Applying sealant to narrow deep gaps in an ablative heat shield surface

• US 8,152,107 B1
• Filed: 02/19/2008
• Issued: 04/10/2012
• Est. Priority Date: 02/19/2008
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Toombs, Gordon R.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US12/033,739
• Time in Patent Office: 1,512 Days
• Field of Search: 244/159.1, 244/131, 244/132, 244/133, 156285-286, 222/566
• US Class Current: 244/159.1
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields

Abstract

A method of applying sealant to a narrow, deep gap in a surface includes covering the gap to form a covered channel, inserting a flared end of a dispensing nozzle into the covered gap at a first location, and applying a vacuum to the covered gap at a second location while using the nozzle to inject the sealant into the gap at the first location. This method may be used to seal gaps between ablative elements of a heat shield.

Claims

1. A method comprising:

assembling a plurality of ablative elements into a heat shield of a spacecraft, wherein the elements form long, narrow, deep gaps there between;

sealing the gaps between the ablative elements with a thixotropic sealant, wherein sealing a portion of the gap includes

applying tape to a surface of the heat shield to cover the gap portion;

inserting a flared end dispensing nozzle into the covered portion; and

applying a vacuum to the covered portion downstream of the flared end nozzle, the vacuum applied while using the nozzle to inject the sealant into the gap, the vacuum causing the sealant to flow through the covered gap portion, the vacuum also removing voids from the sealant in the gap.

2. The method of claim 1 wherein an extrusion gun is used to inject the sealant into the nozzle, whereby the sealant flows out of the flared end nozzle, into the gap.

3. The method of claim 1 wherein the gap has a nominal thickness of 0.080+−

0.020 inches.

4. The method of claim 1, wherein the dispensing nozzle is made of a shrink fit material, the method further comprising shrink-fitting a first end of the nozzle onto an extrusion gun and flattening the other end of the nozzle to form the flared end prior to inserting the flared end into the gap;

and using the extrusion gun to inject the sealant through the nozzle and into the gap.

5. The method of claim 4, wherein dispensing nozzle is made of a material having a shrink ratio of at least 2:

1.

6. The method of claim 1, wherein the gap is formed with a nominal thickness of 0.080+−

0.020 inches and a depth of about 4 inches.

7. A spacecraft comprising a heat shield manufactured according to the method of claim 1.

8. The method of claim 1, wherein using the nozzle includes using a sealant cartridge to inject the sealant into the nozzle, the nozzle including a nozzle body of thin wall shrink tubing material having first and second ends, the first end having been shrink fitted to a nozzle of the sealant cartridge, the second end having been flattened into a flared, elongated end.

9. The method of claim 1, wherein the vacuum and the flared end of the nozzle are spaced apart along a length of the gap portion.

10. The method of claim 1 wherein applying the tape from one side of the gap to an opposite side of the gap.