System for controlling satellite attitude and track based on network on satellites

A technology for orbit control and satellite attitude, applied in attitude control, three-dimensional position/course control, etc., can solve problems that are not fully suitable for satellite applications, achieve convenient hardware and software resource sharing, reduce construction complexity, and shorten delay the effect of time

Active Publication Date: 2007-12-26
AEROSPACE DONGFANGHONG SATELLITE
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AI Technical Summary

Problems solved by technology

FCS is directly used on satellites, and the main problems are: (1) How to transform the existing satellite attitude and orbit control system into FCS; (2) How to construct the sensors and actuators of the spaceborne FCS, (3) How to construct the control loop of spaceborne FCS, and how to realize the FCS control mechanism on the satellite; (4) How to integrate the existing satellite attitude and orbit control systems (5) How to formulate protocols for satellite Internet access, especially the application layer protocols, which are suitable for satellite applications with high reliability and limited resources. Some industry's own application layer protocols are not fully suitable for satellite applications; (6) How to design FCS based on the requirements of satellite reliability and safety, as well as the characteristics of satellites that cannot be repaired

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  • System for controlling satellite attitude and track based on network on satellites
  • System for controlling satellite attitude and track based on network on satellites
  • System for controlling satellite attitude and track based on network on satellites

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Embodiment Construction

[0031] As shown in Figures 2 and 3, the present invention includes a star dispatching unit, a CAN bus star network, an intelligent sensor component with a microprocessor and an execution component with a microprocessor, wherein the intelligent sensor with a microprocessor The sensor components include fiber optic gyroscope IEM, sun sensor IEM, infrared horizon IEM, geomagnetic field attitude measurement IEM, star camera IEM, the above-mentioned intelligent sensor components can be increased or decreased according to needs; intelligent execution components with microprocessors include momentum Wheel IEM, three-axis magnetic torque device IEM, thruster IEM, etc., the above-mentioned intelligent actuators can be increased or decreased as required. IEM is an acronym for Integrated Electronics Module.

[0032] As shown in Figures 2 and 3, the control process of the present invention: the star service dispatching unit sends and obtains information order to a designated intelligent s...

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Abstract

A satellite attitude and orbit control system based on satellite network is prepared for sending transfer order for obtaining information to certain assigned intelligent sensor with microprocessor through satellite network for making satellite affairs dispatch unit obtain relevant information, sending control command to certain assigned intelligent execution element by dispatch unit through satellite network after calculation, executing said control command by intelligent execution element with microprocessor in order to make satellite be moved for realizing control purpose after control command is received by said execution element.

Description

technical field [0001] The invention relates to a satellite attitude and orbit control system based on satellite Internet, in particular to a CAN bus-based satellite attitude and orbit control system. Background technique [0002] At present, the implementation methods of satellite attitude and orbit control adopt the centralized control method based on the computer management of the attitude control center. Figure 1 shows the composition of a typical small satellite attitude and orbit control system. As shown in Figure 1, the system is centered on the control computer, which is connected to the peripheral interface circuit box, various sensors, and actuators with various cables to form a complex and independent "box-cable" structure. This structure is not only complicated to manufacture, but also has a large weight and power consumption. It also brings difficulties such as inflexibility in dealing with emergencies in orbit and reducing the survivability of satellites. It is...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05D1/10
Inventor 李孝同施思寒
Owner AEROSPACE DONGFANGHONG SATELLITE
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