Patent ID: 11879416
Assignee: RAYTHEON COMPANY
Field: Other special machines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 7:
8. A missile, comprising:
a jet assembly;
a thrust vector controller configured to change a thrust deflection angle of an exhaust plume exiting an exit end of a rocket nozzle of the missile after a launch of the missile, thereby creating a lateral control moment on the missile, wherein the thrust vector controller is configured to control the jet tab assembly to change the thrust deflection angle of the exhaust plume; and
a roll controller configured to roll the missile simultaneously with the change of the thrust deflection angle of the exhaust plume by the thrust vector controller, wherein the roll controller is configured to roll the missile a roll amount that is a function of the lateral control moment on the missile and a reduction of maximum exposure of any one of a plurality of jet tabs in the jet tab assembly.