Tube support structure for aircraft

Patent metadata

Field	Value
Publication number	US-9447899-B2
Application number	US-201113877952-A
Country	US
Kind code	B2
Filing date	Oct 21, 2011
Priority date	Oct 26, 2010
Publication date	Sep 20, 2016
Grant date	Sep 20, 2016

Abstract

A tube support structure for an aircraft includes: a parallel movement mechanism configured to support the tube movably in parallel; and an angle adjustment mechanism configured to support the tube angle-adjustably. The parallel movement mechanism includes: an eccentric sleeve, through which the tube passes, configured to adjust a position of the tube in a Z direction perpendicular to the X direction, and a Y direction adjustment mechanism configured to adjust a position of the eccentric sleeve in a Y direction perpendicular to the X direction and the Z direction. The angle adjustment mechanism includes: a first member configured to have a first curved surface and support the tube, and a second member configured to have a second curved surface with a shape corresponding to the first curved surface, have contact slidably with the first curved surface at the second curved surface, and support the first member by the second curved surface. Each of the first curved surface and the second curved surface is formed such that a cross-sectional shape in an XZ plane is a circular arc shape, and an angle of the tube is adjusted by sliding the first curved surface with respect to the second curved surface. Thus, a tube support structure for aircraft, which can suppress a preload, is provided.

First claim

The invention claimed is:

1. A tube support structure for an aircraft, which supports a tube arranged to extend in an X direction inside an aircraft, the tube support structure comprising:
a parallel movement mechanism configured to support the tube and allow parallel movement of the tube; and
an angle adjustment mechanism configured to support the tube and allow an angle of the tube to be adjusted;
wherein the parallel movement mechanism includes:
an eccentric sleeve, through which the tube passes, configured to adjust a position of the tube in a Z direction perpendicular to the X direction, and
a Y direction adjustment mechanism configured to adjust a position of the eccentric sleeve in a Y direction perpendicular to the X direction and the Z direction,
wherein the angle adjustment mechanism includes:
a first member configured to have a first curved surface and support the tube, and
a second member configured to have a second curved surface with a shape corresponding to the first curved surface, have contact slidably with the first curved surface at the second curved surface, and support the first member by the second curved surface,
wherein each of the first curved surface and the second curved surface is formed such that a cross-sectional shape in an XZ plane is a circular arc shape,
wherein the angle of the tube is adjusted by sliding the first curved surface with respect to the second curved surface,
wherein the second member is joined to a structure body fixed to an airframe,
wherein the Y direction adjustment mechanism is configured to shift a position of the second member with respect to the structure body in the Y direction, and
wherein each of the first curved surface and the second curved surface has a shape that corresponds to a portion of an outer circumference surface of an imaginary cylinder with a central axis in the Y direction, the portion extending along the Y direction.

2. The tube support structure for an aircraft according to claim 1 ,
wherein the tube is supported so as to have contact with an inner circumference surface of the eccentric sleeve, and
wherein the first member is configured so as to have contact with the eccentric sleeve and support the tube through the eccentric sleeve.

3. The tube support structure for an aircraft according to claim 2 ,
wherein the first member includes a saddle configured to support the eccentric sleeve so as to have contact with an outer circumference surface of the eccentric sleeve,
wherein the first curved surface is formed in the saddle,
wherein the second member includes a bracket configured to support the saddle,
wherein the bracket includes an attachment portion and a fixing portion, and is bent between the attachment portion and the fixing portion,
wherein the second curved surface is formed in the attachment portion,
wherein the fixing portion is arranged so as to overlap with the structure body and is joined to the structure body.

4. The tube support structure for an aircraft according to claim 3 ,
wherein the Y direction adjustment mechanism has an elongate hole which is provided in the fixing portion and is extended along the Y direction,
wherein the fixing portion is fastened to the structure body by a fastening member penetrating to the elongate hole, and
wherein a length of the elongate hole is longer than a width of an axial portion of the fastening member in the Y direction.

5. An aircraft comprising:
the tube support structure for an aircraft according to claim 1 ;
a main wing; and
a tube supported by the tube support structure and disposed inside the main wing.

6. The aircraft according to claim 5 , wherein the main wing is made of CFRP (Carbon Fiber Reinforced Plastic).

Assignees

• Minami Keisuke
• Mitsubishi Heavy Ind Ltd

Inventors

• Minami Keisuke

Classifications

• Y02T50/40

  Weight reduction · CPC title

• F16L5/025

  the pipe being movable (F16L5/10 takes precedence) · CPC title

• F16L3/16

  with special provision allowing movement of the pipe (F16L3/01 takes precedence; supporting pipes or cables inside other pipes or sleeves F16L7/00) · CPC title

• F16L3/1091

  with two members, the two members being fixed to each other with fastening members on each side · CPC title

• F16L3/1222 Primary

  the member having the form of a closed ring, e.g. used for the function of two adjacent pipe sections · CPC title