Resin transfer molded rocket motor nozzle with adaptive geometry

Patent metadata

Field	Value
Publication number	US-11028803-B2
Application number	US-201816126225-A
Country	US
Kind code	B2
Filing date	Sep 10, 2018
Priority date	Sep 10, 2018
Publication date	Jun 8, 2021
Grant date	Jun 8, 2021

Abstract

A rocket motor has a nozzle that is reconfigurable by erosion or ablation of the material around the throat of the nozzle. The nozzle throat has layers of materials with different erosion characteristics, with the erosion occurring so as to achieve the desired nozzle characteristics (configurations) during different parts of the fuel burn. The nozzle throat includes relatively-high-erosion material layers and relatively-low-erosion material layers, with some layers of the throat resisting erosion, while other of the layers erode or ablate relatively quickly. The relatively-low-erosion material layers may act as thermal barriers to fix the throat at relatively stable geometry for long periods of time, such as during most of the burn of different fuel segments, with the relatively-high-erosion material layers allowing rapid transition of the throat from one geometry to the next. The layers may be made by resin transfer molding (RTM).

First claim

What is claimed is:

1. A rocket motor nozzle comprising:
a pair of relatively-low-erosion material layers; and
a relatively-high-erosion material layer sandwiched between the relatively-low-erosion material layers;
wherein each of the pair of relatively-low-erosion material layers and the relatively-high-erosion material layer include resin-transfer molded materials;
wherein the resin transfer molded material of the pair of relatively-low-erosion material layers and the resin transfer molded material of the relatively-high-erosion material layer are different materials;
wherein the relatively-high-erosion material layer k made of a relatively-high-erosion material that erodes more quickly when exposed to flow through the nozzle than does a relatively-low-erosion material or materials of the relatively-low-erosion material layers; and
wherein the relatively-low-erosion material layers include:
an inner relatively-low-erosion material layer that radially inwardly overlaps the relatively-high-erosion material layer; and
an outer relatively-low-erosion material layer that radially outwardly overlaps the relatively-high-erosion material layer.

2. The rocket motor nozzle of claim 1 ,
wherein the relatively-low-erosion material or materials includes fibers; and
wherein the relatively-high-erosion material is fiberless.

3. The rocket motor nozzle of claim 1 ,
wherein the relatively-low-erosion material or materials includes fibers; and
wherein the relatively-high-erosion material includes fibers of a different material than the fibers of the relatively-low-erosion material or materials.

4. The rocket motor nozzle of claim 1 , wherein the relatively-low-erosion material layers include the same material.

5. The rocket motor nozzle of claim 1 ,
wherein the relatively-high-erosion material layer is an inner relatively-high-erosion material layer; and
further comprising an outer relatively-high-erosion material layer that is radially outward of the inner relatively-high-erosion material layer, and is radially outward of the relatively-low-erosion material layers.

6. The rocket motor nozzle of claim 1 , in combination with fuel, as a part of a rocket motor.

7. The combination of claim 6 , wherein the fuel is a solid fuel.

8. The combination of claim 7 , wherein the solid fuel is in multiple segments.

9. The combination of claim 6 ,
wherein the motor is configured to burn the fuel in multiple pulses; and
wherein the nozzle is configured such that during most of a first pulse of the multiple pulses the inner relatively-low-erosion material layer defines a channel of the nozzle through which combustion gasses pass, and such that during most of a second pulse of the multiple pulses the outer relatively-low-erosion material layer defines the channel of the nozzle.

10. A rocket motor comprising:
a first fuel portion;
a second fuel portion; and
a nozzle operatively coupled to the fuel portions, with hot gasses produced by burning of the fuel portions passing through the nozzle;
wherein the nozzle includes:
a pair of relatively-low-erosion material layers; and
a relatively-high-erosion material layer sandwiched between the relatively-low-erosion material layers;

wherein each of the pair of relatively-low-erosion material layers and the relatively-high-erosion material layer include resin-transfer molded materials;
wherein the resin transfer molded material of the pair of relatively-low-erosion material layers and the resin transfer molded material of the relatively-high-erosion material layer are different materials;
wherein the relatively-high-erosion material layer is made of a material that erodes more quickly when exposed to flow through the nozzle than does a material or materials of the relatively-low-erosion material layers; and
wherein the relatively-low-erosion material layers include:
an inner relatively-low-erosion material layer that radially inwardly overlaps the relatively-high-erosion material layer; and
an outer relatively-low-erosion material layer that radially outwardly overlaps the relatively-high-erosion material layer.

11. The rocket motor of claim 10 , wherein the fuel portions are parts of a single solid fuel segment.

12. The rocket motor of claim 10 ,
wherein the portions are separate fuel segments, with the first fuel portion being a first fuel segment and the second fuel portion being a second fuel segment; and
wherein the first fuel segment and the second fuel segment are configured to be burned sequentially, with the first fuel segment burned before the second fuel segment.

13. The rocket motor of claim 12 , wherein there is no non-fuel-burning time between the burning of the first fuel segment and the burning of the second fuel segment.

14. The rocket motor of claim 10 , wherein the nozzle is configured such that during most of burning of the first fuel portion the inner relatively-low-erosion material layer defines a channel of the nozzle through which combustion gasses pass, and such that most of burning of the second fuel portion of the multiple pulses the outer relatively-low-erosion material layer defines the channel of the nozzle.

15. A method of operating a rocket motor, the method comprising:
burning a first portion of fuel of the motor, with a nozzle of the motor in a first configuration, with a channel in the nozzle defined by an inner relatively-low-erosion material layer of the nozzle, with the inner relatively-low-erosion material layer eroding during the burning of the first portion;
after the burning of at least most of the first portion, and after the inner relatively-low-erosion material layer eroding to expose a relatively-high-erosion material layer that initially underlies the inner relatively-low-erosion material layer, transforming the nozzle from the first configuration to a second configuration by eroding the relatively-high-erosion material layer to expose an outer relatively-low-erosion material layer that initially underlies the relatively-high-erosion material layer; and
after the transforming, burning a second portion of the fuel, with the nozzle in the second configuration;
wherein each of the inner relatively-low-erosion material layer, the relatively-high-erosion material layer and the outer relatively-low-erosion material layer include resin-transfer molded materials;
wherein the resin transfer molded material of the pair of relatively-low-erosion material layers and the resin transfer molded material of the relatively-high-erosion material layer are different materials.

16. The method of claim 15 , wherein the burning of the second fuel portion follows immediately continuously the burning of the first fuel portion.

17. The method of claim 15 , wherein the eroding the relatively-high-erosion material layer to expose the outer relatively-low-erosion material layer occurs at least in part during the burning of the first portion.

18. The method of claim 15 , wherein the eroding the relatively-high-erosion material layer to expose the outer relatively-low-erosion material layer occurs at least in part during the burning of the second portion.

19. The method of claim 15 , wherein the burning of the first portion produces a different thrust than the burning of the second portion.

Assignees

• Raytheon Co

Inventors

• Summers Matt H
• Case David M
• Raymond Iv John J
• Fowler Gray
• Langhenry Mark T

Classifications

• F02K9/86

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

• B29C70/44

  using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding · CPC title

• F02K9/974 Primary

  Nozzle- linings; Ablative coatings · CPC title

• F05D2300/506

  Hardness · CPC title

• F05D2230/31

  Layer deposition · CPC title