A plurality of landing gear are rotatable between a flight position and a landing position under the control of a control system on a vertical takeoff and landing aircraft. The plurality of landing gear may be separately and selectably rotatable to accommodate uneven or sloping terrain. The landing gear may include flight control surfaces and the degree of deployment of the landing gear controls the flight control surfaces. The flight control surfaces may include separately controllable elements. The aircraft may be a flight module of a modular and morphable air vehicle.

A plurality of landing gear are rotatable between a flight position and a landing position under the control of a control system on a vertical takeoff and landing aircraft. The plurality of landing gear may be separately and selectably rotatable to accommodate uneven or sloping terrain. The landing gear may include flight control surfaces and the degree of deployment of the landing gear controls the flight control surfaces. The flight control surfaces may include separately controllable elements. The aircraft may be a flight module of a modular and morphable air vehicle.

A nose structure of an aircraft includes an airframe. A wheel well assembly is coupled to the airframe and forms a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. A floor-panel support is supported by the pressure deck in the pressurized space. The pressure deck and the floor-panel support form a portion of a flight deck floor of a flight deck of the aircraft. A plurality of transport elements is located between the floor-panel support and the pressure deck. The plurality of transport elements is associated with at least one high-level system of the aircraft.

A nose structure of an aircraft includes an airframe. A wheel well assembly is coupled to the airframe and forms a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. A floor-panel support is supported by the pressure deck in the pressurized space. The pressure deck and the floor-panel support form a portion of a flight deck floor of a flight deck of the aircraft. A plurality of transport elements is located between the floor-panel support and the pressure deck. The plurality of transport elements is associated with at least one high-level system of the aircraft.

An aircraft includes an airframe, forming a nose structure of the aircraft, and at least one high-level system. The aircraft also includes a wheel well assembly, coupled to the airframe and forming a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. The aircraft further includes a floor-panel support, supported by the pressure deck. The aircraft also includes a plurality of transport elements, located between the floor-panel support and the pressure deck.

An aircraft includes an airframe, forming a nose structure of the aircraft, and at least one high-level system. The aircraft also includes a wheel well assembly, coupled to the airframe and forming a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. The aircraft further includes a floor-panel support, supported by the pressure deck. The aircraft also includes a plurality of transport elements, located between the floor-panel support and the pressure deck.

A method of making an aircraft includes steps of: assembling a subfloor assembly, including a panel support and plurality of transport elements; coupling a wheel well assembly to an airframe of the aircraft to form a nose landing gear bay of the aircraft; forming a pressure boundary delimiting a pressurized space and a non-pressurized space with the wheel well assembly and the airframe; coupling the subfloor assembly to the wheel well assembly, in the pressurized space, to form a portion of a floor of the aircraft so that the plurality of transport elements is located between the panel support and the wheel well assembly; and coupling the plurality of transport elements to at least one high-level system of the aircraft.

Described are systems and methods for a nacelle auxiliary landing gear to be utilized as an alternative landing gear in the event of main landing gear non-deployment. The systems described herein include a nacelle auxiliary landing gear that includes a nacelle auxiliary landing gear strut and a nacelle auxiliary landing gear wheel, coupled to the nacelle auxiliary landing gear strut, wherein at least a first portion of the nacelle auxiliary landing gear wheel is configured to be disposed outside of a nacelle of an aircraft propulsor. The nacelle auxiliary landing gear strut is coupled to a core engine. Techniques for use of the nacelle auxiliary landing gear are also described herein.

Described are systems and methods for a nacelle auxiliary landing gear to be utilized as an alternative landing gear in the event of main landing gear non-deployment. The systems described herein include a nacelle auxiliary landing gear that includes a nacelle auxiliary landing gear strut and a nacelle auxiliary landing gear wheel, coupled to the nacelle auxiliary landing gear strut, wherein at least a first portion of the nacelle auxiliary landing gear wheel is configured to be disposed outside of a nacelle of an aircraft propulsor. The nacelle auxiliary landing gear strut is coupled to a core engine. Techniques for use of the nacelle auxiliary landing gear are also described herein.

An aircraft includes a landing gear having a shock strut, an outer sleeve at least partially surrounding the shock strut, and a shrink mechanism coupled to both the outer sleeve and the shock strut, where the shrink mechanism moves the shock strut relative to the outer sleeve. The shrink mechanism includes a shaft rotatably coupled to the outer sleeve, an anchor arm coupled to the shaft, a shrink arm coupled to the shaft, the shrink arm and the anchor arm being coupled to the shaft so as to rotate as a unit with the shaft about a shaft rotation axis, relative to the outer sleeve, at least 180 when the anchor arm is coupled to the structure within the wing of the aircraft, and a shrink link rotatably coupled to the shrink arm, the shrink link being configured to rotatably couple to the shock strut.