Nonlinear guidance gain factor for guided missiles
US5975460A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 10, 1997 |
| Grant date | Nov 2, 1999 |
| Priority date | — |
| Expiry date | Nov 10, 2017 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF41G7/22
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
A system (10') for generating a missile guidance gain factor adapted for use with guided missiles. The inventive system includes a guidance control system (52) for obtaining current guidance parameters(55, 57) including ideal navigation gain, closing rate, line of sight rate, missile maneuverability, and missile velocity parameters. Software (56) running on a guidance control processor (54) computes a current guidance gain factor reflective of the current maneuverability of the missile from the guidance parameters (55, 57). In the illustrative embodiment, the system 10' further includes a nonlinear notch circuit (56) that generates an acceleration command (59) from the guidance parameters (55, 57) that varies in response to varying missile maneuverability parameters (57). The guidance control system (10') includes a conventional guidance law computation circuit (54, 55) and electromagnetic sensing equipment (52). An autopilot circuit (58) included in the system (10') provides the missile maneuverability parameters (57). In a specific embodiment, the nonlinear notch circuit (56) is implemented via software running on a guidance processor (54) which performs the following computation…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.