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.
Single stage to orbit rocket engine
2024-12-24
Patent
Electronic Resource
English
Effects of Rocket Engine on Single-Stage-to-Orbit Vehicle
Online Contents | 1998
|Rocket Propulsion For Single Stage To Orbit
British Library Conference Proceedings | 1994
|