This invention relates to the field of
satellite simulation and testing technology, specifically to a multi-
satellite parallel testing
system for attitude and
orbit control systems. The
system includes a
signal transfer unit subsystem, an I / O interface subsystem, a multi-core real-time simulator subsystem, a real-time
simulation main control subsystem, a
database server subsystem, and a power supply module subsystem. The multi-core real-time simulator connects to multiple I / O interface
chassis via PCIe expansion components, with each
chassis corresponding to the test resources of one
satellite. The real-time
simulation main control subsystem deploys the
dynamic simulation models of multiple satellites onto different processor cores of the simulator, achieving multi-core distributed
parallel simulation. Each satellite's
onboard computer establishes a real-
time data interaction link with its corresponding
dynamic simulation model, forming a multi-satellite parallel real-time closed-loop testing state. This
system solves the problem that traditional single-
satellite testing systems cannot meet the requirements of
mass production and parallel testing, offering advantages such as high testing efficiency, low hardware cost, and strong
scalability.