An aerial vehicle engine is proposed which may be powered an adjustable, vortex-based virtual aerospike engine. The vehicle may also include a combustion chamber which may be coupled to the exit nozzle. The combustion chamber may include one or more gas inlets, one or more blanket inlets and one or more main inlets. The gas inlet may be configured to let in a column of gases into the combustion chamber in a direction parallel to the direction of the rocket with minimal angular velocity to prevent the column of gases from mixing with a vortex of propellants or gases. The one or more main inlets may be configured to spray fuel or oxidizer at a specific angle, where the angle may be adjustable for forming the vortex of propellants or gases. The one or more blanket inlets may be configured to spray fuel/oxidizer/(inert) coolant at a specific angle, where the angle may be adjustable and may or may form a vortex, a stagnant pocket of gases (acting as a blanket) or a stream of gases that exits through the exit nozzle. Further, the column of gases inside the combustion chamber leading up to the exit nozzle may form a virtual aerospike nozzle, the virtual aerospike nozzle may exit the gases to propel the vehicle, wherein the virtual aerospike nozzle may not require cooling.


    Access

    Download


    Export, share and cite



    Title :

    Single stage to orbit rocket engine


    Contributors:

    Publication date :

    2024-12-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64G Raumfahrt , COSMONAUTICS



    SINGLE STAGE TO ORBIT ROCKET ENGINE

    UNDIRE ATHARVA | European Patent Office | 2023

    Free access

    SINGLE STAGE TO ORBIT ROCKET ENGINE

    UNDIRE ATHARVA | European Patent Office | 2024

    Free access


    Effects of rocket engine on single-stage-to-orbit vehicle

    Huang, W. D. / Wang, K. C. / Chen, Q. Z. | AIAA | 1998


    Effects of the rocket engine on the single-stage-to-orbit vehicle

    Huang, W. / Wang, K. / Chen, Q. | AIAA | 1997