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Ignition system for rocket engine combustion chambers operated by non- hypergolic propellant components
Ignition system for rocket engine combustion chambers operated by non- hypergolic propellant components
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机译：由非高射性推进剂部件运行的火箭发动机燃烧室点火系统
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摘要
An ignition system for rocket engine combustion chambers which are operated by non-hypergolic propellant components and particularly for the pre-combustion chambers of main stream engines of this type, comprises a main combustion chamber having injector means for injecting a propellant component into the combustion chamber for combustion therein. Since the propellant components employed are non-hypergolically reactive, they are ignited by an ignition agent which is produced by the pressure of a first propellant component which is non-hypergolically reactive with the ignition agent into the combustion chamber. The second propellant component which reacts with the ignition agent hypergolically is also introduced into the combustion chamber so that ignition takes place immediately. The arrangement includes a storage tank for the ignition agent having a piston movable therein by admission of the propellant component which is non-hypergolically reactive with the ignition agent to one side of the storage space which contains the ignition agent which in turn is moved by the piston from the other side of the storage space out through a connecting passage into the combustion chamber. After the piston has travelled an amount sufficient to direct a predetermined quantity of the ignition agent into the combustion chamber, the piston passes a port which communicates the propellant component with the combustion chamber so that it can flow after the ignition agent into the combustion chamber for reaction with the other propellant component which is also introduced into the combustion chamber.
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