Patent ID: 11952967
Assignee: SIERRA SPACE CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A vortex hybrid motor, comprising:
a combustion chamber housing having a proximal end, a distal end, and a sidewall extending between the proximal end and the distal end;
an injector ring positioned adjacent the proximal end of the combustion chamber housing and including a circular body that extends along a circumference of the sidewall, the injector ring comprising:
a plurality of angled injector units circumferentially positioned along the circular body, each of the angled injector units including a first injector and a second injector angled towards an impingement point such that a first fluid stream of a liquid propellant dispensed from the first injector collides with a second fluid stream of the liquid propellant dispensed from the second injector to atomize the liquid propellant and form a spray fan formation, the spray fan formation including the atomized liquid propellant dispersed along an injection plane, at least one of the first injector and the second injector positioned at an injection angle relative to the sidewall such that at least one of the first fluid stream and the second fluid stream, respectively, is dispensed at the injection angle to create a swirl flow of the atomized injector fluid, the plurality of angled injector units comprising:
a first angled injector unit comprising the first injector and the second injector extending along a vertical plane that is parallel to a longitudinal axis of the combustion chamber housing; and
a second angled injector unit comprising the first injector and the second injector extending along a horizontal plane that is transverse to the longitudinal axis of the combustion chamber housing, the first angled injector unit and the second angled injector unit alternating along a length of the circular body of the injector ring; and

a solid propellant positioned within the combustion chamber housing and configured to react with the atomized liquid propellant to thereby create a thrust sufficient to propel at least the vortex hybrid motor.