Real-time control method for satellite laser payload outside China

Abstract

The application provides a method for real-time measurement and control of a satellite laser load outside a country, comprising: inputting configuration parameters of a first satellite on a ground station, the first satellite being provided with a first laser load; establishing microwave inter-satellite link communication between a second satellite and the first satellite, the second satellite being provided with a second laser load; when the first satellite runs to outside the country and the second satellite is in the country, configuring a measurement and control mode of the first satellite as an inter-satellite telemetry mode of the laser load and / or an inter-satellite remote control mode of the laser load; in the inter-satellite telemetry mode of the laser load, the first laser load sends first laser telemetry data to the second satellite through the microwave inter-satellite link, and the second satellite down-transmits the first laser telemetry data to the ground station; in the inter-satellite remote control mode of the laser load, the ground station inputs first laser load remote control instructions to be input to the first satellite to the second satellite, and the second satellite sends the first laser load remote control instructions to the first satellite through the microwave inter-satellite link.

Description

TECHNICAL FIELD

[0001] The present application mainly relates to the field of satellite TT&C technology, and particularly relates to a method for real-time measurement and control of a satellite laser load in a foreign country. BACKGROUND

[0002] With the increasing demand for high-speed information transmission in the information age, more and more satellites are equipped with laser inter-satellite link loads to achieve high-speed data communication and precise measurement. However, due to the complexity of laser inter-satellite link load technology, many optical components and complex rotating mechanisms are involved. In order to ensure stable link establishment of laser terminal equipment and realize laser communication and ranging functions, the satellite generally needs to be calibrated and debugged for a certain period of time after being launched into orbit, and the calibration test between two satellites is particularly important. Since the satellite ground monitoring stations of China are mainly located in the domestic, the observation arc coverage of the satellite is low, and the domestic injection station cannot observe the satellite in the foreign country for a long time. Therefore, the laser terminal equipment generally cannot meet the measurement and control requirements of the two satellites in the visible arc segment during the initial debugging period after being launched into orbit.

[0003] Currently, the measurement and control method for the laser inter-satellite link load of the satellite in orbit mainly includes: when the satellite is located in the domestic, the satellite is injected with relevant instructions and data through the ground conventional measurement and control system, and the laser telemetry data of the satellite in the domestic is observed in real time. Such a measurement and control method has the following disadvantages for the laser inter-satellite link load: after the satellite runs to the foreign country, the instructions cannot be injected in time, and the laser telemetry data cannot be observed in real time, which will result in that the laser load cannot be effectively tested for a long time, and the running state of the laser load cannot be ensured. If the laser inter-satellite link load has a safety problem in the foreign country, it cannot be found and handled in time, and even the function of the laser load can be affected.

[0004] Therefore, it is necessary to provide a new measurement and control method for the satellite laser inter-satellite link load network to make up for the disadvantages of insufficient ground monitoring station layout and low satellite observation arc coverage, realize timely injection of laser load instructions and real-time telemetry monitoring, and realize real-time monitoring of the laser load telemetry of the satellite in the foreign country. SUMMARY

[0005] The technical problem to be solved by the present application is to provide a quasi-real-time and safe method for real-time measurement and control of a satellite laser load in a foreign country.

[0006] To solve the above technical problems, the application provides a satellite laser load overseas real-time measurement and control method, which comprises the following steps: a ground station is used to input configuration parameters of a first satellite, wherein the first satellite is provided with a first laser load; a second satellite and the first satellite establish microwave inter-satellite link communication, wherein the second satellite is provided with a second laser load; when the first satellite runs to overseas and the second satellite is in domestic, the measurement and control mode of the first satellite is configured as a laser load inter-satellite telemetry mode and / or a laser load inter-satellite remote control mode; in the laser load inter-satellite telemetry mode, the first laser load sends first laser telemetry data to the second satellite through the microwave inter-satellite link, and the second satellite down-transmits the first laser telemetry data to the ground station; in the laser load inter-satellite remote control mode, the ground station inputs first laser load remote control instructions to be input to the first satellite to the second satellite, and the second satellite sends the first laser load remote control instructions to the first satellite through the microwave inter-satellite link.

[0007] In an embodiment of the application, the method further comprises: configuring the measurement and control mode of the first satellite as a laser load safety mode; in the laser load safety mode, when the state of the first laser load is abnormal, the first satellite executes corresponding delay remote control instructions according to the instruction execution time of a delay instruction event table.

[0008] In an embodiment of the application, the delay remote control instructions comprise a shutdown operation of the first laser load.

[0009] In an embodiment of the application, the delay remote control instructions are stored in a delay instruction cache area of the first laser load, the first laser load accesses the delay instruction cache area through the delay instruction event table, and when the on-board time of the first satellite reaches the instruction execution time, the first laser load executes the delay remote control instructions corresponding to the instruction execution time.

[0010] In an embodiment of the application, the method further comprises: when the first satellite is in domestic, the ground station inputs the delay instruction event table to the first satellite, wherein the delay instruction event table comprises the instruction execution time and the delay remote control instructions, and the instruction execution time and the delay remote control instructions correspond to each other.

[0011] In an embodiment of the application, in the laser load safety mode, the method further comprises: when the first satellite runs to overseas and the second satellite is in domestic, the ground station inputs a clear delay instruction event table and / or the delay instruction event table to the second satellite, and the second satellite sends the clear delay instruction event table and / or the delay instruction event table to the first satellite through the microwave inter-satellite link.

[0012] In an embodiment of the present application, further comprising: when the state of the first laser payload is normal, clearing the clear delay command event table on the first satellite.

[0013] In an embodiment of the present application, in the laser payload safety mode, further comprising: when the state of the first laser payload is normal, the first laser payload accessing a delay command cache according to the clear delay command event table, and clearing the delay remote control command in the delay command cache.

[0014] In an embodiment of the present application, further comprising: when the first satellite is in the territory, configuring the first satellite in a direct TT&C mode, in which the first satellite directly transmits the first laser telemetry data to the ground station, and the ground station directly injects the first laser payload remote control command to the first satellite.

[0015] In an embodiment of the present application, the first satellite and the second satellite are both Beidou-3 satellites.

[0016] The overseas real-time TT&C method of the present application provides a laser payload inter-satellite TT&C mode for the laser payload, in which the first laser telemetry data located overseas can be transmitted to the ground station through the second satellite, and the quasi-real-time TT&C of the laser terminal payload of the overseas satellite can be realized. In addition, the overseas real-time TT&C method of the present application also provides a laser payload inter-satellite remote control mode and a laser payload safety mode, which further strengthens the TT&C of the laser terminal payload of the overseas satellite, and ensures the safety of the laser inter-satellite link payload. BRIEF DESCRIPTION OF DRAWINGS

[0017] The accompanying drawings are included to provide a further understanding of the present application, and are incorporated and constitute a part of this application, illustrate embodiments of the present application, and together with the description serve to explain the principles of the present application. In the drawings:

[0018] Figure 1 is an exemplary flowchart of the overseas real-time TT&C method of the satellite laser payload in an embodiment of the present application;

[0019] Figure 2 is one of the application scenarios of the overseas real-time TT&C method in an embodiment of the present application;

[0020] Figure 3 is another application scenario of the overseas real-time TT&C method in an embodiment of the present application;

[0021] Figure 4 is an exemplary flowchart of the overseas real-time TT&C method in the laser payload inter-satellite telemetry mode in an embodiment of the present application;

[0022] Figure 5 is an exemplary flowchart of the real-time measurement and control method of the overseas embodiment in the laser payload inter-satellite remote control mode;

[0023] Figure 6 is an exemplary flowchart of the real-time measurement and control method of the overseas embodiment in the laser payload safety mode. DETAILED DESCRIPTION

[0024] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some examples or embodiments of the present application, and for those skilled in the art, the present application can be applied to other similar scenarios without creative labor on the basis of these drawings. Unless the context clearly indicates otherwise or otherwise stated, the same reference numbers in the drawings represent the same structures or operations.

[0025] As shown in the present application and claims, unless the context clearly indicates otherwise or otherwise stated, "one", "a", "an", and / or "the" do not specifically refer to the singular, but can also include the plural. Generally speaking, the terms "comprise" and "include" only indicate the inclusion of the steps and elements explicitly identified, and these steps and elements do not constitute an exclusive list, and the method or device can also include other steps or elements.

[0026] Unless otherwise specifically stated, the relative arrangement of the components and steps, numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application. At the same time, it should be understood that for the purpose of description, the sizes of the various parts shown in the drawings are not drawn in accordance with the actual proportional relationship. The technology, methods and devices known to those skilled in the relevant art can not be discussed in detail, but in appropriate cases, the technology, methods and devices should be considered as part of the authorized description. In all examples shown and discussed here, any specific value should be interpreted as merely exemplary, and not as a limitation. Therefore, other examples of exemplary embodiments can have different values. It should be noted that similar reference numbers and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further discussed in subsequent drawings.

[0027] Moreover, it needs to be explained that the terms of 'first','second' and the like are used to define parts only for the convenience of distinguishing the corresponding parts, and the above terms have no special meaning unless otherwise stated, and therefore cannot be understood as the limitation of the protection scope of the present application. In addition, although the terms used in the present application are selected from the commonly known and used terms, some terms mentioned in the specification of the present application can be selected by the applicant according to his or her judgment, and the detailed meanings thereof are described in the relevant part of the description. In addition, the present application is required to be understood not only by the actual terms used, but also by the meaning implied by each term.

[0028] Flowcharts are used in the present application to illustrate the operations performed by the system according to the embodiments of the present application. It should be understood that the preceding or following operations are not necessarily performed in sequence. On the contrary, various steps can be processed in reverse order or simultaneously. Meanwhile, or other operations are added to these processes, or one or more steps of operations are removed from these processes.

[0029] The method for real-time measurement and control of the satellite laser payload outside the country according to the present application can be applied to any satellite with a laser payload.

[0030] Figure 1 is an exemplary flowchart of the method for real-time measurement and control of the satellite laser payload outside the country according to an embodiment of the present application. Referring to Figure 1 The method for real-time measurement and control outside the country according to the embodiment includes the following steps:

[0031] Step S110: The ground station uploads the configuration parameters of the first satellite, and the first satellite is provided with a first laser payload;

[0032] Step S120: The second satellite and the first satellite establish microwave inter-satellite link communication, and the second satellite is provided with a second laser payload;

[0033] Step S130: When the first satellite runs outside the country and the second satellite is inside the country, the measurement and control mode of the first satellite is configured as a laser payload inter-satellite telemetry mode and / or a laser payload inter-satellite telecontrol mode. In the laser payload inter-satellite telemetry mode, the first laser payload sends the first laser telemetry data to the second satellite through the microwave inter-satellite link, and the second satellite downlinks the first laser telemetry data to the ground station. In the laser payload inter-satellite telecontrol mode, the ground station uploads the first laser payload telecontrol command to be uploaded to the first satellite to the second satellite, and the second satellite sends the first laser payload telecontrol command to the first satellite through the microwave inter-satellite link.

[0034] The above steps S110 to S130 are described below in combination with Figure 2 and Figure 3 .

[0035] As Figure 2As shown in FIG. 1, a ground station 210, a first satellite 220 and a second satellite 230 are shown. The coverage area of the ground station 210 is represented by a dashed oval, and both the first satellite 220 and the second satellite 230 are within the coverage area of the ground station 210. In this scenario, the ground station 210 can directly upload information to the first satellite 220 and the second satellite 230, and directly obtain information from the first satellite 220 and the second satellite 230. Figure 2 As shown in FIG. 2, in this scenario, the first satellite 220 moves out of the coverage area of the ground station 210. At this time, the ground station 210 cannot directly upload information to the first satellite 220, nor can it obtain information from the first satellite 220, resulting in the first satellite 220 and its payload being unable to be effectively controlled for a long time, and the running state of the satellite and the payload cannot be ensured to be normal, causing disconnection.

[0036] As shown in FIG. 3, in this scenario, the first satellite 220 moves out of the coverage area of the ground station 210, and the second satellite 230 is within the coverage area of the ground station 210. At this time, the ground station 210 cannot directly upload information to the first satellite 220, nor can it obtain information from the first satellite 220, resulting in the first satellite 220 and its payload being unable to be effectively controlled for a long time, and the running state of the satellite and the payload cannot be ensured to be normal, causing disconnection. Figure 3 As shown in FIG. 4, in this scenario, the first satellite 220 moves out of the coverage area of the ground station 210, and the second satellite 230 is within the coverage area of the ground station 210. At this time, the ground station 210 cannot directly upload information to the first satellite 220, nor can it obtain information from the first satellite 220, resulting in the first satellite 220 and its payload being unable to be effectively controlled for a long time, and the running state of the satellite and the payload cannot be ensured to be normal, causing disconnection. Figure 3 As shown in FIG. 5, in this scenario, the first satellite 220 moves out of the coverage area of the ground station 210, and the second satellite 230 is within the coverage area of the ground station 210. At this time, the ground station 210 cannot directly upload information to the first satellite 220, nor can it obtain information from the first satellite 220, resulting in the first satellite 220 and its payload being unable to be effectively controlled for a long time, and the running state of the satellite and the payload cannot be ensured to be normal, causing disconnection.

[0037] Specifically, in step S110, the first satellite 220 is provided with a first laser payload, and the specific model and quantity of the first laser payload are not limited in the present application.

[0038] In step S120, the second satellite 230 refers to any satellite that can establish microwave inter-satellite link communication with the first satellite 220, and is provided with a second laser payload, and the specific model and quantity of the second laser payload are not limited in the present application. Further, the first laser payload on the first satellite 220 can establish laser inter-satellite link communication with the second laser payload on the second satellite 230, thereby performing calibration testing between the two satellites.

[0039] In some embodiments, the first satellite 220 and the second satellite 230 are both Beidou-III project satellites, and microwave inter-satellite link communication can be established between the first satellite 220 and the second satellite 230.

[0040] In step S130, when the first satellite 220 and the second satellite 230 are within the coverage area of the ground station 210, Figure 3In the scenario shown, the telemetry and control mode of the first satellite 220 is configured as a laser payload inter-satellite telemetry mode and / or a laser payload inter-satellite remote control mode. In some embodiments, a laser payload inter-satellite telemetry mode and / or a laser payload inter-satellite remote control mode can be preset for the first satellite 220 in the configuration parameters of step S110. When the first satellite 220 is operating within the territory, it adopts the normal telemetry and control mode. When the first satellite 220 is operating outside the territory, its telemetry and control mode is switched to the preset laser payload inter-satellite telemetry mode and / or laser payload inter-satellite remote control mode. The laser payload inter-satellite telemetry mode and the laser payload inter-satellite remote control mode are novel telemetry and control modes proposed in this application to solve the problem that the first satellite 220 cannot be directly telemetry and control when it is outside the territory. Using the first satellite 220 being outside the territory as a trigger condition, when the trigger condition is met, the first satellite 220 automatically switches its telemetry and control mode to the laser payload inter-satellite telemetry and control mode and / or the laser payload inter-satellite remote control mode.

[0041] Figure 4 This is an exemplary flowchart of a real-time telemetry and control method for overseas operations according to an embodiment of this application, in the inter-satellite telemetry mode of a laser payload. (Reference) Figure 4 As shown, the overseas real-time monitoring and control method of this embodiment includes the following steps:

[0042] Step S410: The ground station 210 uploads the configuration parameters of the first satellite 220.

[0043] This step is the same as step S110. It can be understood that this step is performed while the first satellite 220 is within the territory, and the configuration parameters are directly uploaded by the ground station 210. The configuration parameters include those required for laser payload calibration, thereby enabling the first and second laser payloads to be paired.

[0044] Step S412: The first satellite 220 and the second satellite 230 establish microwave inter-satellite link communication. Furthermore, by establishing microwave inter-satellite link communication, the first and second satellites can achieve inter-satellite communication and other functions.

[0045] Step S414: Determine whether the first satellite 220 has moved outside the territory. If yes, proceed to step S416; otherwise, proceed to step S424.

[0046] Step S416: When the first satellite 220 reaches its outer perimeter, the telemetry and control mode will be switched to laser payload inter-satellite telemetry mode. In this step, the telemetry and control modes of ground station 210, the first satellite 220, and the second satellite 230 will all be switched to laser payload inter-satellite telemetry mode.

[0047] Step S418: The first laser payload transmits the first laser telemetry data to the second satellite 230 via a microwave inter-satellite link.

[0048] Step S420: The second satellite 230 transmits the first laser telemetry data to the ground station 210. In this step, this application does not restrict the method of transmitting the first laser telemetry data. In some embodiments, the second satellite 230 transmits the first laser telemetry data to the ground station 210 in real time. In some embodiments, the second satellite 230 periodically packages and transmits the first laser telemetry data over a period of time to the ground station 210.

[0049] Step S422: Ground station 210 receives the first laser telemetry data and uses it to conduct real-time observations of the first satellite. The observed content includes information related to laser telemetry.

[0050] Step S424: When the first satellite 220 is within the territory, the telemetry and control mode remains in direct telemetry and control mode. In direct telemetry and control mode, the first satellite 220 directly transmits the first laser telemetry data to the ground station 210.

[0051] In some embodiments, Figure 3 In the scenario shown, the overseas real-time telemetry and control method of this application also provides a telemetry and control mode, namely, the laser payload inter-satellite remote control mode. In this mode, the ground station 210 transmits the first laser payload remote control command to be transmitted to the first satellite 220 to the second satellite 230. The second satellite 230 then transmits the first laser payload remote control command to the first satellite 220 via a microwave inter-satellite link. According to this embodiment, when the first satellite 220 is operating overseas, both the first satellite 220 and the second satellite 230 can automatically switch to the laser payload inter-satellite remote control mode, and the ground station 210 also switches to the laser payload inter-satellite remote control mode. The ground station 210 selects one or more second satellites 230 located within its territory as command receiving satellites, and then these one or more second satellites 230 forward the command to the first satellite 220.

[0052] In some embodiments, in the laser payload inter-satellite remote control mode, a second satellite 220 that is closer to the first satellite 220 is selected as a relay station.

[0053] Figure 5 This is an exemplary flowchart of a real-time overseas telemetry and control method according to an embodiment of this application in the inter-satellite remote control mode of a laser payload. (Reference) Figure 5 As shown, the overseas real-time monitoring and control method of this embodiment includes the following steps:

[0054] Step S510: The ground station 210 uploads the configuration parameters of the first satellite 220.

[0055] Step S512: The first satellite 220 and the second satellite 230 establish microwave inter-satellite link communication.

[0056] Step S514: Determine whether the first satellite 220 is running to the out-of-country. If yes, execute step S516; if no, execute step S524.

[0057] Step S516: When the first satellite 220 runs to the out-of-country, switch the TT&C mode to the laser payload intersatellite remote control mode. As described above, in this step, the TT&C modes of the ground station 210, the first satellite 220 and the second satellite 230 are all switched to the laser payload intersatellite remote control mode.

[0058] Step S518: The ground station 210 uploads instructions to the second satellite 230.

[0059] Step S520: The second satellite 230 sends the instructions to the first satellite 220 through the microwave intersatellite link.

[0060] Step S522: The first laser payload receives and executes the corresponding instructions. It can be understood that the instructions in this step S520 include instructions for controlling the first laser payload.

[0061] Step S524: When the first satellite 220 is in the country, the TT&C mode remains the direct TT&C mode.

[0062] Step S526: In the direct TT&C mode, the ground station 210 directly uploads instructions to the first satellite 220.

[0063] In some embodiments, in the two scenarios shown in FIGS. 1 and 2, the out-of-country real-time TT&C method of the present application further provides a TT&C mode, i.e., a laser payload safety mode, in which, when the state of the first laser payload is abnormal, the first satellite 220 executes the corresponding delayed remote control instructions according to the instruction execution time of the delayed instruction event table. Figure 2 and Figure 3 In the two scenarios shown in FIGS. 1 and 2, the out-of-country real-time TT&C method of the present application further provides a TT&C mode, i.e., a laser payload safety mode, in which, when the state of the first laser payload is abnormal, the first satellite 220 executes the corresponding delayed remote control instructions according to the instruction execution time of the delayed instruction event table.

[0064] It should be noted that when the state of the first laser payload is normal, both the laser payload intersatellite TT&C mode and the laser payload intersatellite remote control mode can be normally performed. However, when the state of the first laser payload is abnormal, it can not be possible to normally perform the laser payload intersatellite TT&C mode and the laser payload intersatellite remote control mode. Therefore, in this case, the present application provides a laser payload safety mode so that the first satellite can control the first laser payload when the first laser payload is abnormal.

[0065] In some embodiments, the instructions are given in the form of an event table. For example, the event table is a table including time and corresponding execution instructions, from which it can be determined what instructions to execute at what time.

[0066] In some embodiments, the switching of the TT&C mode can be performed by an event table. For example, a first event table is uploaded to the first satellite 220, and the first event table includes an instruction for switching the TT&C mode to the laser payload inter-satellite TT&C mode when the first satellite 220 is located outside the ground station 210; or an instruction for switching the TT&C mode to the laser payload inter-satellite remote control mode; or an instruction for switching the TT&C mode to the laser payload inter-satellite TT&C mode and the laser payload inter-satellite remote control mode.

[0067] Suppose that the laser payload inter-satellite TT&C mode is mode A, the laser payload inter-satellite remote control mode is mode B, and the laser payload safety mode is mode C. The TT&C mode of the first satellite 220 can be any combination of A, B, and C, and the three modes can coexist or exist independently.

[0068] In some embodiments, the TT&C mode of the first satellite 220 can always be the laser payload safety mode. In order to ensure the safety of the first satellite 220 and avoid disconnection, the laser payload safety mode can always be enabled.

[0069] The delayed remote control instruction refers to an instruction to be executed after a certain time, especially an instruction to be executed for the first laser payload, such as a shutdown, restart, etc.

[0070] In the laser payload safety mode, the state anomaly of the first laser payload can be that it cannot work normally, or that the inter-satellite telemetry mode cannot monitor the state of the first laser payload due to a communication failure of the microwave inter-satellite link.

[0071] In some embodiments, the delayed remote control instruction includes a shutdown operation of the first laser payload. In the delayed instruction event table, it can be set that when the state anomaly of the first laser payload is detected, the first laser payload shutdown operation is triggered, and the delay is almost 0. In the delayed instruction event table, it can also be set that at time T, the shutdown operation of the first laser payload is performed. The time T can be an absolute time or a relative time. For example, the time T is an on-board time, which is an absolute time. For another example, the time T refers to the time length during which the first satellite is located outside, which is a relative time.

[0072] In some embodiments, in the laser payload safety mode, it can also be set that when the first satellite 220 is located outside for more than a preset time T1, the shutdown operation of the first laser payload is performed, regardless of whether the state of the first laser payload is normal. According to these embodiments, without the need for data outside, energy and data transmission can be saved by shutdown, and other security risks caused by startup can also be avoided.

[0073] In some embodiments, in the laser payload safety mode, the delay remote control instruction is stored in a delay instruction cache area of the first laser payload, the first laser payload accesses the delay instruction cache area through a delay instruction event table, and when the on-board time of the first satellite 220 reaches the instruction execution time, the first laser payload executes the delay remote control instruction corresponding to the instruction execution time.

[0074] In some embodiments, the delay instruction event table is pre-injected into the first satellite 220 by the ground station 210, and in the delay instruction event table, the instruction execution time and the delay remote control instruction correspond to each other. If the first satellite 220 is located overseas and the second satellite 230 is located in the territory, the delay instruction event table can also be injected into the second satellite 230 by the ground station 210, and then transmitted to the first satellite 220 by the second satellite 230 through the microwave inter-satellite link.

[0075] In some embodiments, when the first laser payload is working normally, the clear delay instruction event table can also be injected into the first satellite 220. The clear delay instruction event table includes the time T2 and the corresponding clear delay instruction in the instruction execution time table, i.e., the delay instruction is cleared at time T2, so that the instruction event table of the first satellite 220 does not include the delay remote control instruction. According to these embodiments, the storage burden of the cache area can be reduced, and the safety risk caused by executing the delay instruction due to errors can be avoided. According to these embodiments, in the Figure 2 In the scenario shown in FIG. 8, the clear delay instruction event table can also be injected into the first satellite 220 by the ground station 210, or in the Figure 3 In the scenario shown in FIG. 8, the clear delay instruction event table can also be injected into the first satellite 220 by the ground station 210, or in the

[0076] Figure 6 FIG. 9 is an exemplary flowchart of the overseas real-time measurement and control method in the laser payload safety mode according to an embodiment of the present application. Referring to FIG. 9, the overseas real-time measurement and control method according to the embodiment includes the following steps: Figure 6

[0077] Step S610: According to the overseas test end time Tend of the first satellite 220, the delay instruction event table ComEvent is set to be executed at time Tend.

[0078] In this step, the overseas test end time Tend of the first satellite 220 can be obtained according to the test requirement, so the execution time in the data field of the delay instruction event table ComEvent can be set to Tend in advance.

[0079] ​Step S612: The ground station 210 injects the delay command event table ComEvent to the first satellite 220, and the first laser payload stores the ComEvent in the corresponding buffer area after receiving the ComEvent. It can be understood that the first laser payload has a corresponding memory as the buffer area.

[0080] Step S614: The first satellite 220 runs to the out-of-bound.

[0081] Step S616: The laser payload safety mode is started.

[0082] It should be noted that, Figure 6 The embodiment shown monitors the running of the first satellite 220 to the out-of-bound as the trigger for starting the laser payload safety mode. In other embodiments, the first satellite 220 can always start the laser payload safety mode without the trigger of step S614.

[0083] Step S618: It is judged whether the working state of the first laser payload is normal, if yes, step S624 is executed; if not, step S620 is executed.

[0084] Step S620: The first laser payload accesses the delay command buffer area through the event table.

[0085] Step S622: At the Tend moment, the first laser payload executes the delay command event table ComEvent, that is, autonomously executes the shutdown command according to the event table.

[0086] Step S624: When the working state of the first laser payload is normal, the clear command event table is injected through the microwave inter-satellite link to clear the ComEvent from the buffer area.

[0087] In some embodiments, in step S624, the clear command event table is injected through the microwave inter-satellite link at an opportunity. The opportunity can be that the ground station 210 injects the clear command event table when the first satellite 220 runs to the in-bound, or the second satellite 230 injects the clear command event table to the first satellite 220.

[0088] The out-of-bound real-time measurement and control method of the satellite laser payload of the present application provides three different measurement and control modes for the laser payload, can realize the quasi-real-time measurement and control of the laser terminal payload of the out-of-bound satellite, prevent the measurement and control failure, and also ensure the single machine safety of the out-of-bound inter-satellite link payload.

[0089] Having described the basic concepts, it is obvious that the above-described disclosure of the application is merely meant to be exemplary and not restrictive of the application. Various modifications, improvements and changes can be made to the application by those skilled in the art, although not explicitly described herein. Such modifications, improvements and changes are contemplated by the present application and are within the spirit and scope of the exemplary embodiments of the present application.

[0090] Also, the application has used certain terminology in describing the embodiments of the application. As used herein, the terms "one embodiment," "an embodiment," "some embodiments," or "one alternative" are intended to mean that a certain feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the application. Therefore, it is emphasized and should be appreciated that a described "embodiment" or "one embodiment" or "an alternative" is not necessarily a same embodiment as previously mentioned embodiments or alternatives. Additionally, the various features, structures, or characteristics of one or more embodiments of the application can be combined in any suitable manner.

[0091] Similarly, it is to be noted that, in describing embodiments of the application, that which is meant by certain terms is sometimes incorporated by reference within descriptions of one or more embodiments to facilitate understanding of one or more embodiments of the application. Such incorporation by reference is not meant to imply that the described embodiments necessarily require more features than are recited in the claims. In fact, the described embodiments require fewer features than all features recited in the described embodiments.

[0092] Some embodiments use numerical terms to describe quantities of ingredients, properties, and the like. It is to be understood that such numerical terms are used in some examples to describe the approximate, about, or nearly, amount of an ingredient, property, or the like. Unless otherwise specified, "about," "approximate," or "nearly" means that the number can vary by ±20%. Accordingly, numerical parameters such as those included in the exemplary embodiments herein are approximations. Although the numerical parameters are approximations, the numerical values set forth in the specific examples are reported as precisely as practicable. The numerical values in some embodiments contain certain errors necessarily resulting from the standard deviation found in their respective testing measurements.

Claims

1. A method for real-time overseas telemetry and control of a satellite laser payload, characterized in that, include: The ground station records the configuration parameters of the first satellite, which is equipped with a first laser payload; The second satellite establishes a microwave inter-satellite link communication with the first satellite, and the second satellite is equipped with a second laser payload. When the first satellite is operating outside the territory and the second satellite is within the territory, the telemetry and control mode of the first satellite is configured as laser payload inter-satellite telemetry mode and / or laser payload inter-satellite remote control mode. In the laser payload inter-satellite telemetry mode, the first laser payload transmits first laser telemetry data to the second satellite through the microwave inter-satellite link, and the second satellite transmits the first laser telemetry data down to the ground station. In the laser payload inter-satellite remote control mode, the ground station transmits the first laser payload remote control command to be transmitted to the first satellite to the second satellite, and the second satellite transmits the first laser payload remote control command to the first satellite through the microwave inter-satellite link.

2. The overseas real-time monitoring and control method as described in claim 1, characterized in that, Also includes: The telemetry and control mode of the first satellite is configured as the laser payload safety mode. In the laser payload safety mode, when the state of the first laser payload is abnormal, the first satellite executes the corresponding delayed remote control command on time according to the command execution time in the delayed command event table.

3. The overseas real-time monitoring and control method as described in claim 2, characterized in that, The delayed remote control command includes the shutdown operation of the first laser payload.

4. The overseas real-time monitoring and control method as described in claim 3, characterized in that, The delayed remote control command is stored in the delayed command buffer of the first laser payload. The first laser payload accesses the delayed command buffer through the delayed command event table. When the on-board time of the first satellite reaches the command execution time, the first laser payload executes the delayed remote control command corresponding to the command execution time.

5. The overseas real-time monitoring and control method as described in claim 2, characterized in that, Also includes: When the first satellite is within the territory, the ground station adds the delayed instruction event table to the first satellite. The delayed instruction event table includes the instruction execution time and the delayed remote control instruction, and the instruction execution time corresponds to the delayed remote control instruction.

6. The overseas real-time monitoring and control method as described in claim 2, characterized in that, In the laser payload safety mode, the method further includes: when the first satellite is operating outside the territory and the second satellite is inside the territory, the ground station will clear the delay command event table and / or add the delay command event table to the second satellite, and the second satellite will send the clear delay command event table and / or the delay command event table to the first satellite through the microwave inter-satellite link.

7. The overseas real-time monitoring and control method as described in claim 2, characterized in that, Also includes: When the first laser payload is in a normal state, the delay command event table will be cleared and added to the first satellite.

8. The overseas real-time monitoring and control method as described in claim 7, characterized in that, In the laser payload safety mode, the method further includes: when the state of the first laser payload is normal, the first laser payload accesses the delay instruction buffer of the first laser payload according to the clear delay instruction event table, and clears the delay remote control instructions in the delay instruction buffer to zero.

9. The overseas real-time monitoring and control method as described in claim 1, characterized in that, Also includes: When the first satellite is within the territory, the telemetry and control mode of the first satellite is configured to direct telemetry and control mode. In the direct telemetry and control mode, the first satellite directly transmits the first laser telemetry data to the ground station, and the ground station directly transmits the first laser payload remote control command to the first satellite.

10. The overseas real-time monitoring and control method as described in claim 1, characterized in that, Both the first and second satellites are BeiDou-3 project satellites.

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