Longitudinal Control Law Design and Simulation of Fixed-Wing UAV

Abstract:

Taken some fixed-wing UAV as the study object, the aircraft movement was broken down into the longitudinal movement and lateral movement according to the linearized small perturbation principle, the longitudinal control law design method was discussed using root locus which belonged to classical control theory. The six degrees of freedom nonlinear model simulation result shows that: the control parameters designed are reasonable, the simulation profile is fully consistent with the setting profile, the control effect of pitch angle loop and altitude loop meets with the indices requirements, the method is mature and reliable, easy to realize in engineering.

• Periodical: Applied Mechanics and Materials (Volumes 241-244)
• Pages: 1128-1132
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.241-244.1128
• Online since: December 2012
• Authors: Zhen Duan
• Keywords: Flight Control, Nonlinear Simulation, Root Locus, UAV

References

[1] FENG M R: World Encyclopedia of UAV[M] .Beijing: Aviation Industry Press,2004. (In Chinese)

[2] WU S T, FEI Y H: Flight control system[M] .Beijing: Beijing University of Aeronautics and Astronautics Press,2005 . (In Chinese)

[3] JIN C J: Flight Control[M] .Beijing: National Defence Industry Press,1999. (In Chinese)

[4] Shi Z K, et al.. Robust Control Theory[M]. Beijing: National Defence industry Press ,2003.(In Chinese)

[5] Ho W K, Hong Y, Hansson A, Hjalmarsson H, et al.. Relay auto-tuning of PID controllers using iterative feedback tuning. Automatic, 2003, 39(1):149-157.

DOI: 10.1016/s0005-1098(02)00201-7

[6] B. Etkin. The turbulent wind and its effect on flight [ C ] . AlAA Aircraft Systems Meeting August 4 - 6, 1980. Anaheim, California. AIAA- 80- 1836.