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An injection head for a liquid-propelled rocket engine has a plurality of first and second injection bores for injecting jets of first and second propellant constituents, respectively, into the combustion chamber of a rocket engine, with mutual mixing of propellant constituents. The first injection

An injection head for a liquid-propelled rocket engine has a plurality of first and second injection bores for injecting jets of first and second propellant constituents, respectively, into the combustion chamber of a rocket engine, with mutual mixing of propellant constituents. The first injection bores are provided for injecting jets of the first propellant constituent with a high impulse, and the second injection bores are provided for injecting propellant jets of the second propellant constituent with a low impulse. In addition, the first and second injection bores are mutually arranged such that an admixing of the second propellant constituent to the first propellant constituent takes place under an ejector effect of the propellant jets of the first propellant constituent leaving the first injection bores.

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What is claimed is: 1. An injection head for a liquid-propelled rocket engine having a number of first and second injection bores for injecting jets of a first propellant constituent and of a second propellant constituent, respectively, into a combustion chamber of a rocket engine, with the mutual

What is claimed is: 1. An injection head for a liquid-propelled rocket engine having a number of first and second injection bores for injecting jets of a first propellant constituent and of a second propellant constituent, respectively, into a combustion chamber of a rocket engine, with the mutual mixing of propellant constituents, wherein: the first injection bores are configured to inject jets of the first propellant constituent with a high impulse; the second injection bores are configured to inject jets of the second propellant constituent with a low impulse; the first and second injection bores are mutually arranged such that an admixing of the second propellant constituent with the first propellant constituent takes place under an ejector effect of the propellant jets of the first propellant constituent leaving the first injection bores; the first injection bores have a small flow cross-section for generating the jets of the first propellant constituent with a high impulse; the second injection bores have large flow cross-section for generating the jets of the second propellant constituent with a low impulse; the first injection bores and the second injection bores lead out at the surface of an injection plate bounding the injection head on a combustion chamber side; on the surface of the injection plate, the second injection bores have a first area with a large flow cross-section provided for generating the jets of the second propellant constituent with a low impulse and, upstream with respect to the flow direction of the second propellant constituent, a second area with a small flow cross-section; the injection bores are arranged with their axes parallel to one another; and the first injection bores and the second injection bores are arranged alternately in an alternating checkerboard configuration. 2. An injection head for a liquid-propelled rocket engine having a number of first and second injection bores for injecting jets of a first propellant constituent and of a second propellant constituent, respectively, into a combustion chamber of a rocket engine, with the mutual mixing of propellant constituents, wherein: the first injection bores are configured to inject jets of the first propellant constituent with a high impulse; the second injection bores are configured to inject jets of the second propellant constituent with a low impulse; the first and second injection bores are mutually arranged such that an admixing of the second propellant constituent with the first propellant constituent takes place under an ejector effect of the propellant jets of the first propellant constituent leaving the first injection bores; the first injection bores have a small flow cross-section for generating the jets of the first propellant constituent with a high impulse; the second injection bores have a large flow cross-section for generating the jets of the second propellant constituent with a low impulse; the first injection bores and the second injection bores lead out at the surface of an injection plate bounding the injection head on a combustion chamber side; on the surface of the injection plate, the second injection bores have a first area with a large flow cross-section provided for generating the jets of the second propellant constituent with a low impulse and, upstream with respect to the flow direction of the second propellant constituent, a second area with a small flow cross-section; the injection bores are arranged with their axes parallel to one another; the first injection bores and the second injection bores are arranged alternately in a honeycomb configuration; the first injection bores have a diameter of from 0.05 to 0.5 mm; the second injection bores have a diameter of from 0.2 to 2 mm. 3. The injection head according to claim 2, wherein the first injection bores have a diameter of from 0.05 to 0.15 mm. 4. The injection head according to claim 2, wherein a distance between the first injection bores and the second injection bores is smaller than 2 mm. 5. The injection head according to claim 4, wherein a distance between the first injection bores and the second injection bores is smaller than 1 mm.