Adaptive sliding model guidance law considering input saturation and autopilot lag
Source abstract
Abstract
In this paper, a guidance law is developed using the sliding model control theory. The designed law possesses good performance when a maneuvering target is intercepted with the consideration of the input saturation and autopilot lag. Regarding the target acceleration as unknown bounded external disturbance, the adaptive control is designed to estimate the upper bound of the disturbance in such a way that it is not required to be known in advance. A sliding model estimator is also presented to estimate the line-of-sight angle rate for which the guidance law is required. According to the Lyapunov theory, the guidance law can be converging to zero, which is proved. Several simulations including 100 Monte Carlo are made to validate the effectiveness of the proposed guidance law.
Source: crossref · Quality: baseline
Research context
OpenAlex topics: Guidance and Control Systems · Military Defense Systems Analysis · Adaptive Control of Nonlinear Systems
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
School of Electronics and Information, JiangSu University of Science and Technology 1 , Zhenjiang 212100, China
National Key Laboratory of Transient Physics, Nanjing University of Science and Technology 2 , Nanjing 210094, China
Funding
China Postdoctoral Science Foundation · National Natural Science Foundation of China
References (17)
Show source-provided references
1. Terminal guidance for impact attitude angle constrained flight trajectories10.1109/taes.1973.309659 ↗
2. Optical guidance with constraints on impact angle and terminal acceleration
3. Time-optimal impact angle control for vertical plane engagements10.1109/7.766954 ↗
4. State-dependent Riccati-equation-based guidance law for impact angle constrained trajectories10.2514/1.37876 ↗
5. Impact angle constraint interceptor of stationary targets10.2514/1.37864 ↗
6. Impact angle constrained guidance against non-stationary non-maneuvering targets10.2514/1.45026 ↗
7. Impact angle control guidance law using Lyapunov function and PSO method
8. Linear quaratic guidance laws for imposing a terminal intercept angle10.2514/1.32836 ↗
9. Proportional navigation through predictive control10.2514/2.4339 ↗
10. Guidance of homing missile via nonlinear geometric-control method10.2514/3.21407 ↗
11. Optimal fixed-interval integrated guidance-control law for hit-to-kill missiles
12. Nonlinear H∞ robust guidance law for homing missiles10.2514/2.4321 ↗
13. Effect of estimation on the performance of an integrated missile guidance and control system10.1109/taes.2011.6034659 ↗
14. Adaptive sliding mode guidance law with input constraints and autopilot lag
15. Target state estimation fore integrated guidance-control of missiles
16. Nonlinear state estimator base on realistic seeker measurements for closed loop applications
17. Maneuver target tracking with an acceleration estimator using target past positions10.1002/ecja.10026 ↗