Modulating internal ballistics in a 3D-printed rocket motor and an additive manufacturing process
A method of making a multi-grained fuel grain for a rocket is disclosed, the method comprising the steps of using at least one nozzle to extrude a first propellant in an additive manufacturing process, the first propellant comprising a multi-grained fuel grain, the multi-grained fuel grain forming the at least one void, the at least one void facilitating variation in internal ballistics, forming sensors, said sensors permitting continuous monitoring and continuous modification such that a user controls the ballistics profile of a rocket motor, forming an electrically-controlled second propellant in contact with and operatively coupled to the sensors; and wherein the additive manufacturing process uses at least at least one nozzle to extrude raw materials.
1. A propulsion system for a rocket, comprising:
rocket combustion components;
a multi-grained fuel grain forming a fuel grain section, the fuel grain section contained in a rocket body, said fuel grain section having a generally cylindrical shape defining a center chamber, the center chamber having a substantially circular cross-section;
a payload section, said payload section located at a distal end of the rocket body;
said rocket body further comprising at least one annular section, wherein said at least one annular section is embedded with sensors;
wherein said sensors provide continuous monitoring and continuous modification such that a user controls the ballistics profile of a rocket motor;
wherein electrically-controlled propellants come in contact with and operatively couple to the sensors;
wherein said sensors comprise an electrically conductive fill in a polymer;
wherein said sensors are used to indicate relative stabilizer depletion and to measure internal off-gassing; and
wherein said at least one annular section is formed via additive manufacturing by applying successive fuel beads for a predefined distance and time.
2. The propulsion system of claim 1 , wherein successive fuel beads are applied continuously for a predefined distance in the direction primarily parallel to the central axis.
3. The propulsion system of claim 1 , wherein the at least one annular section comprises a multi-grained fuel grain, the multi-grained fuel grain printed by fuel beading, the multi-grained fuel grain further formed by printing successive layers of dissolvable core, the multi-grained fuel grain and the dissolvable core printed layer by layer.
4. The propulsion system of claim 1 , wherein said rocket combustion components comprise at least one oxidizer, at least one rocket fuel, at least one catalyst, and a binder.
5. The propulsion system of claim 4 , wherein the binder comprises casein, methyl cellulose, polyethylene oxide, polyvinyl acetate, hydroxy-functional prepolymers of polybutadiene, and/or polyvinyl alcohol.
6. The propulsion system of claim 3 , wherein the multi-grained fuel grain may be supported by a fuel grain support structure, the fuel grain support structure comprising solid propellant and having unique geometrically shaped bead layers.
7. The propulsion system of claim 3 , wherein the multi-grained fuel grain may be supported by a fuel grain support structure, the fuel grain support structure comprising a solid catalyst and having unique geometrically shaped bead layers.
8. The propulsion system of claim 4 , wherein said rocket fuel may comprise a metal-based fuel, polybutadiene acrylic acid acrylonitrile prepolymer, and a perchlorate oxidizer.