Aircraft assembly
View Patent ↗An aircraft assembly having a bush mounted within a lug and a recess which extends along a portion of the lug-bush interface to create a relatively wide cavity for receiving sealant.
1. An aircraft assembly comprising:
a lug comprising a side wall and a lug bore extending therethrough;
a bush mounted within the lug, comprising:
a generally cylindrical body portion secured within the lug bore and having a bush bore extending therethrough defining a bearing face configured to rotatably support a shaft; and
a radial flange extending outwardly from one end of the cylindrical body portion and secured against the lug side wall;
a first lug-bush interface defined between adjacent faces of the lug side wall and the radial flange, comprising a first recess defined by a generally annular groove formed into one or both of the lug and the bush, the first recess extending from a first end of the lug-bush interface where a radial outer surface of the flange is adjacent to the lug side wall into and along a portion of the lug-bush interface to define a first cantilevered end portion of the bush at the flange such that sealant may be applied in the first recess between the cantilevered portion and the lug to provide a moisture tight seal between the lug and bush; and
a second lug-bush interface defined between adjacent faces of the lug bore and the cylindrical body portion, comprising a second recess defined by a generally annular groove formed into one or both of the lug and the bush, the second recess extending from a first end of the lug-bush interface wherein an axial outer surface of the cylindrical body portion is adjacent to the lug bore into and along a portion of the lug-bush interface to define a second cantilevered end portion of the bush at the cylindrical body portion such that sealant may be applied in the second recess between the cantilevered portion and the lug to provide a moisture tight seal between the lug and bush.
2. An aircraft assembly according to claim 1 , wherein the first cantilevered portion of the bush includes a chamfer or groove on the opposite side of the cantilevered portion with respect to the first recess.
3. An aircraft assembly according to claim 1 , wherein the second cantilevered portion of the bush includes a chamfer or groove on the opposite side of the second cantilevered portion with respect to the second recess.
4. An aircraft assembly according to claim 1 , wherein one or more internal edges and/or corners of the first recess defining the groove are arcuate.
5. An aircraft assembly according to claim 1 , wherein the first recess is partially or completely filled with sealant.
6. An aircraft assembly according to claim 1 , wherein the aircraft assembly is arranged to define at least part of an aircraft strut, brace, stay or actuator joint.
7. An aircraft assembly according to claim 1 , wherein the bush is unitary in nature so as to be formed from a single piece of material.
8. An aircraft assembly according to claim 1 , wherein the bush comprises:
the generally cylindrical body and radial flange being integrally formed with one another so as to be unitary in nature.
9. An aircraft assembly according to claim 1 , wherein the body and flange are formed from the same material.
10. An aircraft assembly according to claim 1 , wherein the assembly comprises sealant which extends over half way along the annular groove.
11. An aircraft assembly according to claim 1 , wherein:
the generally annular groove of the first recess is formed into the bush but not the lug;
a first surface of the bush that faces the lug includes a step defined by the generally annular groove; and
a second surface of the lug that faces the first surface of the bush and is the same length as the first surface along the first lug-bush interface is straight such a first portion of the first surface at the first cantilevered end portion is relatively far from the second surface of the lug and a second portion of the of the first surface spaced from the cantilevered end portion along the first lug-bush interface is relatively close to the second surface of the lug.
12. An aircraft landing gear assembly including an aircraft assembly, the aircraft assembly comprising:
a lug comprising a side wall and a lug bore extending therethrough;
a bush mounted within the lug, comprising:
a generally cylindrical body portion secured within the lug bore and having a bush bore extending therethrough defining a bearing face rotatably supporting a shaft; and
a radial flange extending outwardly from one end of the cylindrical body portion and secured against the lug side wall;
a first lug-bush interface defined between adjacent faces of the lug side wall and the radial flange, comprising a first recess defined by a generally annular groove formed into one or both of the lug and the bush, the first recess extending from a first end of the lug-bush interface where a radial outer surface of the flange is adjacent to the lug side wall into and along a portion of the lug-bush interface to define a first cantilevered end portion of the bush at the flange such that sealant may be applied in the first recess between the cantilevered portion and the lug to provide a moisture tight seal between the lug and bush; and
a second lug-bush interface defined between adjacent faces of the lug bore and the cylindrical body portion, comprising a second recess defined by a generally annular groove formed into one or both of the lug and the bush, the second recess extending from a first end of the lug-bush interface wherein an axial outer surface of the cylindrical body portion is adjacent to the lug bore into and along a portion of the lug-bush interface to define a second cantilevered end portion of the bush at the cylindrical body portion such that sealant may be applied in the second recess between the cantilevered portion and the lug to provide a moisture tight seal between the lug and bush.
13. An aircraft assembly comprising:
a lug comprising a side wall and a lug bore extending therethrough;
a bush mounted within the lug, comprising:
a generally cylindrical body portion secured within the lug bore and having a bush bore extending therethrough defining a bearing face configured to rotatably support a shaft; and
a radial flange extending outwardly from one end of the cylindrical body portion and secured against the lug side wall;
a first lug-bush interface defined between adjacent faces of the lug side wall and the radial flange, comprising a first recess defined by a generally annular groove formed into one or both of the lug and the bush, the first recess extending from a first end of the lug-bush interface where a radial outer surface of the flange is adjacent to the lug side wall into and along a portion of the lug-bush interface to define a first cantilevered end portion of the bush at the flange such that sealant may be applied in the first recess between the cantilevered portion and the lug to provide a moisture tight seal between the lug and bush, wherein the first recess is partially or completely filled with sealant; and
a second lug-bush interface defined between adjacent faces of the lug bore and the cylindrical body portion, comprising a second recess defined by a generally annular groove formed into one or both of the lug and the bush, the second recess extending from a first end of the lug-bush interface wherein an axial outer surface of the cylindrical body portion is adjacent to the lug bore into and along a portion of the lug-bush interface to define a second cantilevered end portion of the bush at the cylindrical body portion such that sealant may be applied in the second recess between the cantilevered portion and the lug to provide a moisture tight seal between the lug and bush.
14. An aircraft assembly comprising:
a lug comprising a lug side face and a lug bore extending through the lug side face;
a bush having a hollow cylindrical body and a radial flange extending radially from an end of the hollow cylindrical body and secured against the lug side face, the hollow cylindrical body having an outer face comprising a cylindrical outer wall secured in direct contact with the lug bore and an inner face defining a cylindrical bearing face configured to rotatably support a shaft;
a first lug-bush interface defined in a region in which the outer face of the cylindrical body faces the lug bore, comprising a first recess defined by a first generally annular groove formed into one or both of the lug and the bush, the first recess extending from a first end of the first lug-bush interface where an axial outer surface of the cylindrical body is adjacent to the lug bore into and along a portion of the first lug-bush interface to define a first cantilevered end portion of the bush at the cylindrical body such that sealant may be applied in the first recess between the cantilevered portion and the lug to provide a first moisture tight seal between the lug and the bush; and
a second lug-bush interface defined in a region in which a side of the radial flange faces the lug side face, comprising a second recess defined by a generally annular groove formed into one or both of the lug and the bush, the second recess extending from a first end of the lug-bush interface where a radial outer surface of the flange is adjacent to the lug side face into and along a portion of the lug-bush interface to define a second cantilevered end portion of the bush at the flange such that sealant may be applied in the second recess between the cantilevered portion and the lug to provide a second moisture tight seal between the lug and bush.