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Method for enhancing in-orbit reliability of moonlet

A reliability and satellite technology, which is applied to the generation of response errors, error detection of redundant data in calculations, and instruments. It can solve problems such as out-of-control of single machine components, poor reliability, and abnormal communication of small satellites, so as to avoid expansion. , improve the effect of reliability and stability

Active Publication Date: 2018-03-30
CHANGGUANG SATELLITE TECH CO LTD
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  • Summary
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Problems solved by technology

[0017] In order to solve the problems that the existing small satellites are prone to run out of control of single machine parts or out of control of the whole satellite when performing tasks in orbit, which leads to poor reliability and low work efficiency, the present invention provides a method for solving abnormal communication of small satellites by using interruption. The method can quickly solve the problem of small satellite in-orbit communication anomalies in real time

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  • Method for enhancing in-orbit reliability of moonlet
  • Method for enhancing in-orbit reliability of moonlet
  • Method for enhancing in-orbit reliability of moonlet

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specific Embodiment approach 1

[0041] Specific implementation mode 1. Combination Figure 1 to Figure 6 This embodiment is described as a method for enhancing the reliability of small satellites in orbit. In the whole design of small satellites, the communication interface types between the central computer and stand-alone components are usually RS422 serial interfaces and CAN bus interfaces, often with PPS second pulse signals. Time synchronization, and in order to ensure the timely processing of information, the interruption method is used.

[0042] Step 1. After the central computer initiates communication to the stand-alone component as the communication host, the stand-alone component responds to the communication request of the central computer, and the central computer receives data in an interrupt receiving mode;

[0043] Step 2, the central computer executes the interrupt service function,

[0044] Step 21, closing the interrupt and updating the cumulative number of responses;

[0045] Step 22. D...

specific Embodiment approach 2

[0059] Specific embodiment two, combine Figure 2 to Figure 6 Describe this implementation mode, this implementation mode is an embodiment of a method for enhancing the reliability of small satellites in orbit described in the first specific implementation mode: this implementation mode is based on the abnormality of the Jilin No. 1 Video 01 satellite on-orbit fiber optic gyro as an example illustrate:

[0060] 1. RS422 is used between the central computer and the fiber optic gyroscope. In the communication, the host of the central computer initiates communication, and the fiber optic gyroscope responds to the communication request of the host computer as a slave, and adopts the interrupt receiving method. The running cycle of the central computer application program is 200ms, the watchdog feeding cycle is 200ms, the timing cycle is 500ms, the theoretical time for the fiber optic gyroscope to return parameters is 10ms, and the number of theoretical interruptions is 100 times. ...

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Abstract

The invention discloses a method for enhancing the in-orbit reliability of a moonlet, relates to the field of the in-orbit reliability guaranteeing of a spacecraft, and solves the problems of poor reliability, low working efficiency and the like since the moonlet is likely to be subjected to a situation that one-machine component is out of control or a whole spacecraft is out of control when the moonlet carries out in-orbit task execution. Interruption is used for solving the problem of the abnormal communication of the moonlet, software on satellite is used for automatically solving the problem that an RS422 bus, a CAN bus and a PPS (Pulse Per Second) signal are continuously abnormal. When certain one machine is subjected to abnormal communication, after interruption frequencies achieve apreset threshold value, the communication interface of the one machine is shielded through a continuous interruption way, and the one-machine component is restarted. Since an abnormity processing method is carried out in application software, an effect of quick response and abnormal processing can be achieved. The problem that the abnormity is only solved through the injection of a remote controlinstruction on the ground after the satellite rises to the sky, and the reliability and the stability of the in-orbit operation of the moonlet are effectively improved.

Description

technical field [0001] The invention relates to the field of on-orbit reliability assurance of spacecraft, in particular to a method for enhancing the on-orbit reliability of small satellites. Background technique [0002] In the actual application process of engineering, most small satellites in China use the method of collecting telemetry data to the ground, and then according to the preset fault solution, send remote control instructions through uplink to track and process the location of the abnormality. Therefore, it is impossible to timely judge and maintain the complex situation of the satellite in orbit. Among the existing domestic technologies, the satellite health assessment and anomaly detection technologies are not yet mature. [0003] Modern small satellites are light in weight, small in size, high in performance and low in cost. Modern small satellites have a wide range of applications. Not only does it play an important role in the fields of communication, ...

Claims

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Application Information

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IPC IPC(8): G06F11/14
CPCG06F11/1441G06F11/1443
Inventor 陈茂胜李小明邹吉炜程龙张鑫
Owner CHANGGUANG SATELLITE TECH CO LTD
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