Abstract: An aerospike engine configured to be connected to a liquid methane tank, and to a liquid oxygen tank is provided. The aerospike engine comprises a centerbody including an aerospike nozzle, an external skirt, and a combustion chamber being defined between the external skirt and the centerbody. The centerbody is additively manufactured from one or more copper alloys and has a plurality of centerbody internal cooling channels. The external skirt is additively manufactured from one or more copper alloys and has a plurality of skirt internal cooling channels. The aerospike engine is configured to supply liquid methane and liquid oxygen through the internal cooling channels to the combustion chamber. Also disclosed are stages of a launch vehicle and a launch vehicle comprising such an aerospike engine, as well as methods for re-entry for a re-usable stage of a launch vehicle comprising an aerospike engine.

Abstract: A stage for a space launch vehicle is provided. The space launch vehicle has a main body including a first end and a second end, and defines a central longitudinal axis between the first end and the second end. The stage comprises a stage rocket engine arranged at or near the first end of the stage to propel the launch vehicle vertically upwards at take-off. The stage furthermore comprises a plurality of fans for providing lift during a landing procedure of the stage, wherein the fans have a rotational axis arranged substantially perpendicular to the central longitudinal axis. Also provided are space launch vehicles and methods for transporting a payload into space.

Abstract: A stage for a space launch vehicle is provided. The space launch vehicle has a main body including a first end and a second end, and defines a central longitudinal axis between the first end and the second end. The stage comprises a stage rocket engine arranged at or near the first end of the stage to propel the launch vehicle vertically upwards at take-off. The stage furthermore comprises a plurality of fans for providing lift during a landing procedure of the stage, wherein the fans have a rotational axis arranged substantially perpendicular to the central longitudinal axis. Also provided are space launch vehicles and methods for transporting a payload into space.