value corresponding to the suspected collision time. The key telemetry data statistics based on the collected orbit-entry telemetry packets include: periodically acquiring satellite angular velocity from the orbit-entry telemetry packets; calculating satellite angular momentum based on the satellite angular velocity; calculating the angular momentum change value between the current and previous moments; and if the angular momentum change value is greater than or equal to an angular momentum change threshold, recording the angular momentum change value and the current time as the suspected collision time. If multiple suspected collisions occur, each time is recorded.

[0014] In one embodiment, the method further includes: sending a separation event package and a sailboard deployment event package to the ground equipment, wherein the separation event package is collected when a satellite-rocket separation signal is detected; and the sailboard deployment event package is collected when it is detected that the sailboard begins to deploy.

[0015] In one embodiment, the separation event package includes one or more of the following information: separation event number, separation status, separation time, three-axis angular velocity at the time of separation, three-axis inertia of the entire satellite at the time of separation, battery pack voltage at the time of separation, bus voltage at the time of separation, discharge current at the time of separation, battery temperature at the time of separation, and reaction wheel temperature at the time of separation.

[0016] In one embodiment, the panel deployment event package includes one or more of the following information: panel deployment event number, panel deployment status, three-axis angular velocity at the time of panel deployment, three-axis inertia of the entire satellite at the time of panel deployment, SADA solar panel drive structure information at the time of panel deployment, voltage and current at the time of panel deployment, reaction wheel temperature at the time of panel deployment, panel temperature at the time of panel deployment, and battery pack information at the time of panel deployment.

[0017] In one embodiment, the sending of the orbit entry-specific telemetry package and the key telemetry data to ground equipment includes: when the satellite entry is detected, telemetry is sent according to the priority of real-time telemetry, asynchronous packet telemetry and delayed telemetry; wherein, the separation event package, the sailboard deployment event package and key telemetry data are sent as asynchronous packets; the orbit entry-specific telemetry package is sent as delayed telemetry package; and the telemetry data collected after the satellite entry is sent as real-time telemetry.

[0018] In one embodiment, the method further includes: recording full-scene telemetry data when detecting satellite-rocket separation and sailboard deployment; and sending the full-scene telemetry data when detecting an acquisition instruction sent by ground equipment.

[0019] In a second aspect, the present application provides a satellite device, comprising:

[0020] at least one processor; and

[0021] At least one memory stores thereon instructions, which, when executed individually or collectively by the at least one processor, cause the satellite device to perform the method according to the first aspect.

[0022] In a third aspect, the present application provides a computer storage medium having instructions stored thereon. When the instructions are executed individually or collectively by at least one processor of a satellite device, the satellite device executes the method described in the first aspect.

[0023] The satellite telemetry method provided in this application collects a dedicated orbital telemetry package within the time t (t greater than 0) after the sailboard is deployed during satellite launch, and collects key telemetry data based on the dedicated orbital telemetry package. Subsequently, the dedicated orbital telemetry package and key telemetry data are sent to ground equipment so that the ground equipment can determine the operating status of the satellite during orbital entry based on the dedicated telemetry package and key telemetry data. In this way, telemetry recording during satellite orbital entry can be efficiently achieved without relying on measurement and control support from other equipment (such as relays or ocean-going vessels for orbital measurement and control support). BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The accompanying drawings are included to provide a further understanding of the present application. They are incorporated into and constitute a part of this application. The accompanying drawings illustrate embodiments of the present application and, together with this specification, serve to explain the principles of the present application. In the accompanying drawings:

[0025] Figure 1 This is a schematic diagram of the architecture of a telemetry communication system provided in an embodiment of the present application;

[0026] Figure 2 This is a flow chart of a satellite telemetry method provided in an embodiment of the present application;

[0027] Figure 3 This is a flow chart of another satellite telemetry method provided in an embodiment of the present application;

[0028] Figure 4 1 is a schematic structural diagram of a satellite telemetry device provided in an embodiment of the present application;

[0029] Figure 5 This is a structural diagram of a satellite device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0030] To more clearly illustrate the technical solutions of the embodiments of this application, the following is a brief introduction to the drawings required for describing the embodiments. Obviously, the drawings described below are merely examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without inventive effort. Unless otherwise apparent from the context or otherwise noted, the same reference numerals in the figures represent the same structure or operation.

[0031] As used herein, unless the context clearly indicates otherwise, the terms "a," "an," "an," and / or "the" are not intended to refer to the singular but may include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements specifically identified, and these steps and elements do not constitute an exclusive list. A method or apparatus may also include other steps or elements.

[0032] At the same time, this application uses specific terms to describe the embodiments of this application. For example, "one embodiment," "an embodiment," and / or "some embodiments" refer to a certain feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that "one embodiment," "an embodiment," or "an alternative embodiment" mentioned twice or multiple times in different locations in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application may be appropriately combined.

[0033] Unless otherwise specified, the relative arrangement of the parts and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application. Meanwhile, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to actual proportional relationships. Technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar numbers and letters represent similar items in the following drawings, and therefore, once an item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0034] In addition, although the terms used in this application are selected from commonly known and commonly used terms, some of the terms mentioned in this specification may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description herein. In addition, it is required that this application be understood not only by the actual terms used, but also by the meaning implied by each term.

[0035] Flowcharts are used in this application to illustrate the operations performed by devices or apparatuses according to embodiments of the present application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, the various steps may be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more operations may be removed from these processes.

[0036] In order to better understand the satellite telemetry method disclosed in the embodiment of the present disclosure, the telemetry communication system to which the embodiment of the present disclosure is applicable is first described below.

[0037] Figure 1 The telemetry communication system is a schematic diagram illustrating the architecture of a telemetry communication system according to an embodiment of the present disclosure. The telemetry communication system includes a satellite device 100 and a ground device 101. The satellite device 100 can be a high-orbit satellite, a low-orbit satellite, or a medium-orbit satellite. From launch to orbital operation, a satellite must go through the following stages:

[0038] 1. Pre-launch preparation phase: tasks include: rocket and satellite integration testing, refueling, attitude control system calibration, launch window prediction, etc.

[0039] 2. Launch ascent phase (powered flight phase): Mission content: The rocket ignites and takes off, breaks through the atmosphere, and completes interstage separation and attitude adjustment.

[0040] 3. During the satellite-rocket separation phase, the mission content is as follows: the rocket's last stage is disconnected from the satellite through the separation mechanism, and the satellite enters the transfer orbit.

[0041] 4. In-orbit deployment phase: Mission content: The satellite autonomously completes the deployment of the energy system and functional initialization. Specifically, it includes:

[0042] Solar sail panel deployment: multi-stage hinge deployment and locking;

[0043] Antenna deployment: Extension and alignment of large deployable antennas such as parabolic antennas.

[0044] 5. Orbit transfer and capture phase, mission content: Enter the target orbit (such as geostationary orbit) from the transfer orbit through Hohmann transfer, electric propulsion, etc.

[0045] 6. On-orbit testing and operation phase: Mission content: verify payload performance, establish communication links, and enter mission mode.

[0046] The satellite device 100 can record a variety of data at key stages through the satellite telemetry method proposed in the embodiment of the present application, such as: 1. During the satellite-rocket separation stage, separation event packages and full-scene telemetry data are collected; 2. During the on-orbit deployment stage, solar sail panel deployment event packages, full-scene telemetry data, orbit entry-specific telemetry packages, and key telemetry data are collected. Subsequently, after the satellite device 100 enters the orbit for the first time, the mixed telemetry data (such as separation event packages, full-scene telemetry data, solar sail panel deployment event packages, orbit entry-specific telemetry packages, and key telemetry data, etc.) collected by the satellite device 100 from launch to on-orbit operation can be sent to the ground device 101 to achieve multiple sampling coverage of the satellite's orbital status, provide efficient telemetry data support for the satellite device 100's first entry, and reduce the difficulty of ground flight process control after the satellite device 100 enters the orbit.

[0047] It can be understood that the telemetry communication system described in the embodiment of the present disclosure is for the purpose of more clearly illustrating the technical solution of the embodiment of the present disclosure, and does not constitute a limitation on the technical solution proposed in the embodiment of the present disclosure. A person skilled in the art can know that with the evolution of the system architecture and the emergence of new business scenarios, the technical solution proposed in the embodiment of the present disclosure is also applicable to similar technical problems.

[0048] The following embodiments of the present disclosure can be applied to Figure 1 The telemetry communication system or part thereof is shown, but not limited to it. Figure 1 The various entities shown are examples, and the telemetry communication system may include Figure 1 All or part of the subject, and may also include Figure 1 The number and form of other entities are arbitrary, each entity can be physical or virtual, the connection relationship between the entities is an example, the entities can be connected or disconnected, and the connection can be in any way, which can be direct or indirect, wired or wireless.

[0049] The satellite telemetry method proposed in the embodiment of the present disclosure is described in detail below. The satellite telemetry method can be deployed in Figure 1 The satellite device 100 in the embodiment may also be deployed in a device (such as a satellite-borne product), which is carried in the satellite device 100. This application does not make any specific limitation on this.

[0050] Figure 2 FIG is a schematic diagram of a satellite telemetry method according to an embodiment of the present disclosure. Figure 2 As shown, the satellite telemetry method includes:

[0051] S200: During satellite launch, within time t after the sailboard is deployed, a dedicated orbital telemetry package is collected. This dedicated orbital telemetry package includes one or more of the following: energy system orbital telemetry, attitude and orbit control subsystem orbital telemetry, and attitude and orbit control standalone orbital telemetry. Where t is a time greater than 0 pre-set based on experimental data, for example, 5 minutes.

[0052] In one embodiment, during launch, the satellite device continuously monitors the deployment of the sailboard. Once deployment is detected, a timer is triggered to begin. Within the time t from the start of the timer, dedicated telemetry packets for orbit entry are delayed at intervals of T1 seconds (e.g., 4 seconds), providing relatively intensive telemetry sampling before the satellite performs critical actions before entering orbit. If the sailboard is deployed and the time has exceeded time t, regular telemetry packet collection is performed, with a regular telemetry packet collection frequency T2 slower than T1, for example, T2 set to 16 seconds.

[0053] For example, the information included in the orbital telemetry package is shown in Table 1.

[0054] Table 1

[0055]

[0056]

[0057]

[0058]

[0059] S201: Count key telemetry data based on the collected orbit-entry telemetry packages.

[0060] S202: Sending the dedicated telemetry package and key telemetry data for orbit entry to the ground equipment so that the ground equipment can determine the operation status of the satellite during orbit entry based on the dedicated telemetry package and key telemetry data.

[0061] In one embodiment, the key telemetry data includes any one or more of the following: satellite angular velocity data, satellite angular momentum data, battery pack voltage data, bus voltage data, load current data, and charge and discharge current data.

[0062] Exemplarily, the key telemetry data may include data as shown in Table 2.

[0063] Table 2

[0064]

[0065]

[0066]

[0067] The satellite angular velocity modulus is obtained by taking the modulus of the inertial system angular velocities wbix, wbiy, and wbiz. wbix, wbiy, and wbiz represent the three orthogonal components of the satellite angular velocity in the inertial coordinate system, respectively. When executing step S201, the inertial system angular velocities wbix, wbiy, and wbiz can be periodically obtained from the orbit entry-specific telemetry package. Each time the inertial system angular velocities wbix, wbiy, and wbiz are obtained, the modulus is taken to obtain a satellite angular velocity modulus value at the current moment. Furthermore, the satellite angular modulus values at the current moment are compared with the previous moment to obtain a satellite angular velocity modulus change value at the current moment. Each time a satellite angular velocity modulus change value is obtained, it is compared with the previous satellite angular velocity modulus change value, and so on. The following data is recorded: the maximum satellite angular velocity modulus change value, the moment of the maximum satellite angular velocity modulus change value, the second maximum satellite angular velocity modulus change value, the moment of the second maximum satellite angular velocity modulus change value, the third maximum satellite angular velocity modulus change value, and the moment of the third maximum satellite angular velocity modulus change value.

[0068] In one embodiment, the key telemetry data also includes the suspected collision time and the angular momentum change value corresponding to the suspected collision time. S201 , based on the collected orbit-entry-specific telemetry package, statistically analyzes the key telemetry data in the following manner: regularly obtain the satellite angular velocity from the orbit-entry-specific telemetry package, calculate the satellite angular momentum based on the satellite angular velocity, and calculate the angular momentum change value between the satellite angular momentum at the current moment and the previous moment; if the angular momentum change value is greater than or equal to an angular momentum change threshold, record the angular momentum change value and record the current time as the suspected collision time. When there are multiple suspected collisions, record each time. The angular momentum change threshold is pre-set based on experimental data and can be adjusted later based on actual needs. For example, the key telemetry data may also include the data shown in Table 3.

[0069] Table 3

[0070] Serial number Key telemetry data 1 Suspected collision time 1 2 Satellite angular momentum change value 1 3 Suspected collision time 2 4 Satellite angular momentum change value 2 5 Suspected collision time N 6 Satellite angular momentum change value N

[0071] As a feasible implementation method, the satellite angular momentum can be calculated based on the satellite angular velocity: J = I × W, where J is the satellite angular momentum, I is the satellite inertia, and W is the satellite angular velocity. The satellite inertia I is preset, and the satellite angular velocity W can be directly acquired or obtained by taking the modulus of the inertial system angular velocities wbix, wbiy, and wbiz in the dedicated telemetry package, that is,

[0072]

[0073] Because changes in satellite angular momentum can indicate the severity of a collision, sending this critical telemetry data to ground equipment allows ground personnel to intuitively understand the time at which a suspected collision occurred and the severity of the collision, without requiring complex statistical analysis. Furthermore, because the data in the dedicated orbital telemetry package is more comprehensive, ground personnel can also tailor their analysis to target data around the suspected collision time, focusing on this data for a more accurate review of the satellite's on-orbit performance.

[0074] There are several core risks involved in the deployment of solar panels on satellite equipment, including: a. Jamming of the deployment mechanism (such as failure of lubrication of the panel bearing); b. Collision during the deployment process (such as panels hitting rocket debris, collision of panels on various satellite equipment during the deployment process in a scenario where multiple satellites are launched with one rocket, etc.). The telemetry method proposed in this application can focus on collecting dedicated telemetry packages and key telemetry data within the deployment time t of the panel during satellite launch, and send the dedicated telemetry packages and key telemetry data to ground equipment after the satellite enters the country for the first time. Since the amount of key telemetry data is much smaller than that of the dedicated telemetry package, ground personnel can first analyze the operation of the satellite equipment during the deployment of the panel based on the key telemetry data, and quickly make countermeasures through a small amount of analysis. Subsequently, the dedicated telemetry package can be analyzed according to actual needs to obtain more accurate analysis results.

[0075] Continue to see Figure 3 is a schematic diagram of another satellite telemetry method shown in an embodiment of the present disclosure. Figure 2 Based on the satellite telemetry method shown ( Figure 3 Not shown Figure 2 Steps S200 to S202 in the method further include the following steps:

[0076] S300: When a satellite-rocket separation signal is detected, a separation event packet is collected.

[0077] In one embodiment, the separation event package includes one or more of the following information: separation event number, separation status, separation time, three-axis angular velocity at the time of separation, three-axis inertia of the entire satellite at the time of separation, battery pack voltage at the time of separation, bus voltage at the time of separation, discharge current at the time of separation, battery temperature at the time of separation, and reaction wheel temperature at the time of separation.

[0078] S301: When it is detected that the windsurfing board starts to be deployed, a windsurfing board deployment event packet is collected.

[0079] In one embodiment, a panel deployment event packet includes one or more of the following information: panel deployment event number, panel deployment status, panel deployment time, three-axis angular velocity at panel deployment, three-axis inertia of the entire satellite at panel deployment, SADA solar panel drive structure information at panel deployment, voltage and current at panel deployment, reaction wheel temperature at panel deployment, panel temperature at panel deployment, and battery pack information at panel deployment. The SADA information at panel deployment includes one or more of the following: SADM temperature at panel deployment, SADA stepper motor angle at panel deployment, SADA potentiometer angle at panel deployment, SADA Hall effect sensor angle at panel deployment, and SADA operating status at panel deployment. The voltage and current at panel deployment includes one or more of the following: bus voltage at panel deployment and discharge current at panel deployment. The battery pack information at panel deployment includes one or more of the following: battery pack voltage at panel deployment and battery temperature at panel deployment.

[0080] S302: Send the separation event package and the sailboard deployment event package to the ground equipment.

[0081] In one embodiment, full-scene telemetry data can also be recorded when detecting separation of the rocket and satellite and the deployment of the sails. When an acquisition command is detected from ground equipment, full-scene telemetry data is sent. Full-scene telemetry data refers to all telemetry data on the satellite, such as power information, attitude information, environmental information, etc. of the satellite equipment.

[0082] In one embodiment, after detecting the entry of a satellite, the satellite device executes steps S302 and S202 in the following manner: the satellite device sends telemetry according to the priority of real-time telemetry, asynchronous packet telemetry, and delayed telemetry. Among them, the separation event package, the sailboard deployment event package, and the key telemetry data are sent according to the asynchronous package, the orbit entry-specific telemetry package is sent according to the delayed telemetry package, and the telemetry data collected after the satellite enters the orbit is sent according to the real-time telemetry. In this way, multiple sampling coverage of the satellite's orbit entry status is achieved, providing efficient telemetry data support for the satellite's first entry. On the one hand, it can reduce the difficulty of controlling the ground flight process after the satellite enters the orbit; on the other hand, it can also enable ground personnel to have a more comprehensive understanding of the satellite's operating status during the launch process.

[0083] Figure 4 FIG. 1 is a schematic diagram of the structure of a satellite telemetry device provided in an embodiment of the present application, which can be mounted in a satellite device. Figure 4 As shown, the satellite telemetry device includes:

[0084] The data acquisition module is used to collect orbit-entry telemetry packets during satellite launch within a time t (t greater than 0) after the sailboard is deployed. The orbit-entry telemetry packets include one or more of the following information: energy system orbit-entry telemetry, attitude and orbit control subsystem orbit-entry telemetry, and attitude and orbit control stand-alone orbit-entry telemetry.

[0085] The statistics module is used to collect key telemetry data based on the collected orbit-entry telemetry packages;

[0086] The communication module is used to send the orbit-entry dedicated telemetry package and the key telemetry data to the ground equipment, so that the ground equipment can determine the operating status of the satellite during the orbit-entry period based on the dedicated telemetry package and the key telemetry data.

[0087] In one embodiment, the key telemetry data includes any one or more of the following: satellite angular velocity data, satellite angular momentum data, battery pack voltage data, bus voltage data, load current data, and charge and discharge current data.

[0088] In one embodiment, the key telemetry data also includes a suspected collision time and an angular momentum change value corresponding to the suspected collision time. The statistical module is specifically configured to: periodically obtain the satellite angular velocity from the orbit entry-dedicated telemetry package; calculate the satellite angular momentum based on the satellite angular velocity; calculate the angular momentum change value between the satellite angular momentum at a current moment and a previous moment; and if the angular momentum change value is greater than or equal to an angular momentum change threshold, record the angular momentum change value and record the current time as the suspected collision time.

[0089] In one embodiment, the method further includes: sending a separation event package and a sailboard deployment event package to the ground equipment, wherein the separation event package is collected when a satellite-rocket separation signal is detected; and the sailboard deployment event package is collected when it is detected that the sailboard begins to deploy.

[0090] In one embodiment, the separation event package includes one or more of the following information: separation event number, separation status, separation time, three-axis angular velocity at the time of separation, three-axis inertia of the entire satellite at the time of separation, battery pack voltage at the time of separation, bus voltage at the time of separation, discharge current at the time of separation, battery temperature at the time of separation, and reaction wheel temperature at the time of separation.

[0091] In one embodiment, the panel deployment event package includes one or more of the following information: panel deployment event number, panel deployment status, three-axis angular velocity at the time of panel deployment, three-axis inertia of the entire satellite at the time of panel deployment, SADA solar panel drive structure information at the time of panel deployment, voltage and current at the time of panel deployment, reaction wheel temperature at the time of panel deployment, panel temperature at the time of panel deployment, and battery pack information at the time of panel deployment.

[0092] In one embodiment, the communication module is specifically used to: when a satellite entry is detected, telemetry is sent according to the priority of real-time telemetry, asynchronous packet telemetry and delayed telemetry; wherein the separation event package, the sailboard deployment event package and key telemetry data are sent according to the asynchronous package; the orbit entry-specific telemetry package is sent according to the delayed telemetry package; the telemetry data collected after the satellite entry is sent according to the real-time telemetry.

[0093] In one embodiment, the data acquisition module is also used to record full-scene telemetry data when detecting the separation of the satellite and the rocket and the deployment of the sailboard; the communication module is also used to send the full-scene telemetry data when detecting the acquisition instruction sent by the ground equipment.

[0094] The satellite telemetry device provided in this embodiment is used to implement the aforementioned satellite telemetry method. Therefore, the specific implementation of the satellite telemetry device can be found in the embodiment of the satellite telemetry method in the above text and will not be repeated here.

[0095] Figure 5 This is a schematic diagram of the structure of a satellite device provided in an embodiment of the present application. Figure 5 As shown, the satellite device includes one or more processors 501 , one or more memories 502 coupled to the processors 501 , and one or more communication modules 500 coupled to the processors 501 .

[0096] The communication module 500 is used for two-way communication. The communication module 500 has at least one antenna to facilitate communication. The communication interface may represent any interface necessary for communicating with other network elements.

[0097] Processor 501 may be of any type suitable for the local technology network and may include, by way of non-limiting example, one or more of the following: a general purpose computer, a special purpose computer, a microprocessor, a digital signal processor (DSP), and a processor based on a multi-core processor architecture. A satellite device may have multiple processors, such as application specific integrated circuit chips, which are driven in time to a clock that synchronizes the master processor.

[0098] The memory 502 may include one or more non-volatile memories and one or more volatile memories. Examples of non-volatile memories include, but are not limited to, read-only memory (ROM) 5021, electrically programmable read-only memory (EPROM), flash memory, hard disks, compact disks (CDs), digital video disks (DVDs), and other magnetic and / or optical memories. Examples of volatile memories include, but are not limited to, random access memory (RAM) 5020 and other volatile memories that do not persist during a power outage.

[0099] The computer program 503 includes computer executable instructions that are executed by the associated processor 501. The computer program 503 may be stored in the ROM 5021. The processor 501 may perform any appropriate actions and processes by loading the computer program 503 into the RAM 5020.

[0100] The embodiment of the present application can be implemented by computer program 503, so that the satellite device can execute the reference Figure 2 and Figure 3 The embodiments of the present application may also be implemented by hardware or by a combination of software and hardware.

[0101] In some embodiments, computer program 503 may be tangibly embodied in a computer-readable medium, which may be contained in a satellite device (e.g., memory 502) or other storage device accessible to the satellite device. The satellite device may load computer program 503 from the computer-readable medium into RAM 5020 for execution. The computer-readable medium may include any type of tangible non-volatile memory, such as ROM, EPROM, flash memory, hard disk, CD, DVD, etc. The computer-readable medium stores computer program 503.

[0102] In general, various embodiments of the present application may be implemented in hardware or dedicated circuits, software, logic, or any combination thereof. Certain aspects may be implemented in hardware, while other aspects may be implemented in firmware or software, which may be executed by a controller, microprocessor, or other satellite device. Although various aspects of the embodiments of the present application are shown and described as block diagrams, flow charts, or using some other graphical representation, it should be understood that, as non-limiting examples, the blocks, devices, management platforms, techniques, or methods described herein may be implemented in hardware, software, firmware, dedicated circuits or logic, general-purpose hardware or a controller or other satellite device, or some combination thereof.

[0103] The present application also provides at least one computer program product tangibly stored on a non-transitory computer readable storage medium. The computer program product includes computer executable instructions, such as instructions included in program modules, which are executed in a device on a target real or virtual processor to perform the above-mentioned reference Figure 2 and Figure 3 The method described. Generally, program modules include routines, programs, libraries, objects, classes, components, data structures, etc. that perform specific tasks or implement specific abstract data types. In various embodiments, the functionality of program modules can be combined or separated between program modules as needed. Machine-executable instructions for program modules can be executed on local or distributed devices. In distributed devices, program modules can be located in local and remote storage media.

[0104] The program code that is used to carry out the method for the present application can be written with any combination of one or more programming languages.These program codes can be provided to the processor or controller of general-purpose computer, special-purpose computer or other programmable data processing equipment, make when program code is carried out by processor or controller, the function / operation specified in flow chart and / or block diagram is realized.Program code can be carried out fully on machine as independent software package, partly on machine, partly on machine, partly on remote machine, partly on remote machine, or all on remote machine or server.

[0105] In the context of this application, computer program codes or related data may be carried by any suitable carrier to enable a device, apparatus or processor to perform various processes and operations as described above. Examples of carriers include signals, computer-readable media, etc.

[0106] The computer-readable medium may be a computer-readable signal medium or a computer-readable storage medium. The computer-readable medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor management platform, device, or apparatus, or any suitable combination of the foregoing. More specific examples of computer-readable storage media include an electrical connection having one or more wires, a portable computer floppy disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0107] In addition, although operations are described in a specific order, this should not be understood as requiring the specific order or sequence shown to perform these operations, or to perform all operations shown, to obtain the required result. In some cases, multi-tasking and parallel processing may be advantageous. Similarly, although several specific implementation details are included in the above discussion, these details should not be interpreted as limiting the scope of the application, but can be interpreted as a description of the specific features of a particular embodiment. Some features described in the context of a separate embodiment also can be combined in a single embodiment. On the contrary, the various features described in the context of a single embodiment also can be realized individually or in any suitable sub-combination in multiple embodiments.

[0108] Although the present application has been described in language specific to structural features and / or methodological acts, it should be understood that the present application defined in the appended claims is not necessarily limited to the specific features or acts described above. Rather, the specific features and acts described above are disclosed as example forms of implementing the claims.

Claims

1. A satellite telemetry method, characterized in that: include: During satellite launch, within time t after the sailboard is deployed, a dedicated orbital telemetry package is collected. The dedicated orbital telemetry package includes one or more of the following information: energy system orbital telemetry, attitude and orbit control subsystem orbital telemetry, and attitude and orbit control stand-alone orbital telemetry; where t is greater than 0; Count key telemetry data based on the collected orbit-entry telemetry packages; The dedicated telemetry package for orbit entry and the key telemetry data are sent to ground equipment so that the ground equipment can determine the operating status of the satellite during orbit entry based on the dedicated telemetry package and the key telemetry data.

2. The method according to claim 1, wherein The key telemetry data includes any one or more of the following: satellite angular velocity data, satellite angular momentum data, battery pack voltage data, bus voltage data, load current data, and charge and discharge current data.

3. The method according to claim 1 or 2, wherein: The key telemetry data also includes the suspected collision time and the angular momentum change value corresponding to the suspected collision time. The key telemetry data is statistically analyzed based on the collected orbital insertion dedicated telemetry package, including: Regularly acquiring the satellite angular velocity from the orbit-entry dedicated telemetry package; Calculate satellite angular momentum based on satellite angular velocity; Calculate the change in angular momentum between the satellite angular momentum at the current moment and the previous moment; If the angular momentum change value is greater than or equal to the angular momentum change threshold, the angular momentum change value is recorded, and the current time is recorded as the suspected collision time.

4. The method according to any one of claims 1 to 3, wherein The method further comprises: The separation event package and the sailboard deployment event package are sent to the ground equipment. The separation event package is collected when the satellite-rocket separation signal is detected; the sailboard deployment event package is collected when it is detected that the sailboard starts to deploy.

5. The method according to claim 4, wherein The separation event package includes one or more of the following information: separation event number, separation status, separation time, three-axis angular velocity at the time of separation, three-axis inertia of the entire satellite at the time of separation, battery pack voltage at the time of separation, bus voltage at the time of separation, discharge current at the time of separation, battery temperature at the time of separation, and reaction wheel temperature at the time of separation.

6. The method according to claim 4, wherein The sailboard deployment event package includes one or more of the following information: sailboard deployment event number, sailboard deployment status, three-axis angular velocity at the time of sailboard deployment, three-axis inertia of the entire satellite at the time of sailboard deployment, SADA solar sailboard drive structure information at the time of sailboard deployment, voltage and current at the time of sailboard deployment, reaction wheel temperature at the time of sailboard deployment, sailboard temperature at the time of sailboard deployment, and battery pack information at the time of sailboard deployment.

7. The method according to claim 5, wherein The sending of the orbit entry dedicated telemetry package and the key telemetry data to ground equipment includes: When the satellite entry is detected, telemetry is sent according to the priority of real-time telemetry, asynchronous packet telemetry and delayed telemetry; among them, the separation event package, the sailboard deployment event package and key telemetry data are sent according to the asynchronous package; the orbit entry-specific telemetry package is sent according to the delayed telemetry package; the telemetry data collected after the satellite entry is sent according to the real-time telemetry.

8. The method according to any one of claims 1 to 7, wherein: The method further comprises: When the separation of the rocket and satellite is detected and the sail begins to deploy, full-scene telemetry data recording is performed; When an acquisition instruction sent by the ground equipment is detected, the full-scene telemetry data is sent down.

9. A satellite device, characterized in that: include: at least one processor; as well as At least one memory having instructions stored thereon, which, when executed individually or collectively by the at least one processor, cause the satellite device to perform the method according to any one of claims 1 to 8.

10. A computer storage medium, characterized in that The computer storage medium stores instructions, which, when executed individually or collectively by at least one processor of a satellite device, cause the satellite device to perform the method according to any one of claims 1 to 8.

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