Sep 15, 2026

US12736308 - Anti-air missile guidance technique

A computer implementation processor is provided for directing a missile from a radar towards an interception point of a moving target. The processor includes a missile simulator module; a pre-launch module; a trajectory curvature module; and a guidance module. The missile simulator module determines look angle time to the interception point from the radar. This module determines the look angle time remaining to intercept, at which the angular difference between the line-of-sight to the interceptor and the target are below a threshold value. The pre-launch module provides an initial curvature gain value. The trajectory curvature module updates the curvature gain value from the look angle time. The simulator module receives the gain value in feedback. The guidance module receives the gain value and physical characteristic information for the missile and provides acceleration command to the missile to intercept the target.

Assignee: United States of America, as represented by the Secretary of the Navy
Inventors: Craig Alan Phillips
Filing date: 2024-05-02

The patent describes a computer implementation processor designed to guide a missile towards a moving target by calculating the look angle time and adjusting curvature gain during flight. It includes modules for simulation, pre-launch preparation, trajectory adjustment, and guidance commands to ensure effective interception.

Claim 1

1 . A computer implementation processor for directing a missile during flight time by a radar towards an interception point of a moving target, said processor performing operations comprising: determining look angle time to the interception point from the radar with a line-of-sight between the radar and the target, said look angle time being a portion of the flight time between the missile reaching said line-of-sight and the interception point; providing an initial value of curvature gain; updating said curvature gain from said look angle time during the flight time, said determining operation receiving said curvature gain in feedback; and receiving said curvature gain and physical characteristic information for the missile and providing acceleration command adjusted by said curvature gain to the missile. determining look angle time to the interception point from the radar with a line-of-sight between the radar and the target, said look angle time being a portion of the flight time between the missile reaching said line-of-sight and the interception point; providing an initial value of curvature gain; updating said curvature gain from said look angle time during the flight time, said determining operation receiving said curvature gain in feedback; and receiving said curvature gain and physical characteristic information for the missile and providing acceleration command adjusted by said curvature gain to the missile.

Google Patents

https://patents.google.com/patent/US12736308

USPTO PDF

https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/12736308