O2/H2 Advanced Maneuvering Propulsion Technology Program. Water-Cooled Segment Testing
O2/H2 Advanced Maneuvering Propulsion Technology Program. Water-Cooled Segment Testing
This report describes the analysis, design, fabrication, and test of water-cooled segments to define the most suitable injector configurations and combustion chamber geometries for 25,000-pound-thrust, O2/H2, lightweight, aerospike thrust chambers. Two-hundred and seventy-one hot-fire tests with numerous injector and chamber configurations were conducted at chamber pressures between 140 and 988 psi. The injector development was supplemented with cold-flow tests of single injection elements. High measured performance was demonstrated in low-volume combustion chambers (3.0-inch length from injector face to the throat).
Dokumentinformationen
O2/H2 Advanced Maneuvering Propulsion Technology Program. Water-Cooled Segment Testing
1972
429 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Liquid propellant rocket engines , Liquid cooled , Water , Combustion chambers , Regenerative cooling , Air , Plug nozzles , Coolants , Heat transfer , Fuel injectors , Baffles , Captive tests , Nozzle throats , Hydrogen , Liquefied gases , Oxygen , Propellant tanks , Nozzle area ratio , Silver alloys , Copper alloys , Liquid rocket oxidizers , Panels , Planning , Aerospike nozzles