Helicopter skid landing gear

Patent metadata

Field	Value
Publication number	US-2016244155-A1
Application number	US-201514626365-A
Country	US
Kind code	A1
Filing date	Feb 19, 2015
Priority date	Feb 19, 2015
Publication date	Aug 25, 2016
Grant date	—

Abstract

A landing gear for an aircraft can include a skid tube having an inboard flat side wall and an outboard flat side wall, the skid tube having a skid tube centerline plane that is parallel to at least one of the outboard flat side wall and the inboard flat side wall, the skid tube being canted inboard at an angle The landing gear can include a forward cross tube having a straight horizontal portion, a first bend transitioning the straight horizontal portion into a straight angled portion, and a second bend transitioning the straight angled portion into a straight end portion.

First claim

What is claimed is:

1 . A landing gear for an aircraft, the landing gear comprising:
a skid tube having an inboard flat side wall and an outboard flat side wall, the skid tube having a skid tube centerline plane that is parallel to at least one of the outboard flat side wall and the inboard flat side wall, the skid tube being canted inboard at an angle; a forward cross tube having a straight horizontal portion, a first bend transitioning the straight horizontal portion into a straight angled portion, and a second bend transitioning the straight angled portion into a straight end portion; and a step member coupled to a forward end portion of the skid tube, the step member having a first inboard flat side wall and a first inboard flat side wall, the first inboard flat side wall and the first inboard flat side wall being parallel to the inboard flat side wall and the outboard flat side wall of the skid tube, respectively.

2 . The landing gear according to claim 1 , wherein the step member curves upward such that a step member central axis forms a first plane, and wherein the straight end portion of the forward cross tube has a straight end central axis that lies on the first plane defined by the step member.

3 . The landing gear according to claim 1 , the step member comprising:
a step portion having a tow ring opening at a forward portion of the step member.

4 . The landing gear according to claim 1 , the step member comprising:
a step portion having a striated portion

5 . The landing gear according to claim 4 , wherein the striated portion has a crowned geometry such that an inboard portion of the striated portion has a first normal vector directed toward a fuselage of the aircraft, and outboard portion of the striated portion has a second normal vector directed away from the fuselage of the aircraft.

6 . The landing gear according to claim 1 , the step member comprising:
a plurality of interference features at an aft portion of the step member.

7 . The landing gear according to claim 1 , comprising:
a saddle member for coupling the cross tube to the skid tube, the saddle member having an outboard planar portion and an inboard planar portion, with a bend portion therebetween, the outboard planar portion being adjacent and parallel to the outboard flat side wall of the skid tube, the inboard planar portion being adjacent and parallel to the inboard flat side wall of the skid tube.

8 . The landing gear according to claim 7 , wherein the bend portion of the saddle member provides an aerodynamic surface.

9 . The landing gear according to claim 7 , wherein a central bend axis of the bend portion of the saddle is located in the same plane as the skid tube centerline plane and a centerline axis of the straight end portion of the forward cross tube.

10 . The landing gear according to claim 1 , further comprising:
an aft cross tube having an aft straight horizontal portion, an aft first bend transitioning the aft straight horizontal portion into an aft straight angled portion, and an aft second bend transitioning the aft straight angled portion into an aft straight end portion.

11 . The landing gear according to claim 1 , wherein the angle is 20 degrees.

12 . The landing gear according to claim 1 , wherein the angle is between 0 degrees and 35 degrees.

13 . A landing gear for an aircraft, the landing gear comprising:
a skid tube having an inboard flat side wall and an outboard flat side wall, the skid tube having a skid tube centerline plane that is parallel to at least one of the outboard flat side wall and the inboard flat side wall, the skid tube being oriented at a canted angle such that the skid tube centerline plane is canted at the canted angle relative to a fore/aft centerline plane of the aircraft; a cross tube having a straight horizontal portion, a first bend that transitions the straight horizontal portion into a straight angled portion, and a second bend that transitions the straight angled portion into a straight end portion, the straight end portion being oriented at the same canted angle as the skid tube; and a saddle member for coupling the cross tube to the skid tube, the saddle formed from a constant thickness sheet metal, the saddle member having an outboard planar portion and an inboard planar portion with a bend portion therebetween, the outboard planar portion being adjacent and parallel to the outboard flat side wall of the skid tube, the inboard planar portion being adjacent and parallel to the inboard flat side wall of the skid tube.

14 . The landing gear according to claim 13 , wherein the canted angle is 20 degrees.

15 . The landing gear according to claim 13 , wherein the canted angle is between 0 degrees and 35 degrees.

16 . The landing gear according to claim 13 , further comprising:
a step member coupled to a forward end portion of the skid tube, the step member having a first inboard flat side wall and a first inboard flat side wall, the first inboard flat side wall and the first inboard flat side wall being parallel to the inboard flat side wall and the outboard flat side wall of the skid tube, respectively.

17 . The landing gear according to claim 16 , wherein the step member curves upward such that a step member central axis forms a first plane, and wherein the straight end portion of the forward cross tube has a straight end central axis that lies on the first plane defined by the step member.

18 . The landing gear according to claim 16 , wherein the step member curves upward such that a step member central axis forms a first plane, and wherein a centerline axis of the straight end portion of the forward cross tube lies on the first plane.

19 . The landing gear according to claim 13 , the step member comprising:
a step portion having a tow ring opening forward of a striated portion.

20 . The landing gear according to claim 19 , wherein the striated portion has a crowned geometry such that an inboard portion of the striated portion has a first normal vector directed toward a fuselage of the aircraft, and outboard portion of the striated portion has a second normal vector away from the fuselage of the aircraft.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Amante William A

Classifications

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64C25/52 Primary

  Skis or runners · CPC title

• B64C25/32

  characterised by elements which contact the ground or similar surface  (arrester hooks B64C25/68) · CPC title