TY - GEN
T1 - Online rendezvous guidance for helicopter using state dependent riccati equation
AU - Halbe, Omkar
AU - Hajek, Manfred
N1 - Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - Autonomous rendezvous with mobile ground targets is essential in maritime unmanned helicopter missions, such as shipboard recovery, aerial reconnaissance, and target interception. This paper presents an online guidance scheme for rendezvous guidance using the state–dependent Riccati equation (SDRE) technique. First, a typical helicopter-target engagement scenario and the necessary conditions for successful rendezvous are described. After a brief overview of the SDRE technique, three nonlinear quadratic regulator problems for the lateral, vertical, and forward motion each are formulated and solved analytically. The resulting rendezvous guidance laws are then coupled to a robust flight controller in a full-scale helicopter simulation model. The target motion is simulated with a constant ground speed but different lateral maneuvering profiles. Simulations results show that the SDRE guidance laws successfully steer the helicopter for intercepting the target with the required terminal velocity vector.
AB - Autonomous rendezvous with mobile ground targets is essential in maritime unmanned helicopter missions, such as shipboard recovery, aerial reconnaissance, and target interception. This paper presents an online guidance scheme for rendezvous guidance using the state–dependent Riccati equation (SDRE) technique. First, a typical helicopter-target engagement scenario and the necessary conditions for successful rendezvous are described. After a brief overview of the SDRE technique, three nonlinear quadratic regulator problems for the lateral, vertical, and forward motion each are formulated and solved analytically. The resulting rendezvous guidance laws are then coupled to a robust flight controller in a full-scale helicopter simulation model. The target motion is simulated with a constant ground speed but different lateral maneuvering profiles. Simulations results show that the SDRE guidance laws successfully steer the helicopter for intercepting the target with the required terminal velocity vector.
UR - http://www.scopus.com/inward/record.url?scp=85092364255&partnerID=8YFLogxK
U2 - 10.2514/6.2020-1827
DO - 10.2514/6.2020-1827
M3 - Conference contribution
AN - SCOPUS:85092364255
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
SP - 1
EP - 15
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -