Flexible bearing assemblies, rocket motors including such assemblies, and methods of forming flexible bearings

Patent metadata

Field	Value
Publication number	US-10815936-B2
Application number	US-201615347621-A
Country	US
Kind code	B2
Filing date	Nov 9, 2016
Priority date	Nov 9, 2016
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

A flexible bearing assembly includes at least one metal end ring, a flexible bearing core having a plurality of layers of a resilient material between layers of a reinforcement material, and a phenolic composite material between and bonded to each of the at least one metal end ring and the flexible bearing core. A rocket motor assembly includes a chamber configured to contain a propellant and a movable thrust nozzle coupled to the chamber. The movable thrust nozzle includes a phenolic composite material between and bonded to each of a metal end ring and a flexible bearing core. Methods of forming a flexible bearing assembly include bonding a phenolic composite material to at least one metal end ring and bonding a flexible bearing core to the phenolic composite material. The flexible bearing core includes a plurality of layers of a resilient material between layers of a reinforcement material.

First claim

What is claimed is:

1. A rocket motor assembly, comprising:
a movable thrust nozzle, comprising:
a first metal end ring;
a second metal end ring;
a flexible bearing core comprising a plurality of layers of a resilient material between layers of a reinforcement material, the flexible bearing core disposed between the first metal end ring and the second metal end ring;
a first phenolic composite material disposed between and bonded to each of the first metal end ring and a first layer of resilient material of the flexible bearing core, wherein the first phenolic composite material has a wedge-shaped cross-section; and
a second phenolic composite material disposed between and bonded to each of the second metal end ring and a second layer of resilient material of the flexible bearing core, wherein the second phenolic composite material has a cross-sectional shape at least substantially matching cross-sectional shapes of the layers of a reinforcement material.

2. The rocket motor assembly of claim 1 , wherein the first metal end ring comprises steel.

3. The rocket motor assembly of claim 1 , wherein the resilient material comprises an elastomer.

4. The rocket motor assembly of claim 1 , wherein the reinforcement material comprises glass and a phenolic resin.

5. The rocket motor assembly of claim wherein the plurality of layers of the resilient material each comprise surfaces partially defining concentric spheres.

6. A rocket motor assembly, comprising:
a chamber configured to contain a propellant; and
a movable thrust nozzle coupled to the chamber, the movable thrust nozzle comprising:
a first metal end ring;
a second metal end ring;
a flexible bearing core comprising a plurality of layers of a resilient material between layers of a reinforcement material, the flexible bearing core disposed between the first metal end ring and the second metal end ring;
a first phenolic composite material disposed between and bonded to each of the first metal end ring and a first layer of resilient material of the flexible bearing core, wherein the first phenolic composite material has a wedge-shaped cross-section;
a second phenolic composite material disposed between and bonded to each of the second metal end ring and a second layer of resilient material of the flexible bearing core; and
an adhesive comprising a phenolic polymeric material and carbon fibers disposed between the first phenolic composite material and the first metal end ring and between the second phenolic composite material and the second metal end ring, the adhesive forming a composite material with both the first phenolic composite material and the second phenolic composite material.

7. The rocket motor assembly of claim 6 , wherein the first metal end ring is fixed in relation to the chamber.

8. The rocket motor assembly of claim 6 , wherein one of the first metal end ring and the second metal end ring is capable of moving relative to the other by deformation of at least one of the layers of the resilient material.

9. The rocket motor assembly of claim 6 , further comprising a solid propellant within the chamber.

10. A method of forming a rocket motor assembly, comprising:
forming a movable thrust nozzle, comprising the steps:
bonding a first phenolic composite material to a first metal end ring,
bonding a second phenolic composite material to a second metal end ring; and
bonding a flexible bearing core to the first and second phenolic composite materials, the flexible bearing core comprising a plurality of layers of a resilient material between layers of a reinforcement material, wherein bonding the first phenolic composite material to the first metal end ring and bonding the second phenolic composite material to the second metal end ring occurs prior to bonding the flexible bearing core to the first and second phenolic composite materials,
wherein the first phenolic composite material has a wedge-shaped cross-section, and
wherein the second phenolic composite material has a cross-sectional shape at least substantially matching cross-sectional shapes of the layers of a reinforcement material.

11. The method of claim 10 , further comprising forming the flexible bearing core by forming the plurality of layers of the resilient material between the layers of the reinforcement material.

12. The method of claim 11 , wherein forming the plurality of layers of the resilient material between the layers of the reinforcement material comprises forming an adhesive bond between the resilient material and the reinforcement material.

13. The method of claim 11 , wherein forming the plurality of layers of the resilient material between the layers of the reinforcement material comprises crosslinking a polymeric material to form the resilient material.

14. The method of claim 11 , wherein forming the plurality of layers of the resilient material between the layers of the reinforcement material comprises forming the plurality of layers of the resilient material between the layers of the reinforcement material before at least one of bonding the first phenolic composite material to the first metal end ring, bonding the second phenolic composite material to the second metal end ring, or bonding the flexible bearing core to the first and second phenolic composite materials.

15. The method of claim 10 , further comprising non-destructively evaluating the flexible bearing core before at least one of bonding the first phenolic composite material to the first metal end ring, bonding the second phenolic composite material to the second metal end ring, or bonding the flexible bearing core to the first and second phenolic composite materials.

16. The method of claim 15 , wherein non-destructively evaluating the flexible bearing core comprises exposing the flexible bearing core to high-energy radiation.

17. The method of claim 16 , wherein exposing the flexible bearing core to high-energy radiation comprises exposing the flexible bearing core to X-ray radiation.

18. The method of claim 10 , further comprising coupling at least one of the first metal end ring and the second metal end ring to a chamber containing a propellant.

Assignees

• Northrop Grumman Innovation Systems Inc

Inventors

• Garbe Duane J
• Collins Edward L
• Thompson Allan P

Classifications

• F02K9/86 Primary

  using nozzle throats of adjustable cross- section {(F02K9/978 takes precedence)} · CPC title

• B29C65/1403

  characterised by the type of electromagnetic or particle radiation (B29C65/1603 takes precedence) · CPC title

• F02K9/80

  characterised by thrust or thrust vector control (burning control of solid propellants F02K9/26; feeding control of liquid or gaseous propellants F02K9/56; re-ignitable, restartable or intermittently operated rocket-engine plants F02K9/94) · CPC title

• F05D2230/23

  by permanently joining parts together · CPC title

• F02K9/97

  Rocket nozzles (thrust or thrust vector control F02K9/80) · CPC title