Satellite entry-exit independent telemetry processing control method

A technology for processing control and entry and exit, applied in the direction of multi-programming devices, etc., can solve the problems of manual monitoring and insufficient time accuracy, and achieve the effects of reducing the workload of human intervention, precise control, high efficiency and precision

Inactive Publication Date: 2012-05-02
BEIJING INST OF SPACECRAFT SYST ENG
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AI Technical Summary

Problems solved by technology

This method requires manual monitoring, and the time precision is not enough
Especially when the number of satellites increases a

Method used

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  • Satellite entry-exit independent telemetry processing control method
  • Satellite entry-exit independent telemetry processing control method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0030] Taking a certain satellite as an example, the following introduces the satellite entry-exit autonomous telemetry processing control method:

[0031] The satellite realizes the control of the autonomous telemetry processing of the entry and exit of the satellite through the time scale command and the time scale command group. The autonomous control has enabled and disabled states, which can be modified by remote control commands. When enabled, self-management with time-stamped commands. Its time stamp command and time stamp command group have the following characteristics:

[0032] (1) The time stamping instructions in the time stamping instruction group are injected and deleted in units of groups, and the maximum length is 36 instructions;

[0033] (2) All the instructions stored in the time stamp command group need to be verified. When the verification result of a certain time stamp command is wrong, the telemetry alarm flag will be set to indicate that the time stam...

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PUM

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Abstract

A satellite entry-exit independent telemetry processing control method sets a time mark instruction group for each satellite mission. Each time mark instruction group is composed of time mark instructions with time marks, and the execution time of the time mark instructions is the time indicated by corresponding time marks. A program control cycle is set according to a satellite orbit cycle, timemark instruction groups required by one program control cycle are injected on the ground in one time, a satellite retrieves corresponding time mark instruction groups according to the current executing mission, then corresponding instructions in the time mark instruction groups are executed according to the current satellite time, and all the time mark instructions are executed sequentially according to the time marks. After one instruction is completed, the instruction is automatically arranged at the rears of the time mark instruction groups, and one program control cycle is added on an original execution time so as to serve as the next execution time. If overtime occurs in the time mark instruction execution process, the instruction is executed at once or given up. The method can achieve satellite entry-exit independent telemetry management.

Description

technical field [0001] The invention belongs to the technical field of spacecraft measurement, control and communication, and relates to a satellite autonomous telemetry control method. Background technique [0002] The telemetry data of the spacecraft generally includes the health data, working condition data, remote control response data and performance data of each subsystem and each equipment. Telemetry data is of great significance for understanding the health status and working status of the spacecraft. However, due to the limitation of the number and distribution of measurement and control points, the spacecraft has an unmonitorable arc section, which becomes a blind area for spacecraft monitoring. How to obtain the telemetry information of this working segment has become an important issue. [0003] The traditional method is that before the satellite enters the invisible arc (ie exit), the ground injection command gives the storage strategy for the telemetry in the...

Claims

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Application Information

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IPC IPC(8): G06F9/46
Inventor 李林唐自新陶利民杨聪伟翟君武李瑞军王向晖
Owner BEIJING INST OF SPACECRAFT SYST ENG
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