Airframe panel for aircraft and aircraft wing
An airframe panel for aircraft having stringers and ribs which enables reduction of the workload of the shimming operation includes a plurality of stringers provided on the inner surface of a lower skin along the spanwise direction of a wing, and a plurality of ribs provided along the chordwise direction of the wing. In a part of the panel in which a rib is provided, a flat support surface connects the two adjacent stringers. In another part of the panel in which no rib is provided, a stepped surface connects the two adjacent stringers where the stepped surface includes a thin-walled groove, and thick-walled bases to be connected to the stringers located at both sides of the groove.
1. An airframe panel for aircraft comprising:
a skin having an inner surface; and
a plurality of stringers provided on the skin along a first direction, the plurality of stringers each comprising a base portion extending from the inner surface of the skin and a web portion extending from the base portion, the base portion being wider than the web portion;
wherein the skin includes a first region in which a rib is provided along a second direction that intersects the first direction, and a second region in which the rib is not provided,
wherein the skin comprises a raised surface portion integral with and extending from the inner surface, the raised surface portion having a raised support surface that is flat and is integral with and connects the base portion of two adjacent stringers of the plurality of stringers in the first region,
wherein a stepped surface connects the two adjacent stringers in the second region,
wherein the rib contacts the raised support surface of the skin,
wherein a region of the skin having the raised support surface and the base portion of two adjacent stringers has a constant thickness along the second direction,
wherein the plurality of stringers and the skin comprise a single, unitary piece of a base material, and
wherein the plurality of stringers are integrally formed with the skin by machining out of the base material.
2. The airframe panel for aircraft according to claim 1 , wherein the stepped surface includes:
a thin-walled portion located at a center of the two adjacent stringers, and thick-walled portions located at both sides of the thin-walled portion along roots of the two adjacent stringers.
3. The airframe panel for aircraft according to claim 2 , wherein a portion where the flat surface of the skin connects the two adjacent stringers in the first region has a same thickness as the thick-walled portions of the stepped surface in the second region.
4. An aircraft wing comprising:
a plurality of stringers provided on an upper skin and a lower skin, respectively, to extend along a spanwise direction;
a plurality of ribs provided between the upper skin and the lower skin to extend along a chordwise direction;
wherein the aircraft includes the airframe panel for aircraft according to claim 1 .
5. A method for forming an airframe panel for aircraft, the airframe panel comprising:
a skin having an inner surface; and
a plurality of stringers provided on the skin along a first direction, the plurality of stringers each comprising a base portion extending from the inner surface of the skin and a web portion extending from the base portion, the base portion being wider than the web portion;
wherein the skin includes a first region in which a rib is provided along a second direction that intersects the first direction, and a second region in which the rib is not provided,
wherein the skin comprises a raised surface portion integral with and extending from the inner surface, the raised surface portion having a flat support surface that is integral with and connects the base portion of two adjacent stringers of the plurality of stringers in the first region,
wherein a stepped surface connects the two adjacent stringers in the second region,
wherein the rib contacts the flat support surface of the skin,
wherein a region of the skin having the raised support surface and the base portion of two adjacent stringers has a constant thickness along the second direction,
wherein the plurality of stringers and the skin comprise a single, unitary piece of a base material, and
wherein the plurality of stringers are integrally formed with the skin by machining out of the base material.