An aircraft subassembly comprises a fuselage structure, comprising a first side and a second side. The aircraft subassembly further comprises a main-landing-gear system, having a single pair of wheels. The main-landing-gear system additionally comprises a sponson, connected to and extending outward from the fuselage structure. The sponson comprises a central portion and a first main-landing-gear door that is moveable relative to the central portion between, inclusively, a closed position and an open position. The sponson further comprises a second main-landing-gear door that is moveable relative to the central portion between, inclusively, a closed position and an open position. The main-landing-gear system further comprises a first main-landing-gear assembly, connected to the first wheel and a second main-landing-gear assembly, connected to the second wheel.

An aircraft for the transport of cargo and/or passengers, comprising a fuselage extending in longitudinal direction and having an upper deck, in particular main deck, and a lower deck separated from each other by a floor, wherein the fuselage comprises a barrel section with a cross-sectional profile for accommodating cargo and/or passengers, wherein the cross-sectional profile is essentially formed by several, in particular four, circular arc sections, which have radii (R1, R2, R3) with centers (M1, M2, M3′, M3″) differing from one another, so that the cross-sectional profile is designed in such a way that cargo items with different size dimensions, in particular cargo containers with different height and width dimensions, can be accommodated in the upper deck and the lower deck.

A landing gear for an aircraft comprising a truck support strut, a landing gear retract mechanism coupling the truck support strut to a frame of the aircraft, so that the truck support strut is suspended from the frame by the landing gear retract mechanism, at least one wheel support arm rotatably coupled to the truck support strut, a carrier member coupled to the landing gear retract mechanism and to the truck support strut so that the landing gear retract mechanism drives the carrier member along the truck support strut, and at least one shock absorber, each of the at least one shock absorber being coupled to both a respective one of the at least one wheel support arm and the carrier member so that movement of the carrier member effects rotation of the at least one wheel support arm relative to the truck support strut.

Landing gear monitoring systems and methods for an aircraft include a landing gear timing analysis control unit that is configured to analyze one or both of landing gear motion of one or more landing gears of the aircraft or door motion of one or more doors proximate to the landing gear(s) to determine an operational status of one or both of the landing gear(s) or the door(s).

A device configured to deploy a retractable landing gear having a main landing gear and a secondary landing gear is provided. The device includes an electrical motor in driving connection with a drive shaft connecting the secondary landing gear with the main landing gear. A retractable landing gear including the device and an aircraft having the landing gear are also provided.

A nose landing gear system is disclosed. In various embodiments, the nose landing gear system includes an electro-hydraulic actuator configured to raise and lower a nose shock strut assembly; a first electro-mechanical actuator configured to steer the nose shock strut assembly; and a second electro-mechanical actuator configured to open and close a fairing door.

A retractable landing gear system configured to contour an aircraft fuselage includes a landing wheel having an axle, a wheel rotation strut assembly coupling the landing wheel to the aircraft fuselage and an actuation strut assembly configured to move the wheel rotation strut assembly between various positions including a deployed position and a stowed position. The axle of the landing wheel is pivotably coupled to a distal end of the wheel rotation strut assembly and configured to pivot relative to the wheel rotation strut assembly as the actuation strut assembly moves the wheel rotation strut assembly between the deployed and stowed positions such that the landing wheel generally contours the aircraft fuselage when the wheel rotation strut assembly is in the stowed position.

An aircraft landing gear 2 is disclosed having a first arm 6a configured to have one or more wheels 8a mounted at one end, the first arm 6a being configured for mounting to a pivot 10a. The landing gear 2 includes a second arm 6b configured to have one or more wheels 8b mounted at one end, the second arm 6b being configured for mounting to a pivot 10b. The landing gear 2 further includes a first link 18a pivotally coupled to the first arm 6a, a second link 18b pivotally coupled to the second arm 6b; and a main link 20 pivotally coupled to each of the first and second links 18a, 18b and to a shock absorber 22 arranged to provide a biasing force via (i) the main linkage 20 and the first link 18a which opposes rotation of the first arm 6a about the pivot 10a and (ii) the main linkage 20 and the second link 18b which opposes rotation of the second arm 6b about the pivot 10b.

Systems and methods for bipedal nose landing gear of an aircraft. One embodiment is a nose landing gear of an aircraft. The nose landing gear includes a shock strut coupled to an axle with a nose wheel, and a folding side brace extending from the shock strut inboard toward a belly of the aircraft and configured to stabilize the shock strut. The nose landing gear also includes a trunnion configured to pivot the shock strut forward toward a nose and inboard toward the belly of the aircraft to retract the nose wheel.

Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.