Abstract: An aircraft surface cover is provided. The aircraft surface cover includes a cover member that is configured to be removably secured to an aircraft structure. The cover member includes an exterior surface that has a microtextured surface including microtexture ribs that are configured to improve aerodynamic performance of the aircraft structure.

Abstract: An aircraft surface cover is provided. The aircraft surface cover includes a cover member that is configured to be removably secured to an aircraft structure. The cover member includes an exterior surface that has a microtextured surface including microtexture ribs that are configured to improve aerodynamic performance of the aircraft structure.

Abstract: An electromagnetically formed fluid circuit joint (276) includes a hollow fitting (272) and a tubular conduit (274). The hollow fitting (272) has an outer surface (280) with a groove (278). The tubular conduit (274) is received over the hollow fitting (272). The tubular conduit (274) includes a fitting overlay section (284), a first wall deformation for extension of the fitting overlay section (284) over the hollow fitting (272), and an electromagnetic field formed wall deformation (291) that extends into the groove (278). Another electromagnetically formed fluid circuit joint (642) includes a hollow fitting (654) and a tubular conduit (648). The hollow fitting (654) has an inner surface (668) with a groove (666). The tubular conduit (648) is mechanically separate from and is received within the hollow fitting (654). The tubular conduit (648) includes an externally applied electromagnetic field formed wall deformation (667) that extends into the groove (666).

Abstract: A powered nose aircraft wheel system (130) for an aircraft (12) includes landing gear (104) that extends from the aircraft (12). A wheel axel (136) is coupled to the landing gear (104). A wheel (134) is coupled to the wheel axel (136). A wheel motor (106) is coupled to the wheel axel (136) and the wheel (134). A controller (120) is coupled to the wheel motor (106) and rotates the wheel (134). A method of taxiing an aircraft (12) includes permitting the wheel (134) of the aircraft (12) to freely spin during the landing of the aircraft (12). Power is transferred from an auxiliary power unit (73) of the aircraft (12) to the wheel motor (106). The wheel (134) is rotated via the wheel motor (106). The aircraft (12) is steered and the speed of the wheel (134) is controlled via one or more controllers selected from an onboard controller (18, 118, 120) and an offboard controller (45, 58, 59).

Abstract: A method of forming a torque-transmitting coupling (193) includes forming at least one fitting (192) having a tube conforming area (200). The forming area (200) includes a material overflow groove (194) and multiple flat surfaces (202). The forming area (200) has an associated tube arc length that is approximately equal in length to a formed area length of the flat surfaces (202) with the elongated overflow groove (194). An elongated tube (190) is procured. The elongated tube (190) is formed onto the tube conforming area (200) to form the torque-transmitting coupling (193).