Overview of the spacecraft onboard command and control bus


Summary of Onboard Bus Requirements
 
 
Mars Express Avionics Test Bench highlighting the inter-unit electrical harnesses.
 
The main functions of the spacecraft onboard command and control bus are:
  • The acquisition of data from sensors and the commanding of actuators,
  • The transfer of packets of data between onboard instruments and control computers,
  • The distribution of time information.

 
Summary of Onboard Bus Requirements
 
The architecture of safety critical systems, such as flight control systems, in new spaceccrafts is moving from fully centralized processing towards distributed processing in which specialized microcontrollers are used to control intelligent actuators over a digital communication bus. We can then summarize the requirements that must be met by the spacecraft onboard bus as:
  • Ability to acquire synchronous data frames from sensors with controlled latency,
  • Ability to transmit synchronous to actuators with controlled latency,
  • Ability to transfer asynchronous and isochronous data packets between nodes,
  • Provide a symmetric medium access control service to nodes (i.e. each node can access the bus on demand),
  • Provide accurate distribution of time data and time reference pulse.
  • Provide a safe implementation for a cross-strapping mechanism

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Last update: 21 March 2012


More information

 •  General characteristics of a spacecraft data bus (http://www.esa.int/TEC/OBCDH/SEMA6G2T00H_0.html)
 •  Future Trends in Onboard Bus Use (http://www.esa.int/TEC/OBCDH/SEMCAG2T00H_0.html)
 •  ECSS standardization Background (http://www.esa.int/TEC/OBCDH/SEMYAG2T00H_0.html)