EP0279620A2
Expired / Lapsed
EP
⏱️ 0.0 years remaining
Aircraft shell module
Assignee: ATR International Inc
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Filing: 1988-02-16
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Granted: —
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Expires: 2008-02-16
Abstract
Abstract Starboard (30) and port (32) arcuate panel sections having a dampening layer (80) between two honeycomb layers (82) form a cocoon or module (10) which is mounted in multiple elastomeric isolators (38, 42, 72, 78) located within channel members (40, 44, 74, 79). Starboard support bracket (46), attached to the interior of the aircraft skin (12) supports the channel (44) adjacent deck (14). Port support bracket (90) supports channel (79). The module (10) is thereby spaced apart from the aircraft frame (12). There is a resulting diminution of acoustic transmission from the aircraft frame (12) to its interior passenger area (18).
Inventors
- 👤 David R. Humphries
- 👤 Donald C. Fetterhoff
- 👤 William R. Higgins
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-11-10 00:42
CPC Classifications
B; B64; B64C; B64C1/00; B64C1/06; B64C1/066; B64D; B64D11/00
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
138 words
A cocoon structure (10) for acoustical protection of passengers within the interior of an aircraft fuselage (12) containing a fuselage deck (14) characterized by: (a) a multiplicity of panels (30, 32) held together in abutting end to end relationship by one or more joiner arches (52, 54); (b) each panel having a port (32) and starboard (30) component with each component having first (34, 76) and second (36, 77) ends inserted into multiple isolators (38, 42, 72, 78); (c) each isolator (38, 42, 77, 78) engaged within a channel member (40, 44, 76, 79) attached to a mounting element (46, 50, 90) structurally affixed to an interior fuselage surface of the aircraft; and (d) one or more acoustical panels (88) covering the fuselage deck (14), the cocoon structure thereby being spaced apart from the fuselage of the aircraft.
Claim 2
Dependent Claim
138 words
A cocoon structure (10) for acoustical protection of passengers within the interior of an aircraft fuselage (12) containing a fuselage deck (14) characterized by: (a) a multiplicity of panels (30, 32) held together in abutting end to end relationship by one or more joiner arches (52, 54); (b) each panel having a port (32) and starboard (30) component with each component having first (34, 76) and second (36, 77) ends inserted into multiple isolators (38, 42, 72, 78); (c) each isolator (38, 42, 77, 78) engaged within a channel member (40, 44, 76, 79) attached to a mounting element (46, 50, 90) structurally affixed to an interior fuselage surface of the aircraft; and (d) one or more acoustical panels (88) covering the fuselage deck (14), the cocoon structure thereby being spaced apart from the fuselage of the aircraft.
Claim 3
Dependent Claim
22 words
A cocoon structure according to Claim 1 characterized by isolators (38, 42, 72, 78) containing an elastomeric cartilage of vibration absorbing material.
Claim 4
Dependent Claim
40 words
A cocoon structure according to Claim 1 or Claim 2 characterized by each port (32) and starboard (30) panel containing a central damping layer (80) between layers (82) of honeycomb material and outer layers of a structurally supportive material (84).
Claim 5
Dependent Claim
187 words
A cocoon structure according to Claim 1 for the interior of an aircraft fuselage containing a fuselage deck (14), characterized by: (a) contiguous pairs of arcuate port (32) and starboard (30) panels having a first (34, 76) and second end (36, 77); (b) the first (34, 36) end of each panel mounted in multiple isolators (38, 72) located within separate overhead support channels (40, 74); (c) multiple support brackets (46, 90) attached to a starboard and port side of the fuselage deck; (d) an adjustable port support channel (79) attached to the support bracket (90) on the port side of the fuselage deck; (e) an adjustable starboard support channel (44) attached to the support bracket (46) on the starboard side of the fuselage deck; (f) multiple isolators (42, 78) mounted in the starboard and port channels for receiving and holding the second end (36, 77) of each arcuate panel; and (g) the overhead support channels (40, 74) supported by an assembly attached to an overhead portion (28) of the fuselage (12), the arcuate panels (30, 32) thereby being spaced apart from the fuselage (12) of the aircraft.
Claim 6
Dependent Claim
23 words
A cocoon structure according to Claim 4 characterized by the isolators (38, 42, 72, 78) having an elastomeric cartilage of vibration absorbing material.
Claim 7
Dependent Claim
27 words
A cocoon structure according to Claim 4 or Claim 5 characterized by the fuselage deck (14) being covered by multiple panels (88) of a honeycomb material (82).
Claim 8
Dependent Claim
29 words
A cocoon structure according to Claim 4, 5, or 6 characterized by the panels (30, 32) containing a layer of damping material (80) between layers of honeycomb material (82).
Claim 9
Independent Claim
205 words
A method of mounting an aircraft interior module (10) within an aircraft fuselaage (12) containing a fuselage deck (14) characterized by: (a) mounting support beams (28) from an overhead interior surface of the fuselage (12); (b) attaching a mounting plate containing a port (74) and starboard (40) overhead channel member to the support beams (28) by multiple overhead brackets (50); (c) attaching a port (79) and starboard (44) deck channel member to a multiplicity of port (90) and starboard (46) mounting brackets respectively affixed to the fuselage deck (14); (d) mounting multiple isolator members (38, 42, 72, 78) in each channel member; (e) mounting a first end (34) of an arcuate starboard acoustical panel (30) in the isolators (38) in the starboard overhead channel member (40) and a second end (36) in the isolators (42) in the starboard deck channel member (44); (f) mounting a first end (76) of an arcuate port acoustical panel (32) in the isolators (72) in the port overhead channel member (74) and a second end (77) in the isolators (78) in the port deck channel member (79); (g) mounting flat deck acoustical panels (88) over the fuselage deck (14) to form a module spaced apart from the aircraft fuselage (12).
Claim 10
Independent Claim
205 words
A method of mounting an aircraft interior module (10) within an aircraft fuselaage (12) containing a fuselage deck (14) characterized by: (a) mounting support beams (28) from an overhead interior surface of the fuselage (12); (b) attaching a mounting plate containing a port (74) and starboard (40) overhead channel member to the support beams (28) by multiple overhead brackets (50); (c) attaching a port (79) and starboard (44) deck channel member to a multiplicity of port (90) and starboard (46) mounting brackets respectively affixed to the fuselage deck (14); (d) mounting multiple isolator members (38, 42, 72, 78) in each channel member; (e) mounting a first end (34) of an arcuate starboard acoustical panel (30) in the isolators (38) in the starboard overhead channel member (40) and a second end (36) in the isolators (42) in the starboard deck channel member (44); (f) mounting a first end (76) of an arcuate port acoustical panel (32) in the isolators (72) in the port overhead channel member (74) and a second end (77) in the isolators (78) in the port deck channel member (79); (g) mounting flat deck acoustical panels (88) over the fuselage deck (14) to form a module spaced apart from the aircraft fuselage (12).
Claim 11
Dependent Claim
41 words
The method according to Claim 8 characterized by joining adjacent panels (30, 32) together side to side by one or more joiner members (52, 54) to form a module (10) within substantially the entire interior space of the aircraft fuselage (12).
Claim 12
Dependent Claim
36 words
The method according to Claim 8 or Claim 9 characterized by mounting panels (30, 32) containing a central damping layer (80) between layers of honeycomb material (82) and outer layers of a structural supportive material (84).
References Cited (Backward Citations)
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