The invention discloses a high-integration-
level flight control system, relates to the field of wind tunnel dynamic flight tests, and solves the problems that an existing flight
control system is limited in interface
adaptation type, single in
control mode and insufficient in attitude and power cooperative control precision under closed-
loop control. Comprising a data receiving interface, a
control signal output interface and a control
processing module. The data receiving interface is adapted to various communication types such as 485, 232 and the like and is used for acquiring
sensing data of multiple components such as inertial navigation, a GPS (
Global Positioning System), a remote controller and the like; and the
control signal output interface outputs corresponding signals to the control surface
control unit, the
electronic speed control and electric
culvert unit and the like. The control
processing module comprises a
system self-checking module, a
data analysis module and an instruction resolving module,
sensing data are analyzed after self-checking is passed, the instruction resolving module can select an open loop mode or a
closed loop mode to resolve an instruction and transmit the instruction, and multi-
source data collection and multi-execution-unit cooperative control are achieved. The method can be used for flight control of virtual flight,
free flight and outfield flight of a dynamic
flight model.