Missile control system and method
US7287725B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 25, 2005 |
| Grant date | Oct 30, 2007 |
| Priority date | — |
| Expiry date | Apr 25, 2025 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.