ROCKETS
Assignee
Filed
Aug 3, 1977
Granted
Jun 27, 1989
Location
GB
Abstract
An integrated rocket ramjet in which initial acceleration of the rocket is achieved by a rocket fuel propellant and subsequent flight is sustained by a ramjet engine receiving air via a supersonic diffuser from an inlet disposed at the middle of the rocket. The flame for the ramjet combustion system is incorporated into the diffuser so that diffusion and combustion take place simultaneously. The combustion process continues within the space previously occupied by the rocket fuel propellant and the walls bounding this space are the outer casing of the rocket and are directly cooled by free stream air flowing past the rocket.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Aug 25, 1982
Rescinded
Jul 27, 1988
Duration
5 years, 11 months
Inventor
- 1JOHN MATTHEW HALL
Record Details
- Patent number
- US 4841724
- Application
- 05822959
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
More from this assignee
IMPROVED CATALITIC SYNTHESIS OF CAGED POLYNITRAMINE COMPOUNDS
SOLID ROCKET PROPELLANT
DUAL INFRARED BAND OBJECTIVE LENS
BANDGAP RADIATION DETECTOR
METHOD OF FORMING TEXTURED HIGH-TEMPERATURE SUPERCONDUCTORS
APPARATUS FOR CONTROLLING THE POSITION AND DIRECTION OF A LASER BEAM
Related by domain
NEURAL NETWORK CONTROLLER FOR A PULSED ROCKET MOTOR TACTICAL MISSILE SYSTEM
Raytheon
VTOL AIRCRAFT NOZZLE
ROLLS-ROYCE PLC
MISSILE JET VANE CONTROL SYSTEM AND METHOD
HUGHES MISSILE SYSTEMS COMPANY
COOLED AIRFOILS FOR A GAS TURBINE ENGINE
UNITED TECHNOLOGIES CORPORATION
LOW OBSERVABLE ENGINE AIR INLET SYSTEM
UNITED TECHNOLOGIES CORPORATION
VECTORABLE NOZZLE FOR AIRCRAFT
ROLLS-ROYCE PLC