Hybrid rocket motor with integral oxidizer tank

Patent metadata

Field	Value
Publication number	US-10823115-B2
Application number	US-201615044490-A
Country	US
Kind code	B2
Filing date	Feb 16, 2016
Priority date	Feb 16, 2016
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

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:
a solid fuel adjoining and at least partially defining a combustion chamber; and
an oxidizer tank at least partially within the combustion chamber, 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; and
wherein the oxidizer tank is supported by a series of radial ribs that extend outward from the oxidizer tank, radially through the combustion chamber, to a radially inner surface of the solid fuel that at least partially defines the combustion chamber.

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 oxidizer from the liquid 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 and the solid fuel are parts of a single unitary piece of material.

10. The hybrid rocket motor of claim 9 , wherein the single unitary piece that includes the solid fuel and the oxidizer tank is formed by additive manufacturing.

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

12. 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, with the solid fuel element adjoining and at least partially defining a combustion chamber, and with the oxidizer tank at least partially within the combustion chamber, the oxidizer tank within the solid fuel element;
filling the oxidizer tank with a liquid oxidizer;
wherein the solid fuel element and the liquid oxidizer from the oxidizer tank are burned in the combustion chamber to produce thrust in the hybrid rocket motor; and
wherein the oxidizer tank is supported by a series of radial ribs that extend outward from the oxidizer tank, radially through the combustion chamber, to a radially inner surface of the solid fuel element that at least partially defines the combustion chamber.

13. The method of claim 12 , wherein the using additive manufacturing includes extruding a fuel material to produce the solid fuel element, and an oxidizer tank material to produce the oxidizer tank.

14. The method of claim 13 , wherein the fuel material and the oxidizer tank material are extruded by respective extruders.

15. The method of claim 12 ,
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.

16. A hybrid rocket motor comprising:
a solid fuel adjoining and at least partially defining a combustion chamber; and
an oxidizer tank fully within the combustion chamber, 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;
wherein the oxidizer tank is supported by a series of radial ribs that extend outward from the oxidizer tank, radially through the combustion chamber, to a radially inner surface of the solid fuel that at least partially defines the combustion chamber.

17. The hybrid rocket motor of claim 16 , wherein the oxidizer tank encloses the liquid oxidizer within, during combustion in the combustion chamber radially outward from the oxidizer tank.

Assignees

• Raytheon Co

Inventors

• Summers Matt H
• Danforth Jeremy C

Classifications

• F05D2230/53

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

• F02K9/72 Primary

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

• F05D2230/24

  by extrusion · CPC title

• F02K9/32

  Constructional parts; Details not otherwise provided for · CPC title

• F02K9/10

  Shape or structure of solid propellant charges · CPC title