High temperature thermal protection system for rockets, and associated methods

Patent metadata

Field	Value
Publication number	US-11174818-B2
Application number	US-201916409195-A
Country	US
Kind code	B2
Filing date	May 10, 2019
Priority date	May 10, 2018
Publication date	Nov 16, 2021
Grant date	Nov 16, 2021

Abstract

A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and/or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and/or cooling effects.

First claim

We claim:

1. An aerospace system comprising:
a launch vehicle configured to move in a first direction;
a propulsion system carried by the launch vehicle, the propulsion system comprising a nozzle; and
a thermal protection apparatus positioned around an exterior surface of the nozzle, the thermal protection apparatus comprising:
an outer fabric layer that comprises metal alloy fibers woven together such that the outer fabric layer has an angle-interlock architecture;
a layer of insulation positioned adjacent to the outer fabric layer and that comprises ceramic fibers, wherein the layer of insulation is configured to be at least partially saturated with water;
waterproofing applied to an edge of the thermal protection apparatus, wherein the waterproofing contacts the outer fabric layer and the layer of insulation; and
a plurality of threads formed with the metal alloy fibers and that project through the outer fabric layer and the layer of insulation to attach the outer fabric layer to the layer of insulation, wherein—
the plurality of threads are arranged only in columns that are oriented in the first direction.

2. The aerospace system of claim 1 , wherein—
the thermal protection apparatus includes an inner fabric layer positioned adjacent to the layer of insulation such that the layer of insulation is positioned between the inner and outer layers of fabric, and
the plurality of threads project through the inner fabric layer.

3. The aerospace system of claim 1 , further comprising a water distribution system positioned to deliver water to the layer of insulation.

4. The aerospace system of claim 1 , wherein adjacent columns are separated from each other by a distance between 0.125 and 0.5 inches.

5. The aerospace system of claim 4 , wherein the distance comprises a first distance, the rows are perpendicular to the columns, and adjacent rows are separated from each other by a second distance greater than the first distance.

6. The aerospace system of claim 5 , wherein the second distance is greater than 1 inch.

7. An aerospace system, comprising:
a launch vehicle;
a propulsion system carried by the launch vehicle, the propulsion system comprising a nozzle; and
a thermal protection apparatus positioned around an exterior surface of the nozzle, the thermal protection apparatus including:
an outer fabric layer that comprises a first fabric;
an inner fabric layer that comprises a second fabric different from the first fabric;
a layer of insulation interposed between the inner and outer fabric layers and formed from ceramic fibers, wherein the layer of insulation is configured to be at least partially saturated with water;
a plurality of threads stitching the outer fabric layer, the inner fabric layer, and the layer of insulation together; and

waterproofing applied to an edge of the thermal protection apparatus, wherein the waterproofing contacts the outer fabric layer and the inner fabric layer.

8. The aerospace system of claim 7 wherein the launch vehicle has a body and wherein the system further comprises an additional thermal protection apparatus on the body.

9. The aerospace system of claim 7 wherein the launch vehicle includes a water vessel and wherein the thermal protection apparatus is coupled to the water vessel with a water conduit positioned to deliver water from the water vessel to the layer of insulation.

10. The aerospace system of claim 7 wherein—
the outer fabric layer comprises two layers of weft fibers woven together,
the plurality of threads are arranged in columns that align with the vehicle axis, and
adjacent columns are separated from each other by a distance between 0.125 and 0.5 inches.

11. The aerospace system of claim 7 wherein each of the plurality of threads comprises:
a plurality of surface portions positioned on the outer fabric layer;
a plurality of connecting portions that project through the outer fabric layer, the layer of insulation, and the inner fabric layer, wherein each of the connecting portions is coupled between two of the plurality of surface portions.

12. An aerospace system, comprising:
a launch vehicle comprising a first end and a second end opposite the first end, wherein the launch vehicle includes a vehicle axis that extends between the first and second opposite ends;
a propulsion system carried by the launch vehicle and comprising at least one nozzle positioned at the second end of the launch vehicle and configured to direct exhaust products away from the second end to generate thrust; and
a flexible thermal protection apparatus positioned around an exterior surface of the nozzle to insulate the nozzle, the thermal protection apparatus comprising:
an outer fabric layer that forms an outer surface of the thermal protection apparatus, wherein the outer fabric comprises metal alloy fibers woven together;
an inner fabric layer that forms an inner surface of the thermal protection apparatus, wherein the inner surface faces towards the exterior surface of the nozzle;
a layer of insulation between the inner and outer fabric layers, wherein the layer of insulation is configured to be at least partially saturated with water;

waterproofing applied to an edge of the thermal protection apparatus, wherein the waterproofing contacts the outer fabric layer and the inner fabric layer; and
a plurality of threads that stitch the outer fabric layer to the layer of insulation and the inner fabric layer, wherein—
the plurality of threads are arranged only in columns that align with the vehicle axis or in columns and rows such that the number density of the columns is greater than the number density of the rows.

13. The aerospace system of claim 12 wherein individual threads comprise:
a plurality of surface portions positioned on the outer surface; and
a plurality of connecting portions that project through the outer fabric layer, the layer of insulation, and the inner fabric layer, wherein each of the connecting portions is coupled between two of the plurality of surface portions and extends between the outer and inner surfaces.

14. The aerospace system of claim 13 , wherein the plurality of threads comprises a first plurality of threads, the flexible thermal protection apparatus further comprising:
a second plurality of threads positioned on the inner surface, wherein individual of the plurality of connecting portions overlaps with one of the second plurality of threads.

15. The aerospace system of claim 1 wherein the rows are perpendicular to the columns and to the vehicle axis.

16. The aerospace system of claim 15 wherein adjacent columns are separated from each other by a first distance and wherein adjacent rows are separated from each other by a second distance greater than the first distance.

17. The aerospace system of claim 15 wherein the metal alloy fibers comprise a nickel-chromium alloy.

18. The aerospace system of claim 12 , comprising:
an adhesive layer between the inner surface of the thermal protection apparatus and the exterior surface of the nozzle, wherein the adhesive layer couples the thermal protection apparatus to the nozzle.

19. The aerospace system of claim 12 wherein the metal alloy fibers are woven together such that the outer fabric layer has an angle-interlock architecture.

20. The aerospace system of claim 12 wherein the threads comprise the metal alloy fibers.

Assignees

• Blue Origin Llc

Inventors

• Norman Adam Keith
• Brendel John Paul
• Hupf Christopher Patrick
• Gulli Stefano

Classifications

• F02K9/97

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

• B32B2605/18

  Aircraft · CPC title

• B32B7/09

  by stitching, needling or sewing (by {mechanically connecting} fibrous layers {to another layer} B32B5/06) · CPC title

• B64G1/58

  Thermal protection, e.g. heat shields · CPC title

• B64G1/226

  Special coatings for spacecraft · CPC title