TY - JOUR
T1 - Research on guidance and control of hardware-in-loop simulation system based on UAV
AU - Xu, Ping
AU - Wang, Wei
AU - Lin, De Fu
AU - Wang, Jiang
AU - Cui, Xiao Xi
PY - 2012/8
Y1 - 2012/8
N2 - Based on unmaned aerial vehicle (UAV) integrated guidance and control technology and real-time simulation technology, a new hardware-in-loop (HIL) simulation system, which includes inertial navigation system, GPS, three-axis turntable, simulation computer, and display monitor system is established in this paper. In this HIL system, the simulation computer collects the output signal of integrated guidance and control computer, calculates the UAV kinematics and dynamics data, and sends the attitude information to the three-axis turntable. The three-axis turntable and inertial navigation system complete the simulation of UAV course and attitude. The guidance and control computer utilizes navigation information to form control command and sends the control command to simulation computer. The results of this experiment show that the design of this inertial navigation calculation method is reasonable. With simulation step of 1ms, the control signal error is limited within 1%. This system can be miniaturized, modularized, and utilized for UAV guidance and control system further improved.
AB - Based on unmaned aerial vehicle (UAV) integrated guidance and control technology and real-time simulation technology, a new hardware-in-loop (HIL) simulation system, which includes inertial navigation system, GPS, three-axis turntable, simulation computer, and display monitor system is established in this paper. In this HIL system, the simulation computer collects the output signal of integrated guidance and control computer, calculates the UAV kinematics and dynamics data, and sends the attitude information to the three-axis turntable. The three-axis turntable and inertial navigation system complete the simulation of UAV course and attitude. The guidance and control computer utilizes navigation information to form control command and sends the control command to simulation computer. The results of this experiment show that the design of this inertial navigation calculation method is reasonable. With simulation step of 1ms, the control signal error is limited within 1%. This system can be miniaturized, modularized, and utilized for UAV guidance and control system further improved.
KW - Flight control system
KW - GPS
KW - Hardware-in-loop
KW - Integrated navigation
KW - Unmanned aerial vehicle
UR - http://www.scopus.com/inward/record.url?scp=84867406085&partnerID=8YFLogxK
U2 - 10.3969/j.issn.1673-3193.2012.04.015
DO - 10.3969/j.issn.1673-3193.2012.04.015
M3 - Article
AN - SCOPUS:84867406085
SN - 1673-3193
VL - 33
SP - 420
EP - 424
JO - Zhongbei Daxue Xuebao (Ziran Kexue Ban)/Journal of North University of China (Natural Science Edition)
JF - Zhongbei Daxue Xuebao (Ziran Kexue Ban)/Journal of North University of China (Natural Science Edition)
IS - 4
ER -