| dc.contributor.author | Ang Li | |
| dc.contributor.author | Yaohua Shen | |
| dc.contributor.author | Bin Du | |
| dc.contributor.other | Shenyang Aircraft Design and Research Institute, Yangzhou Collaborative Innovation Research Institute Co., Ltd., Yangzhou 225006, China | |
| dc.contributor.other | College of Automation, Jiangsu University of Science and Technology, Zhenjiang 212100, China | |
| dc.contributor.other | College of Automation Engineering, Nanjing University and Aeronautics and Astronautics, Nanjing211106, China | |
| dc.date.accessioned | 2025-08-27T13:59:21Z | |
| dc.date.accessioned | 2025-10-08T08:42:40Z | |
| dc.date.available | 2025-10-08T08:42:40Z | |
| dc.date.issued | 01-07-2025 | |
| dc.identifier.uri | http://digilib.fisipol.ugm.ac.id/repo/handle/15717717/36841 | |
| dc.description.abstract | In this paper, the problem of pitching attitude finite-horizon optimization for aircraft is posed with system uncertainties, external disturbances, and input constraints. First, a neural network (NN) and a nonlinear disturbance observer (NDO) are employed to estimate the value of system uncertainties and external disturbances. Taking input constraints into account, an auxiliary system is designed to compensate for the constrained input. Subsequently, the backstepping control containing NN and NDO is used to ensure the stability of systems and suppress the adverse effects caused by the system uncertainties and external disturbances. In order to avoid the derivation operation in the process of backstepping, a dynamic surface control (DSC) technique is utilized. Simultaneously, the estimations of the NN and NDO are applied to derive the backstepping control law. For the purpose of achieving finite-horizon optimization for pitching attitude control, an adaptive method termed adaptive dynamic programming (ADP) with a single NN-termed critic is applied to obtain the optimal control. Time-varying feature functions are applied to construct the critic NN in order to approximate the value function in the Hamilton–Jacobi–Bellman (HJB) equation. Furthermore, a supplementary term is added to the weight update law to minimize the terminal constraint. Lyapunov stability theory is used to prove that the signals in the control system are uniformly ultimately bounded (UUB). Finally, simulation results illustrate the effectiveness of the proposed finite-horizon optimal attitude control method. | |
| dc.language.iso | EN | |
| dc.publisher | MDPI AG | |
| dc.subject.lcc | Motor vehicles. Aeronautics. Astronautics | |
| dc.title | Backstepping-Based Finite-Horizon Optimization for Pitching Attitude Control of Aircraft | |
| dc.type | Article | |
| dc.description.keywords | pitching attitude control | |
| dc.description.keywords | backstepping control | |
| dc.description.keywords | finite-horizon optimization | |
| dc.description.keywords | adaptive method | |
| dc.description.doi | 10.3390/aerospace12080653 | |
| dc.title.journal | Aerospace | |
| dc.identifier.e-issn | 2226-4310 | |
| dc.identifier.oai | oai:doaj.org/journal:220613d5e91b489583c76da5377fb054 | |
| dc.journal.info | Volume 12, Issue 8 | |
