Means for vaporizing liquid propellants
First Claim
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1. IN A HYBIRD ROCKET ENGINE HAVING AN ANNULARLY DISPOSED SOLID PROPELLANT, A SOURCE OF LIQUID PROPELLANT, A COMBUSTION CHAMBER AND AN EXHAUST NOZZLE THE COMBINATION COMPRISING:
- SAID COMBUSTION CHAMBER CONTAINING SAID SOLID PROPELLANT AND HAVING INJECTORS FOR ENTRY OF SAID LIQUID PROPELLANT;
CONDUIT MEANS DISPOSED WITHIN THE ANNULUS OF THE SOLID PROPELLANT FOR CONDUCTING SAID LIQUID PROPELLANT FROM THE SOURCE OF SUPPLY THEREOF TO THE FORWARD END OF THE SOLID PROPELLANT;
SAID SOLID PROPELLANT SELECTIVELY SPACED FROM SAID CONDUIT MEANS;
AND
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1 Claim
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1. IN A HYBIRD ROCKET ENGINE HAVING AN ANNULARLY DISPOSED SOLID PROPELLANT, A SOURCE OF LIQUID PROPELLANT, A COMBUSTION CHAMBER AND AN EXHAUST NOZZLE THE COMBINATION COMPRISING:
- SAID COMBUSTION CHAMBER CONTAINING SAID SOLID PROPELLANT AND HAVING INJECTORS FOR ENTRY OF SAID LIQUID PROPELLANT;
CONDUIT MEANS DISPOSED WITHIN THE ANNULUS OF THE SOLID PROPELLANT FOR CONDUCTING SAID LIQUID PROPELLANT FROM THE SOURCE OF SUPPLY THEREOF TO THE FORWARD END OF THE SOLID PROPELLANT;
SAID SOLID PROPELLANT SELECTIVELY SPACED FROM SAID CONDUIT MEANS;
AND
- SAID COMBUSTION CHAMBER CONTAINING SAID SOLID PROPELLANT AND HAVING INJECTORS FOR ENTRY OF SAID LIQUID PROPELLANT;
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Current AssigneeAllen L. Holzman
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Original AssigneeAllen L. Holzman
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InventorsHolzman, Allen L.
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Application NumberUS04/435,098Time in Patent Office678 DaysField of SearchUS Class Current60/251CPC Class CodesF02K 9/72 using liquid and solid prop...
