Research On Real-Time Simulation Of Helicopter Flight Control

The design of unmanned helicopter flight control system is inseparable from digital simulation and physical semi-simulation, using the simulation test can be a great extent to avoid the risk of accidents in the verification process, shorten the development cycle and reduce costs. In this paper, using MATLAB / RTW technology, the author designed and constructed a RTW and VxWorks-based software environment unified helicopter flight control modeling and real-time simulation. In order to improve the accuracy of flight control simulation, the author maked a research into the non-linear helicopter flight dynamics modeling.During the research of software environment unified flight control modeling and real-time simulation, in accordance with the specific requests, the author designed the hardware architecture, software components and communication structure of simulation system. By intensively analyzing of MATLAB / RTW technology, the author established software cross-development environment aiming at VxWorks embedded target, and introduced details of the relevant documents and property in the development of software environment. According to the functional requirements of flight control system simulation target machine, the author completed the division of the application-level tasks, analyzed the gist, method and realizing format of task program under Simulink environment. The timing driving of model tasks and the input and output of IO devices were focused discussion. The author has analyzed the feasibility and reliability of the software environment in accordance with simulation executive procedure test.In the research of helicopter flight dynamics modeling, the author discussed a modeling method of helicopter nonlinear flight dynamics for low speed and steady state, focusing on the derivation of blade plate motion model which introduced Pitt and Peters's first-order harmonics rotor dynamic inflow theory. The author also developed trim and linear software and non-linear flght dynamics model based on s-function for UH-60A helicopter. Compared with data of the flight test, the author verify the validity of the flight dynamic model .