Terminal guidance method and a guided missile operating according to this method
US4568040A · kind A · utility
40Cited by
14References
16Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Dec 3, 1982 |
| Grant date | Feb 4, 1986 |
| Priority date | — |
| Expiry date | Dec 3, 2002 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF42C13/006
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
A guidance method is provided for the terminal portion of the trajectory of a guided missile having a sensor and comprising two sections coupled together by a central shaft and free to rotate with respect to one another about the longitudinal axis of the missile; one section comprises a drive means for controlling the roll attitude of this section and a gas generator which feeds a nozzle for providing a transverse throat force and the other section has a stabilizing tail unit formed by a set of fins able to be opened out.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.