Support system having a crown integration panel (CIP)

Patent metadata

Field	Value
Publication number	US-9758233-B2
Application number	US-201514840225-A
Country	US
Kind code	B2
Filing date	Aug 31, 2015
Priority date	Aug 31, 2015
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

A support system for a crown area of an aircraft and a corresponding method is disclosed. The support system includes a crown integration panel (CIP). The CIP is configured to provide a mounting surface for a plurality of aircraft equipment and to provide an electrical ground for at least one of the aircraft equipment of the plurality of aircraft equipment. The system further includes a first attachment and a second attachment attached to the CIP. The first attachment and the second attachment are configured to attach to an airframe of the aircraft. The system further includes a crown raceway support (CRS) having a first end and a second end, where the first end is attached to a first end of the CIP and the second end is configured to attach to an outboard rail of the aircraft.

First claim

We claim:

1. A support system for a crown area of an aircraft, the system comprising:
a crown integration panel (CIP) comprising a honeycomb panel and sheet metal, wherein the CIP is configured to provide a mounting surface for a plurality of aircraft equipment and to provide an electrical ground for at least one of the aircraft equipment of the plurality of aircraft equipment;
a first attachment and a second attachment attached to the CIP, wherein the first attachment and the second attachment are configured to attach to an airframe of the aircraft and to provide support for the CIP; and
a crown raceway support (CRS) having a first end and a second end, wherein the first end of the CRS is attached to a first end of the CIP, and wherein the second end of the CRS is configured to attach to an outboard rail of the aircraft.

2. The support system of claim 1 , wherein the first attachment and the second attachment are attached to the airframe, and wherein the first attachment and the second attachment are the only attachments directly attaching the first end of the CIP to the airframe.

3. The support system of claim 1 , wherein the first attachment and the second attachment are configured to allow the CIP freedom to move with body deflections of the airframe.

4. The support system of claim 1 , further comprising a lateral support arm, wherein the lateral support arm is connected to a second end of the CIP and the outboard rail.

5. The support system of claim 4 , wherein the lateral support arm is configured to receive a plurality of ceiling support brackets.

6. The support system of claim 1 , wherein the CRS comprises a plurality of attachments and a support rod, the support rod configured to hold at least one wire.

7. The support system of claim 1 , wherein the sheet metal comprises a first metal face sheet and a second metal face sheet, and wherein the honeycomb panel is disposed between the first metal face sheet and the second metal face sheet.

8. The support system of claim 7 , wherein the first metal face sheet and the second metal face sheet increase the vibrational stiffness of the honeycomb panel and provide the electrical ground for the at least one of the plurality of aircraft equipment.

9. The support system of claim 1 , wherein the CIP comprises a plurality of wire pass-through holes and a plurality of equipment-attachment holes.

10. The support system of claim 9 , wherein the sheet metal comprises a first metal face sheet and a second metal face sheet, and wherein (i) the thickness of the honeycomb panel, the first metal face sheet, and the second metal face sheet and (ii) the number and location of the plurality of wire pass-through holes and the plurality of equipment-attachment holes are selected such that the CIP has a vibrational stiffness resulting in a natural resonance frequency of at least 14 hertz (Hz).

11. The support system of claim 1 , wherein the plurality of aircraft equipment comprises equipment selected from the group consisting of electrical equipment, wires, an environmental control system (ECS) duct, an oxygen line, a water line, and a power feeder.

12. A system comprising:
a plurality of support systems for a crown area of an aircraft, wherein each support system comprises:
(i) a crown integration panel (CIP) comprising a honeycomb panel and sheet metal, wherein the CIP is configured to provide a mounting surface for a plurality of aircraft equipment and to provide a ground for at least one of the aircraft equipment of the plurality of aircraft equipment;
(ii) a first attachment and a second attachment attached to the CIP, wherein the first attachment and the second attachment are configured to attach to an airframe of the aircraft and to provide support for the CIP; and
(iii) a crown raceway support (CRS) having a first end and a second end, wherein the first end of the CRS is attached to a first end of the CIP, and wherein the second end of the CRS is configured to attach to an outboard rail of the aircraft;

the plurality of the aircraft equipment attached to each support system, wherein the plurality of the aircraft equipment attached to each support system comprises at least some equipment that is attached to more than one of the plurality of the support systems.

13. The system of claim 12 , further comprising a plurality of connecting straps, wherein each support system is connected to at least one other support system by a respective connecting strap.

14. The system of claim 12 , wherein the plurality of aircraft equipment comprises equipment selected from the group consisting of electrical equipment, wires, an environmental control system (ECS) duct, an oxygen line, a water line, and a power feeder.

15. The system of claim 12 , wherein the at least some equipment that is attached to more than one of the plurality of the support systems is selected from the group consisting of wires, an environmental control system (ECS) duct, an oxygen line, and a water line.

16. A method comprising:
(i) providing a plurality of support systems for a crown area of an aircraft, wherein each support system comprises:
(a) a crown integration panel (CIP) comprising a honeycomb panel and sheet metal, wherein the CIP is configured to provide a mounting surface for a plurality of aircraft equipment and to provide a ground for at least one of the aircraft equipment of the plurality of aircraft equipment;
(b) a first attachment and a second attachment attached to the CIP, wherein the first attachment and the second attachment are configured to attach to an airframe of the aircraft and to provide vertical and lateral support for the CIP; and
(c) a crown raceway support (CRS) having a first end and a second end, wherein the first end of the CRS is attached to a first end of the CIP, and wherein the second end of the CRS is configured to attach to an outboard rail of the aircraft; and

(ii) prior to attaching the plurality of support systems to the airframe of the aircraft, (a) attaching, to each support system, the plurality of the aircraft equipment and (b) assembling together the plurality of support systems.

17. The method of claim 16 , wherein attaching, to each support system, the plurality of the aircraft equipment and assembling together the plurality of support systems takes place outside of the airframe of the aircraft.

18. The method of claim 16 , wherein the plurality of aircraft equipment comprises equipment selected from the group consisting of electrical equipment, wires, and environmental control system (ECS) duct, an oxygen line, a water line, and a power feeder.

19. The method of claim 16 , wherein attaching, to each support system, the plurality of the aircraft equipment comprises attaching at least one wire or line that extends from at least one support system to at least one other support system.

20. The method of claim 16 , further comprising:
attaching, to the airframe of the aircraft, the assembled plurality of the support systems having the attached plurality of aircraft equipment.

Assignees

• Boeing Co

Inventors

• King Timothy Todd
• Ackerman Douglas R
• Lora Gil-Antonio
• Davis Kenneth G
• Nadvornick Mark J
• Altmyer Brett N
• Mullins Jason W
• Steele Christopher J
• Thomas Matthew R
• Parrish Cynthia T
• Mccune James R

Classifications

• B64D11/00

  Passenger or crew accommodation; Flight-deck installations not otherwise provided for · CPC title

• B64C1/066 Primary

  Interior liners · CPC title

• B64F5/40

  Maintaining or repairing aircraft · CPC title

• B64D11/003

  Stowage devices for passengers' personal luggage · CPC title

• B64F5/0009

  Operations & Transport · mapped topic