Aircraft thermal protection system

• US 5,560,569 A
• Filed: 04/06/1995
• Issued: 10/01/1996
• Est. Priority Date: 04/06/1995
• Status: Expired due to Fees

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Corporation (Martin Marietta Corporation)
• Inventors: Schmidt, Ronald P.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US08/418,104
• Time in Patent Office: 544 Days
• Field of Search: 89/36 A, 244/158 A, 244/117 R, 244/121, 244/117 A, 428/116, 428/117, 428/118, 52/573.1, 404/47, 404/49, 404/50, 404/74
• US Class Current: 244/117.00R
• CPC Class Codes: B64G 1/50 for temperature control
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields
• CPC Class Codes: Y10T 428/24149 Honeycomb-like
• CPC Class Codes: Y10T 428/24157 Filled honeycomb cells [e.g., solid substance in cavities, etc.]

Abstract

A method and apparatus are disclosed for providing an aircraft thermal protection system for hypersonic cruise and space launch vehicles. A flexible outer skin formed from a metal super alloy is designed to flex and accommodate thermal growth in the vehicle structure. The flexible super alloy skin is made from a plurality of hexagonal shaped cups which are welded together at the edges in a honeycomb type of array with thermal expansion gaps provided between the outermost surfaces of the hexagonal cups. Gap covers extend across the thermal expansion gaps to reduce aerodynamic drag. The flexible outer skin extends over hexagonal shaped, high temperature ceramic blocks, which provide both an insulation layer and support for the outer skin. The flexible outer skin distributes airloads across various ones of the rigid ceramic blocks. A strain isolation pad extends across the ends of the blocks, opposite the flexible outer skin, to absorb strains induced by thermal expansion of the ceramic blocks and the materials beneath. A closed cell foam sheeting extends adjacent to the strain isolation pads, opposite the ceramic blocks, to provide a moisture barrier for preventing liquid formation and freezing on cryogenic fuel tanks. A thin super alloy backing foil extends along the closed cell foam sheeting, opposite the strain isolation pads. The flexible outer skin is secured to the backing foil by super alloy rods.

Claims

1. An apparatus for preventing thermal transfer through an exterior of an aircraft, the apparatus comprising in combination:

a flexible outer skin formed from a plurality of metal cups having open ends which face inward toward an interior of the aircraft, and closed base ends which are smaller than the open ends and which face outward and away from the interior of the aircraft, sidewalls which are joined with the sidewalls of adjacent metal cups with the base ends spaced apart with thermal expansion gaps extending therebetween;

rigid insulation formed from a plurality of ceramic blocks which are spaced apart and have outer ends which extend into the open ends of the metal cups, wherein the flexible outer skin extends over the ceramic blocks and retains the ceramic blocks against the interior of the aircraft; and

an inner barrier extending across the inner ends of the blocks to block moisture transfer.

2. The apparatus according to claim 1, wherein:

the inner barrier includes a metal liner; and

fastening means extends between the metal liner and the metal cups to fasten the metal cups to the metal liner.

3. The apparatus according to claim 1, wherein:

the inner barrier includes a thermoplastic liner;

the inner barrier further includes metal liner disposed opposite the thermoplastic liner from the inner ends of the blocks; and

rods extend between the metal liner and the metal cups to fasten the metal cups to the metal liner.

4. The apparatus according to claim 1, wherein the sidewalls of the adjacent metal cups are joined at inner edges.

5. The apparatus according to claim 1, wherein the sidewalls of the adjacent metal cups are joined at inner edges, with the thermal expansion gaps extending between outer portions of the sidewalls and adjacent ones of the base ends of the metal cups.

6. The apparatus according to claim 1, wherein:

the sidewalls of the adjacent metal cups are joined at inner edges of the sidewalls, with the thermal expansion gaps extending between outer portions of the sidewalls and adjacent ones of the base ends of the metal cups; and

cover strips extend over the thermal expansion gaps, each cover strip welded to only one base of one cup to allow expansion and contraction of the thermal expansion gaps.

7. The apparatus according to claim 1, wherein the metal cups have at least five (5) sidewalls.

8. The apparatus according to claim 1, wherein the blocks have a greater thickness than the height of the sidewalls.

9. An apparatus for preventing thermal transfer through an exterior of an aircraft, the apparatus comprising in combination:

a plurality of metal cups having open ends which face inward toward an interior of the aircraft, closed base ends which are smaller than the open ends and which face outward and away from the interior of the aircraft, and each cup having at least five (5) sidewalls which are joined at inner edges with the sidewalls of adjacent metal cups, with outer portions of the sidewalls and the base ends spaced apart with thermal expansion gaps extending therebetween;

a plurality of rigid ceramic insulation blocks which are spaced apart and have outer ends which extend into the open ends of the metal cups, wherein metal cups extend over the outer ends of the blocks, and the blocks have a thickness which is greater than the height of the sidewalls for the metal cups;

a thermoplastic liner extending inward of and parallel to inner ends of the blocks;

a metal liner extending inward of the thermoplastic liner, and parallel to the inner ends of the blocks, for blocking moisture transfer; and

rods extending between the metal liner and the metal cups to fasten the metal cups to the metal liner.

10. The apparatus according to claim 9, wherein the rods are secured to the inner edges of the sidewalls of the metal cups.

11. The apparatus according to claim 9, further comprising:

cover strips extending over the thermal expansion gaps, each cover strip welded to only one base of one cup to allow expansion and contraction of the thermal expansion gaps.

12. The apparatus according to claim 9, wherein the inner edges of the sidewalls of the adjacent metal cups are joined by welding.

13. The apparatus according to claim 9, wherein at least a portion of the inner edges of the sidewalls of the adjacent metal cups are sealed by brazing.

14. The apparatus according to claim 9, further comprising:

an elastomeric pad extending between the inner ends of the blocks and the thermoplastic liner for absorbing and distributing strain which result from thermal expansion.

15. The apparatus according to claim 9, wherein thermoplastic liner comprises a closed cell foam pad.

16. An apparatus for preventing thermal transfer through an exterior of an aircraft, the apparatus comprising in combination:

a plurality of metal cups having open ends which face inward toward an interior of the aircraft, closed base ends which are smaller than the open ends and which face outward and away from the interior of the aircraft, and each cup having at least five (5) sidewalls which are joined at inner edges with the sidewalls of adjacent metal cups with outer portions of the sidewalls and the base ends spaced apart with thermal expansion gaps extending therebetween;

a plurality of rigid ceramic insulation blocks which are spaced apart and have outer ends which extend into the open ends of the metal cups, wherein metal cups extend over the outer ends of the blocks, and the blocks have a thickness which is greater than the height of the sidewalls for the metal cups;

a thermoplastic liner extending inward of and parallel to the inner ends of the blocks;

a metal liner extending inward of the thermoplastic liner, and parallel to the inner ends of the blocks for blocking moisture transfer;

rods extending between the metal cups and the metal liner and having outer ends which are secured to the inner edges of the metal cups, and to the metal liner to fasten the metal cups to the metal liner; and

cover strips extending over the thermal expansion gaps, each cover strip welded to only one base of one cup to allow expansion and contraction of the thermal expansion gaps.

17. The apparatus according to claim 16, wherein:

at least a portion of the inner edges of the sidewalls of the adjacent metal cups are joined by welding.

18. The apparatus according to claim 16, further comprising:

an elastomeric pad extending between the inner ends of the blocks and the thermoplastic liner for absorbing and distributing strain which result from thermal expansion; and

wherein thermoplastic liner comprises a closed cell foam pad.