Hybrid rocket motor with integral oxidizer tank

Patent metadata

Field	Value
Publication number	US-11326556-B2
Application number	US-202017035880-A
Country	US
Kind code	B2
Filing date	Sep 29, 2020
Priority date	Feb 16, 2016
Publication date	May 10, 2022
Grant date	May 10, 2022

Abstract

A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.

First claim

What is claimed is:

1. A hybrid rocket motor comprising:
an outer casing;
a solid fuel radially inward of the outer casing, the solid fuel adjoining and at least partially defining a combustion chamber that is a cavity inside the solid fuel; and
an oxidizer tank fully within the cavity, and within the solid fuel;
wherein the solid fuel and a liquid oxidizer from the oxidizer tank are burned in the combustion chamber to produce thrust in the hybrid rocket motor.

2. The hybrid rocket motor of claim 1 ,
wherein the combustion chamber is cylindrical; and
wherein the oxidizer tank is located along a central longitudinal axis of the combustion chamber.

3. The hybrid rocket motor of claim 1 , wherein the solid fuel has injection ports for releasing the liquid oxidizer from the oxidizer tank into the combustion chamber.

4. The hybrid rocket motor of claim 1 , wherein the solid fuel includes a fuel plastic material.

5. The hybrid rocket motor of claim 4 , wherein the solid fuel also includes an energetic additive to the fuel plastic material.

6. The hybrid rocket motor of claim 1 , wherein the oxidizer tank includes an oxidizer tank plastic material.

7. The hybrid rocket motor of claim 6 , wherein the oxidizer tank plastic material is the same as a fuel plastic material that is at least part of the solid fuel.

8. The hybrid rocket motor of claim 6 , wherein the oxidizer tank plastic material is different from a fuel plastic material that is at least part of the solid fuel.

9. The hybrid rocket motor of claim 1 , wherein the oxidizer tank is supported by a series of ribs that connect the oxidizer tank to an outer casing of the hybrid rocket motor that surrounds the combustion chamber.

10. The hybrid rocket motor of claim 1 , wherein the oxidizer tank and the solid fuel are parts of a single unitary piece of material.

11. The hybrid rocket motor of claim 10 , wherein the single unitary piece that includes the solid fuel and the oxidizer tank is formed by additive manufacturing.

12. The hybrid rocket motor of claim 1 , wherein the hybrid rocket motor is part of a flying vehicle.

13. A method of making a hybrid rocket motor, the method comprising:
using additive manufacturing to form a solid fuel element and an oxidizer tank of the hybrid rocket motor radially inward of an outer casing of the hybrid rocket motor, with a combustion chamber that is a cavity within the solid fuel element, and with the oxidizer tank fully within the cavity; and
filling the oxidizer tank with a liquid oxidizer;
wherein the solid fuel element and the liquid oxidizer from the oxidizer tank are configured to be burned in the combustion chamber to produce thrust in the hybrid rocket motor.

14. The method of claim 13 , wherein the using additive manufacturing includes extruding fuel material to produce the solid fuel element, and an oxidizer tank material to produce the oxidizer tank.

15. The method of claim 14 , wherein the fuel material and the oxidizer tank material are extruded by respective extruders.

16. The method of claim 13 , wherein the using the additive manufacturing also includes forming a support structure for the oxidizer tank.

17. The method of claim 13 ,
wherein the using additive manufacturing includes forming a fill line for filling the oxidizer tank; and
further comprising, subsequent to the using additive manufacturing, filling the oxidizer tank with the liquid oxidizer.

Assignees

• Raytheon Co

Inventors

• Summers Matt H
• Danforth Jeremy C

Classifications

• F02K9/72 Primary

  using liquid and solid propellants, i.e. hybrid rocket-engine plants · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• F05D2230/30

  with deposition of material · CPC title

• F05D2230/53

  by integrally manufacturing a component, e.g. by milling from a billet or one piece construction · CPC title

• F05D2230/22

  by sintering · CPC title