Velocity controller for ramjet missile and method therefor
US4745740A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 24, 1986 |
| Grant date | May 24, 1988 |
| Priority date | — |
| Expiry date | Feb 24, 2006 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/042
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A velocity controller for a ramjet missile, having a supersonic inlet proximate the peripheral skin thereof for admitting air to a combustion zone of a ramjet engine, is comprised of a variable pitch cover disposed in pivotable engagement within the inlet and an actuator in operative engagement with the cover for adjustably positioning same over an angular range and thereby modulating airflow for the purpose of controlling flight characteristics and, principally, velocity of the missile. A sensing system is provided for detecting a dynamic flight parameter indicative of velocity of the missile and generating an output characteristic thereof for controlling the actuator and, in turn, the pitch of the cover. Methods for improving the flight performance of both solid fuel ramjet missiles and ducted rocket missiles are also disclosed herein.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.