Protective sleeves for fire and overheat detection systems for aircraft applications

Patent metadata

Field	Value
Publication number	US-11846548-B2
Application number	US-202117202605-A
Country	US
Kind code	B2
Filing date	Mar 16, 2021
Priority date	Mar 16, 2021
Publication date	Dec 19, 2023
Grant date	Dec 19, 2023

Abstract

Aircraft fire and overheat detection systems are described. The systems include a support bracket configured to secure the system to a component of an aircraft. A terminal assembly is fixedly connected to the support bracket and includes a connection assembly and a connection cable. A sensing element is electrically connected to the terminal assembly and arranged to detect at least one of fire and heat associated with the component of the aircraft. A protective sleeve is arranged about the connection assembly and connection cable. The sleeve has a lug portion at a first end with a sealing protrusion extending radially inward, a first wire portion, and a second wire portion, with progressively smaller diameters for each portion.

First claim

What is claimed is:

1. An aircraft fire and overheat detection system, comprising:
a support bracket configured to secure the aircraft fire and overheat detection system to a component of an aircraft;
a terminal assembly fixedly connected to the support bracket, the terminal assembly comprising a connection assembly and a connection cable;
a sensing element electrically connected to the terminal assembly and arranged to detect at least one of fire and heat associated with the component of the aircraft, wherein the connection cable is electrically connected to the sensing element to enable detection of an electrical resistance in the sensing element; and
a protective sleeve arranged about the connection assembly and connection cable, the protective sleeve comprising a first end having an opening and a second end having an opening and an interior bore extending between the openings at the first and second ends, wherein:
a lug portion is arranged at the first end and includes a sealing protrusion extending radially inward within the interior bore, the lug portion having a first diameter,
a first wire portion having a second diameter that is less than the first diameter and extending toward the second end, and
a second wire portion arranged at the second end, the second wire portion having a third diameter that is less than the second diameter.

2. The aircraft fire and overheat detection system of claim 1 , wherein the protective sleeve is made from at least one of polyolefin, fluoropolymer, polyvinyl chloride (PVC), polychloroprene (neoprene), and silicone elastomer.

3. The aircraft fire and overheat detection system of claim 1 , further comprising an adhesive sealant applied to a surface of the interior bore.

4. The aircraft fire and overheat detection system of claim 3 , wherein the adhesive sealant is applied at least to the first wire portion.

5. The aircraft fire and overheat detection system of claim 3 , wherein the adhesive sealant is applied at least to the second wire portion.

6. The aircraft fire and overheat detection system of claim 3 , wherein the adhesive sealant is at least one of hot-melt, silicone, elastomer, and epoxy.

7. The aircraft fire and overheat detection system of claim 1 , wherein the terminal assembly includes a mounting nut threaded onto a threaded barrel and a mounting head wherein a portion of the support bracket is secured between the mounting nut and the mounting head.

8. The aircraft fire and overheat detection system of claim 7 , wherein the sealing protrusion sealingly engages between the threaded nut and the portion of the support bracket.

9. The aircraft fire and overheat detection system of claim 1 , wherein the third diameter is less than an external diameter of the connection cable.

10. The aircraft fire and overheat detection system of claim 1 , wherein the second diameter is substantially equal to an external diameter of the connection cable.

11. The aircraft fire and overheat detection system of claim 1 , wherein the protective sleeve comprises a first transition portion defining a tapering diameter between the lug portion and the first wire portion.

12. The aircraft fire and overheat detection system of claim 1 , wherein the protective sleeve comprises a second transition portion defining a tapering diameter between the first wire portion and the second wire portion.

13. An aircraft comprising:
a fire-protected space; and
an aircraft fire and overheat detection system, comprising:
a support bracket configured to secure the aircraft fire and overheat detection system within the fire-protected space;
a terminal assembly fixedly connected to the support bracket, the terminal assembly comprising a connection assembly and a connection cable;
a sensing element electrically connected to the terminal assembly and arranged to detect at least one of fire and heat associated with the component of the aircraft, wherein the connection cable is electrically connected to the sensing element to enable detection of an electrical resistance in the sensing element; and
a protective sleeve arranged about the connection assembly and connection cable, the protective sleeve comprising a first end having an opening and a second end having an opening and an interior bore extending between the openings at the first and second ends, wherein:
a lug portion is arranged at the first end and includes a sealing protrusion extending radially inward within the interior bore, the lug portion having a first diameter,
a first wire portion having a second diameter that is less than the first diameter and extending toward the second end, and
a second wire portion arranged at the second end, the second wire portion having a third diameter that is less than the second diameter.

14. The aircraft of claim 13 , wherein the fire protected space is located within a portion of an engine of the aircraft.

15. The aircraft of claim 13 , wherein the protective sleeve is made from at least one of polyolefin, fluoropolymer, polyvinyl chloride (PVC), polychloroprene (neoprene), and silicone elastomer.

16. The aircraft of claim 13 , further comprising an adhesive sealant applied to a surface of the interior bore.

17. The aircraft of claim 13 , wherein the terminal assembly includes a mounting nut threaded onto a threaded barrel and a mounting head wherein a portion of the support bracket is secured between the mounting nut and the mounting head.

18. The aircraft of claim 13 , wherein the third diameter is less than an external diameter of the connection cable.

19. The aircraft of claim 13 , wherein the second diameter is substantially equal to an external diameter of the connection cable.

20. The aircraft of claim 13 , wherein the protective sleeve comprises a first transition portion defining a tapering diameter between the lug portion and the first wire portion and a second transition portion defining a tapering diameter between the first wire portion and the second wire portion.

Assignees

• Kidde Tech Inc

Inventors

• Newlin Scott Kenneth
• Wallace Steven
• Rouse Albert Chad

Classifications

• G01K1/12 Primary

  for preventing damage due to heat overloading · CPC title

• A62C37/36

  an actuating signal being generated by a sensor separate from an outlet device · CPC title

• A62C3/08

  in aircraft {(A62C3/0207 takes precedence)} · CPC title

• G01D11/245

  Housings for sensors · CPC title

• G01K1/08 Primary

  Protective devices, e.g. casings · CPC title