The hypersonic target has the characteristics of a large attack angle, fast flight speed, and strong maneuverability in the reentry phase, whereas the missile has a relatively low speed, which puts forward a high overload requirement for the missile. In order to reduce the overload requirement of missile, a composite optimal predictive guidance law is proposed. Firstly, a tactical Lambert guidance is proposed based on Lambert problem. When the missile and target maneuver in the existing way, the missile can intercept the target under the condition of zero-effort. Then, an optimal predictive guidance law is designed to satisfy the initial conditions of Lambert guidance based on variational method. Finally, considering that the target maneuvering mode will change during the guidance process, a predictive guidance law based on the zero-effort miss distance is designed to correct the missile trajectory. The simulation results show that the composite optimal predictive guidance law can effectively reduce the missile’s overload when intercepting hypersonic targets, and improve the guidance accuracy; in addition, when the target maneuvering mode does not change, the time-to-go can be accurately estimated.
A composite optimal predictive guidance law for hypersonic target interception
01.10.2022
1287076 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Predictive Differential Game Guidance Approach for Hypersonic Target Interception Based on CQPSO
DOAJ | 2022
|Suboptimal Midcourse Guidance with Terminal-Angle Constraint for Hypersonic Target Interception
DOAJ | 2019
|DOAJ | 2022
|