直升機(jī)飛行控制實(shí)時(shí)仿真研究.pdf

1、南京航空航天大學(xué)碩士學(xué)位論文直升機(jī)飛行控制實(shí)時(shí)仿真研究姓名：沈俊申請(qǐng)學(xué)位級(jí)別：碩士專業(yè)：飛行器設(shè)計(jì)指導(dǎo)教師：徐錦法2011-03直升機(jī)飛行控制實(shí)時(shí)仿真研究 iiABSTRACT The design of unmanned helicopter flight control system is inseparable from digital simulation and physical semi-simulation, using

2、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

3、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 int

4、o 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 t

5、he 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

6、 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 mach

7、ine, 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

8、 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 dyn

9、amics 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 fir

10、st-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