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Navigation satellite integrated electronic system

A technology for integrated electronic systems and navigation satellites, applied in digital data processing, generation of response errors, instruments, etc., can solve problems such as low functional density, poor reconfiguration, inconsistent interfaces, etc., to improve the degree of reuse, function The effect of high density and high reliability

Pending Publication Date: 2022-01-14
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The characteristics of distributed electronic systems will lead to large volume and mass of satellites, high power consumption, and complex interface relationships. The resulting impacts are inconsistent interfaces, complex system control, poor reconfiguration, and low functional density.

Method used

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  • Navigation satellite integrated electronic system
  • Navigation satellite integrated electronic system
  • Navigation satellite integrated electronic system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0092] Such as figure 1 As shown in , the thermistor, SADA, and main distributor are respectively connected to the on-board computer. The power controller and the navigation task processor are connected to the onboard computer through the 1553B bus. The telemetry terminal is connected with the on-board computer through the 1553B bus and synchronous serial port. The attitude control device is connected to the on-board computer through the RS422 serial port. The remote control terminal and fixed amplifier are respectively connected with the telemetry terminal. The spread spectrum transponder and the telemetry terminal are connected through a synchronous serial port. The battery pack, solar panels, thermistors, auxiliary distributors, load equipment, and autonomous operation units are respectively connected to the data processing terminal. The autonomous operation unit is connected to the on-board computer and the high-performance unit respectively through the 1553B bus. The...

Embodiment 2

[0096] The on-board computer is the central equipment of the satellite, so the failure of the on-board computer will directly lead to the failure of the satellite mission. In order to improve the long-term on-orbit reliability of the on-board computer, the on-board computer adopts a dual-computer cold backup mode, and the design does not allow both computers to shut down at the same time. The on-board computer has manual switching and autonomous switching functions.

[0097] Due to the concentrated and complex functions of the onboard computer, in order to ensure business continuity, an autonomous repair function must be designed. Autonomous switching is the process of autonomous reconfiguration of the on-board computer, and the basis of this switching mechanism is the hardware watchdog. Autonomous switching adopts the method of combining software and hardware to independently judge that a certain stand-alone machine needs to be turned on.

[0098] Such as figure 2As shown...

Embodiment 3

[0102] The star software, that is, the on-board computer software, is divided into two configuration items: normal mode and minimal mode, and each configuration item can be run independently. Such as image 3 As shown, there are 4 input actions that affect the transition between normal mode and minimum mode: (1) direct instruction "computer force to maintain minimum mode"; (2) direct instruction "computer cancels hold minimum mode"; (3) indirect instruction "computer The software restarts and enters the minimum mode”; (4) the indirect instruction “the computer software restarts and enters the normal mode”.

[0103] The initial state of the on-board computer hardware is "direct command hardware request normal", the ground station sends a direct command "computer forced to keep the minimum mode", the on-board computer modifies the telemetry parameter "computer normal / minimum request-straight" to "restart to minimum", The hardware state transitions to "direct instruction hardwar...

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PUM

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Abstract

The present invention relates to a navigation satellite integrated electronic system, comprising: a spaceborne computer configured to execute all algorithms and autonomous management functions; and a data processing terminal configured to receive an instruction sent by the spaceborne computer and return collected load equipment data to the spaceborne computer; wherein the spaceborne computer communicates with the data processing terminal through a 1553B bus; the spaceborne computer and the data processing terminal mutually form far-end storage through the 1553B bus, and data is recovered from a far end after a single machine is recovered after power failure; the 1553B bus is uniformly connected with the satellite-borne computer unit and a plurality of satellite subsystems and reserves electrical interfaces for equipment of the satellite subsystems; the invention also comprises integrated electronic system software comprising a satellite-borne computer software normal mode, a satellite-borne computer software minimum mode, data processing terminal software and FPGA (Field Programmable Gate Array) software.

Description

technical field [0001] The present invention generally relates to the technical field of aerospace electronics, and more specifically relates to a navigation satellite integrated electronic system. Background technique [0002] The navigation satellite integrated electronic system is the core system of the satellite platform and the satellite control center. It is responsible for analyzing the remote control data to realize the control and management of the equipment; sending the telemetry information on the satellite; Calculate and control the attitude of the satellite; realize the orbit control of the satellite according to the orbit data of the satellite; collect the temperature data of the satellite to realize the active temperature control and ensure that each equipment works in the best performance state; monitor the status of the energy system in real time to ensure the energy of the satellite Safety; according to the current orbit and attitude of the satellite, contr...

Claims

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Application Information

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IPC IPC(8): G06F11/07G06F11/14
CPCG06F11/0757G06F11/1448G06F11/1456
Inventor 石龙龙贺芸祁见忠王正凯涂珍贞王学良林宝军沈苑张军
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS