On-orbit emergency mission instruction response time test method, system and medium

Abstract

The application provides a kind of on-orbit emergency task instruction response time test method, system and medium, comprising: compiling test data packet, including emergency task instruction response test target packet, emergency task packet and corresponding task interruption instruction;Before emergency response test arc section, emergency task instruction response test target packet is arranged on the ground, and emergency response test is used by interrupted task;After entering the measurement and control arc section, the execution of emergency task instruction response test target packet is monitored;After the execution of emergency task instruction response test target packet, task interruption instruction is injected on the ground, and the time T0 when satellite receives task interruption instruction in real-time telemetry is recorded;After confirming that the load device is powered off, emergency task packet is injected on the ground;The time T1 when satellite load is powered on is recorded;T1-T0 is used as on-orbit emergency task instruction response time.The application can ensure that under on-orbit emergency imaging environment, microwave remote sensing satellite on-orbit emergency task instruction response time is effectively and accurately tested.

Description

Technical Field

[0001] This invention relates to the field of on-orbit testing technology for microwave remote sensing satellites, specifically to a method for testing the response time of on-orbit emergency mission commands for microwave remote sensing satellites, and more particularly to a method, system, and medium for testing the response time of on-orbit emergency mission commands. Background Technology

[0002] With the rapid development of microwave remote sensing satellite technology, all parties are gradually emphasizing satellite controllability design, based on continuous improvement of core capabilities such as imaging indicators, and constantly promoting the "ease of use, usability," and "versatility" of satellites. The on-orbit emergency mission command response capability is a crucial aspect of satellite control performance. It is a key factor determining the timeliness of a satellite in completing critical and emergency missions, as well as its applicability to large-scale space-ground systems. The on-orbit emergency mission command response time directly characterizes the emergency mission command response capability and has been included as an important on-orbit evaluation indicator for microwave remote sensing satellites.

[0003] The entire process of on-orbit emergency mission response for microwave remote sensing satellites mainly includes: mission scheduling, mission upload, on-board mission planning, on-board mission preparation, on-board mission execution, reconnaissance data transmission, ground imaging data processing, and ground image data transmission to user terminals. These steps are executed sequentially, but their timing may overlap. The time required for mission scheduling and mission upload is uncertain due to the influence of actual ground operations; the reconnaissance data transmission is constrained by the satellite's orbit and the relative position of the emergency response mission's reconnaissance area; and the ground imaging data processing and ground image data transmission to user terminals are ground equipment testing indicators. Therefore, the satellite's emergency mission command response capability is mainly reflected in the speed of the three steps: on-board mission planning, on-board mission preparation, and on-board mission execution. This speed is constrained by the content, duration, and serial / parallel relationships of these three steps; this time constitutes the on-orbit emergency mission command response time for microwave remote sensing satellites.

[0004] On-orbit emergency missions primarily refer to missions arising from emergency imaging needs, requiring the interruption of ongoing on-orbit tasks. Currently, the testing methods used for the response time of on-orbit emergency mission commands on microwave remote sensing satellites fail to simulate real-world imaging emergency situations. Generally, to avoid affecting normal imaging tasks, other tasks unrelated to imaging are used as "interrupted missions." The shutdown time for these "interrupted missions" does not reflect the actual duration of the imaging mission's completion, reducing the validity of the on-orbit test data and, to some extent, affecting the satellite user's evaluation of the satellite's operability.

[0005] Patent CN112308374A discloses a method for executing satellite autonomous mission planning instruction sequences based on multi-level queues. First, it uses an instruction buffer to cache the sequence of instructions to be executed within a certain time range, and updates the instruction buffer in real time according to emergency mission instructions, dynamically adjusting the tasks to be planned. Second, it designs an instruction planning area and an instruction execution area, and plans and executes the instruction tasks according to the timing requirements and execution strategy of the instruction sequence. This patent does not pertain to testing methods for emergency mission instruction response time and is not related to or similar to this invention.

[0006] Patent CN113313356A discloses a method and apparatus for synthesizing emergency missions for remote sensing satellite Earth observation. This method inserts emergency missions into mission planning to avoid mission conflicts and increase the number of observations. Patent CN113269386A discloses a method and system for planning emergency missions for imaging satellites based on a synthesis strategy. This method synthesizes conflicts between emergency missions and planning schemes, reducing satellite maneuvers and activation frequency, and is a planning method for emergency missions. Neither of the above patents pertains to testing methods for emergency mission command responses and is not related to or close to this invention. Summary of the Invention

[0007] To address the shortcomings of existing technologies, this invention provides a method, system, and medium for testing the response time of on-orbit emergency mission commands.

[0008] According to the present invention, an on-orbit emergency mission command response time testing method, system, and medium are provided, the solution of which is as follows:

[0009] Firstly, a method for testing the response time of on-orbit emergency mission commands is provided, the method comprising:

[0010] Step S1: Compile test data packages, including emergency task instruction response test target packages, emergency task packages, and corresponding task interruption instructions;

[0011] Step S2: Before the emergency response test arc, arrange the emergency mission instruction response test target package on the ground for use by the interrupted mission during the emergency response test;

[0012] Step S3: After entering the measurement and control arc, the execution status of the emergency mission command response test target package is monitored in real time by satellite telemetry;

[0013] Step S4: After the emergency mission instruction response test target package is executed, the mission interruption instruction is recorded on the ground, and the time T0 when the satellite receives the mission interruption instruction in real-time telemetry is recorded as the start time of the emergency mission instruction response.

[0014] Step S5: After confirming the payload equipment is powered off via real-time satellite telemetry, inject the emergency mission package on the ground;

[0015] Step S6: Record the satellite payload power-on time T1 as the end time of the emergency mission command response;

[0016] Step S7: Use T1 to T0 as the response time for on-orbit emergency mission commands.

[0017] Preferably, the emergency mission instruction response test target package is set to power on the payload 1 minute after entering the measurement and control arc, with a power-on time of not less than 2 minutes and not more than 4 minutes.

[0018] Preferably, the emergency mission command response test target package uses a load operating mode with the shortest power-on preparation time and power-off time.

[0019] Preferably, the time T0 when the satellite receives the mission interruption command and the time T1 when the satellite payload is powered on are both on-board times, excluding the time when the mission interruption command is received on the ground, thus eliminating the influence of ground operations on the calculation results.

[0020] Secondly, an on-orbit emergency mission command response time testing system is provided, the system comprising:

[0021] Module M1: Compiles test data packages, including emergency task instruction response test target packages, emergency task packages, and corresponding task interruption instructions;

[0022] Module M2: Before the emergency response test arc, arrange the emergency mission command response test target package on the ground for use by the interrupted mission during the emergency response test;

[0023] Module M3: After entering the telemetry and control arc, it monitors the execution status of the emergency mission command response test target package in real time via satellite telemetry;

[0024] Module M4: After the emergency mission instruction response test target package is executed, the mission interruption instruction is noted on the ground, and the time T0 when the satellite receives the mission interruption instruction in real-time telemetry is recorded as the start time of the emergency mission instruction response;

[0025] Module M5: After confirming the payload equipment is powered off via real-time satellite telemetry, an emergency mission package is injected on the ground.

[0026] Module M6: Records the satellite payload power-on time T1, which serves as the end time of the emergency mission command response;

[0027] Module M7: T1 to T0 are used as the response time for on-orbit emergency mission commands.

[0028] Preferably, the emergency mission instruction response test target package is set to power on the payload 1 minute after entering the measurement and control arc, with a power-on time of not less than 2 minutes and not more than 4 minutes.

[0029] Preferably, the emergency mission command response test target package uses a load operating mode with the shortest power-on preparation time and power-off time.

[0030] Preferably, the time T0 when the satellite receives the mission interruption command and the time T1 when the satellite payload is powered on are both on-board times, excluding the time when the mission interruption command is received on the ground, thus eliminating the influence of ground operations on the calculation results.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] 1. This invention designs an "emergency mission command response test target package," in which the satellite's required work content, duration, and serial (parallel) relationships are consistent with actual on-orbit operations. Without affecting normal on-orbit imaging missions, it realistically assesses interruptions to imaging missions, recreating the on-orbit operational environment where emergency missions and preceding missions may conflict, thus ensuring the effectiveness of the test.

[0033] 2. By using the moment the "mission interruption command" is received onboard as T0, the time recorded on the ground for the "mission interruption command" is eliminated, thus avoiding fluctuations in test data caused by uncertainties in ground operations, and also improving the clarity of the test interface. Using the onboard time as the benchmark for the "mission interruption command" moment T0 and the satellite payload startup moment T1 avoids errors that exist between satellite-transmitted telemetry decisions and ground timing, improving the accuracy of test data. Attached Figure Description

[0034] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0035] Figure 1 This is a schematic diagram of the process of the present invention. Detailed Implementation

[0036] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0037] This invention provides a method for testing the response time of on-orbit emergency mission commands, referring to... Figure 1 As shown, the method specifically includes:

[0038] Step S1: Compile test data packages, including "Emergency Task Instruction Response Test Target Package", "Emergency Task Package", and corresponding "Task Interruption Instructions".

[0039] Step S2: One day before the emergency response test arc, arrange for the ground to be marked with "Emergency Mission Command Response Test Target Pack" for use by missions interrupted during the emergency response test.

[0040] Step S3: One minute after entering the telemetry and control arc, monitor the execution status of the "Emergency Mission Command Response Test Target Package" via real-time satellite telemetry.

[0041] Step S4: One minute after the "Emergency Mission Command Response Test Target Package" is executed, the "Mission Interruption Command" is noted on the ground. The time T0 when the satellite receives the "Mission Interruption Command" in real-time telemetry is recorded as the start time of the emergency mission command response.

[0042] Step S5: After confirming the payload equipment is powered off via real-time satellite telemetry, mark the "Emergency Mission Package" on the ground.

[0043] Step S6: Record the satellite payload power-on time T1 as the end time of the emergency mission command response.

[0044] Step S7: Use T1 to T0 as the response time for on-orbit emergency mission commands.

[0045] Specifically, the target package is designed to be replaced by emergency missions to avoid conflicts between test activities and normal on-orbit missions of the satellite; the "emergency mission command response test target package" is set to power on the payload 1 minute after entering the telemetry and control arc, with a power-on time of not less than 2 minutes and not more than 4 minutes, so as to facilitate confirmation of the power-on status through telemetry and save on-board energy.

[0046] The "Emergency Mission Command Response Test Target Pack" uses a payload operating mode with the shortest power-on preparation time and power-off time, saving measurement and control arc resources.

[0047] The time T0 when the satellite receives the "mission interruption instruction" and the time T1 when the satellite payload is powered on are both on-board times. The time when the "mission interruption instruction" is noted on the ground is excluded to minimize the impact of ground operations on the calculation results.

[0048] The present invention will now be described in more detail.

[0049] Step S3, which involves real-time satellite telemetry monitoring of the execution of the "Emergency Mission Command Response Test Target Package," should include the following satellite telemetry information:

[0050] Data transmission master / slave power-on status: TMA005 = 3.5~5V, TMA008 = 3.5~5V

[0051] Data transmission record status: TMA205=1, TMA405=1

[0052] Load command execution status: TML198 = 9AH

[0053] Single-unit voltage telemetry for load: TML116 = 4.275~5.705V, TML126 = 2.78~3.82V

[0054] TML144=4.275~5.705V, TML217=4.275~5.705V

[0055] TML167=4.275~5.705V, TML183=4.275~5.705V

[0056] TML188=4.175~5.845V, TML190=4.39~5.62V

[0057] TML211=3.56~5.70V, TML130=4.275~5.705V

[0058] TML132=4.275~5.705V, TML133=4.275~5.705V

[0059] TML135=4.275~5.705V, TML136=4.275~5.705V

[0060] TML138=4.275~5.705V, TML139=4.275~5.705V

[0061] TML141=4.275~5.705V, TML169=4.14~5.86V

[0062] TML171=4.14~5.86V, TML173=4.14~5.86V

[0063] In step S5, confirming the power-off of the payload equipment via real-time satellite telemetry should include the following satellite telemetry information:

[0064] Load command execution status: TML198 = DAH

[0065] Telemetry voltage measurement of single load unit: TML116 = 0.7~1.4V, TML126 = 0.7~1.2V

[0066] TML144=0.7~1.4V, TML217=0.7~1.4V

[0067] TML167=0.7~1.4V, TML183=0.7~1.4V

[0068] TML188=0~0.8V, TML190=0.7~1.4V

[0069] TML211=0.7~1.4V, TML130=0.7~1.4V

[0070] TML132=0.7~1.4V, TML133=0.7~1.4V

[0071] TML135=0.7~1.4V, TML136=0.7~1.4V

[0072] TML138=0.7~1.4V, TML139=0.7~1.4V

[0073] TML141=0.7~1.4V, TML169=0.7~1.4V

[0074] TML171=0.7~1.4V, TML173=0.7~1.4V

[0075] After the data transmission system is powered off: TMA005 = 0~0.5V, TMA008 = 0~0.5V

[0076] In step S5, the ground-based "emergency mission package" should include the following satellite telemetry information:

[0077] Remote control frame coincidence count: TMS123 count +1

[0078] Step S6, which records the satellite payload power-on time, should include the following telemetry information:

[0079] Data transmission master / slave power-on status: TMA005 = 3.5~5V, TMA008 = 3.5~5V

[0080] Data transmission record status: TMA205=1, TMA405=1

[0081] Load command execution status: TML198 = 9AH

[0082] Single-unit voltage telemetry for load: TML116 = 4.275~5.705V, TML126 = 2.78~3.82V

[0083] TML144=4.275~5.705V, TML217=4.275~5.705V

[0084] TML167=4.275~5.705V, TML183=4.275~5.705V

[0085] TML188=4.175~5.845V, TML190=4.39~5.62V

[0086] TML211=3.56~5.70V, TML130=4.275~5.705V

[0087] TML132=4.275~5.705V, TML133=4.275~5.705V

[0088] TML135=4.275~5.705V, TML136=4.275~5.705V

[0089] TML138=4.275~5.705V, TML139=4.275~5.705V

[0090] TML141=4.275~5.705V, TML169=4.14~5.86V

[0091] TML171=4.14~5.86V, TML173=4.14~5.86V

[0092] This invention provides a method, system, and medium for testing the response time of on-orbit emergency mission instructions. By designing an "emergency mission instruction response test target package" that is consistent with the characteristics of actual on-orbit mission planning, on-board mission preparation, and on-board mission execution, and optimizing its time information, it not only simulates real emergency scenarios in the on-orbit environment, but also improves the convenience and effectiveness of the test recording process; using on-board time as the time reference, a relatively more accurate response time is obtained.

[0093] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0094] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for testing the response time of on-orbit emergency mission commands, characterized in that, include: Step S1: Compile test data packages, including emergency task instruction response test target packages, emergency task packages, and corresponding task interruption instructions; Step S2: Before the emergency response test arc, arrange the emergency mission instruction response test target package on the ground for use by the interrupted mission during the emergency response test; Step S3: After entering the measurement and control arc, the execution status of the emergency mission command response test target package is monitored in real time by satellite telemetry; Step S4: After the emergency mission instruction response test target package is executed, the mission interruption instruction is recorded on the ground, and the time T0 when the satellite receives the mission interruption instruction in real-time telemetry is recorded as the start time of the emergency mission instruction response. Step S5: After confirming the payload equipment is powered off via real-time satellite telemetry, inject the emergency mission package on the ground; Step S6: Record the satellite payload power-on time T1 as the end time of the emergency mission command response; Step S7: Use T1-T0 as the response time for on-orbit emergency mission commands; The time T0 when the satellite receives the mission interruption command and the time T1 when the satellite payload is powered on are both on-board times. The time when the mission interruption command is recorded on the ground is excluded to eliminate the influence of ground operations on the calculation results.

2. The on-orbit emergency mission command response time testing method according to claim 1, characterized in that, The emergency mission command response test target package is set to power on the payload 1 minute after entering the measurement and control arc, with a power-on time of not less than 2 minutes and not more than 4 minutes.

3. The on-orbit emergency mission command response time testing method according to claim 2, characterized in that, The emergency mission command response test target package uses a load operating mode with the shortest power-on preparation time and power-off time.

4. An on-orbit emergency mission command response time testing system, characterized in that, include: Module M1: Compiles test data packages, including emergency task instruction response test target packages, emergency task packages, and corresponding task interruption instructions; Module M2: Before the emergency response test arc, arrange the emergency mission command response test target package on the ground for use by the interrupted mission during the emergency response test; Module M3: After entering the telemetry and control arc, it monitors the execution status of the emergency mission command response test target package in real time via satellite telemetry; Module M4: After the emergency mission instruction response test target package is executed, the mission interruption instruction is noted on the ground, and the time T0 when the satellite receives the mission interruption instruction in real-time telemetry is recorded as the start time of the emergency mission instruction response; Module M5: After confirming the payload equipment is powered off via real-time satellite telemetry, an emergency mission package is injected on the ground. Module M6: Records the satellite payload power-on time T1, which serves as the end time of the emergency mission command response; Module M7: T1-T0 is used as the response time for on-orbit emergency mission commands; The time T0 when the satellite receives the mission interruption command and the time T1 when the satellite payload is powered on are both on-board times. The time when the mission interruption command is recorded on the ground is excluded to eliminate the influence of ground operations on the calculation results.

5. The on-orbit emergency mission command response time testing system according to claim 4, characterized in that, The emergency mission command response test target package is set to power on the payload 1 minute after entering the measurement and control arc, with a power-on time of not less than 2 minutes and not more than 4 minutes.

6. The on-orbit emergency mission command response time testing system according to claim 5, characterized in that, The emergency mission command response test target package uses a load operating mode with the shortest power-on preparation time and power-off time.

7. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 3.

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