Method and apparatus for enhancing combustion efficiency of solid fuel hybrid rocket motors
AssigneeThiokol Corporation
InventorsGary K. Lund, Kent W. Richman
Life of this patent
Estimating the term…
Abstract
A hybrid rocket motor having enhanced fuel combustion efficiency is disclosed which includes a plurality of axially aligned fuel grains having multiple axial perforations. The fuel grains are rotated or canted relative to adjacent fuel grains such that the multiple axial perforations are offset.
Claims20
A hybrid rocket motor comprising:
- a combustion chamber having aft and forward sections;
- and
- a plurality of solid fuel grains, each grain containing more than one perforation and said fuel grains being cartridge loaded into the combustion chamber along a rocket motor axis such that the perforations of at least two solid fuel grains are misaligned with the perforations of an adjacent solid fuel grain and such that the fuel grains are arranged within the combustion chamber to allow gas flow through the perforations in a direction substantially parallel to the rocket motor axis.
A hybrid rocket motor having enhanced fuel combustion efficiency comprising a plurality of fuel grains, said fuel grains being aligned along a rocket motor axis and having multiple axial perforations, at least two of said fuel grains being rotated around the rocket motor axis relative to adjacent fuel grains so as to offset the multiple axial perforations with respect to adjacent multiple axial perforations, and wherein the plurality of fuel grains are arranged within the hybrid rocket motor to allow gas flow through the multiple axial perforations in a direction substantially parallel to the rocket motor axis.
A hybrid rocket motor having enhanced fuel combustion efficiency comprising a plurality of fuel grains, said fuel grains being aligned in a longitudinal direction along a rocket motor axis and having multiple perforations in said longitudinal direction, at least two of said fuel grains being horizontally offset, along a horizontal plane normal to the rocket motor axis, relative to adjacent fuel grains such that the multiple longitudinal perforations are horizontally offset, and wherein the plurality of fuel grains are structurally located within the hybrid rocket motor to allow gas flow through the multiple longitudinal perforations in a direction substantially parallel to the rocket motor axis.
Dependencies are inferred from the claim text.