TY - JOUR
T1 - Compound robust flight time and heading angle constrained guidance law
AU - Ji, Yi
AU - Pei, Pei
AU - Lin, Defu
AU - Zhao, Jianting
AU - Wang, Wei
N1 - Publisher Copyright:
© 2020 The Authors. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0)
PY - 2020
Y1 - 2020
N2 - This work studies accurate interception problem for salvo-attack missions and proposes a robust guidance law in the presence of impact time and angle constraints. First, the dynamic model for planar homing endgame guidance is built. Different with conventional guidance dynamic model, this work takes the derivative with respect to range, rather than time. Next, the trajectory of desired line-of-sight is formed and a time-to-go prediction method is introduced. On this basis, according to sliding mode methodology, a sliding manifold consisting the knowledge of time-to-go and line-of-sight angle is built and an integrated Lyapunov control method based guidance law is deduced to force this sliding manifold converge to a small region around zero in finite time, so that the missile will intercept target with a desired flight time and a heading angle. Detailed theoretical analysis and numerical simulations verified above properties.
AB - This work studies accurate interception problem for salvo-attack missions and proposes a robust guidance law in the presence of impact time and angle constraints. First, the dynamic model for planar homing endgame guidance is built. Different with conventional guidance dynamic model, this work takes the derivative with respect to range, rather than time. Next, the trajectory of desired line-of-sight is formed and a time-to-go prediction method is introduced. On this basis, according to sliding mode methodology, a sliding manifold consisting the knowledge of time-to-go and line-of-sight angle is built and an integrated Lyapunov control method based guidance law is deduced to force this sliding manifold converge to a small region around zero in finite time, so that the missile will intercept target with a desired flight time and a heading angle. Detailed theoretical analysis and numerical simulations verified above properties.
KW - Flight time constraint
KW - Heading angle constraint
KW - Homing guidance
KW - Salvo attack
KW - Sliding mode control
UR - http://www.scopus.com/inward/record.url?scp=85107815933&partnerID=8YFLogxK
U2 - 10.1016/j.ifacol.2020.12.2417
DO - 10.1016/j.ifacol.2020.12.2417
M3 - Conference article
AN - SCOPUS:85107815933
SN - 2405-8963
VL - 53
SP - 9452
EP - 9457
JO - IFAC-PapersOnLine
JF - IFAC-PapersOnLine
T2 - 21st IFAC World Congress 2020
Y2 - 12 July 2020 through 17 July 2020
ER -