A dual mode engine for propelling a spacecraft, including a combustion chamber having a flange end, an open nozzle end, and an enclosed chamber portion extending therebetween, a propellant tank in fluidic communication with the combustion chamber, an electronic controller, a power source operationally connected to the electronic controller, and a fluid flow motivator operationally connected to the electronic controller and connected in fluidic communication with the propellant tank. The engine further includes a chemical propulsion portion further including a propellant inlet port operationally connected to the combustion chamber and disposed adjacent the flange end, an ignition trigger electrode positioned in the combustion chamber adjacent the propellant inlet port and operationally connected to the electronic controller and operationally connected to the power source, wherein the propellant inlet port is fluidically connected to the propellant tank. The engine also includes an electric propulsion portion, further including at least two spaced electrodes for ionizing the propellant positioned in the combustion chamber adjacent the nozzle end, a plurality of attitude control thrusters operationally connected to the electronic controller and in fluidic communication with the propellant tank, and a plurality of respective valves, each respective valve fluidically connected between a respective attitude control thruster and the propellant tank, wherein the propellant inlet port is fluidically connected to the propellant tank.
DUAL-MODE ELECTRICAL AND CHEMICAL PROPULSION SYSTEM FOR SMALL SPACECRAFT AND CUBESATS
2024-04-25
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS |
DUAL-MODE ELECTRICAL AND CHEMICAL PROPULSION SYSTEM FOR SMALL SPACECRAFT AND CUBESATS
European Patent Office | 2024
|Online Contents | 2017
|Elsevier | 2017
|Hybrid Propulsion for CubeSats
NTRS | 2016
|