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.

The present disclosure relates to unmanned aerial vehicles (“UAVs”), systems, and methods for efficiently and safely landing while improving flight performance. In particular, the disclosure incudes a light-weight, gravity-fed, self-deploying landing gear assembly that aligns to the direction of the runway upon landing. For example, the landing gear assembly can include a pin switch and a tear-through barrier that releases and deploys the landing gear assembly. Additionally, the landing gear assembly can include castering wheels that rotate (i.e., swivel) while the UAV is in flight. Furthermore, the landing gear assembly can include friction-disks to reduce the rotation of the castering wheels when the landing gear assembly contacts the ground and receives the weight of the UAV. Moreover, the landing gear assembly can detect that the UAV has landed and can signal the UAV to initiate a roll stop mechanism.

The present disclosure relates to unmanned aerial vehicles (“UAVs”), systems, and methods for efficiently and safely landing while improving flight performance. In particular, the disclosure incudes a light-weight, gravity-fed, self-deploying landing gear assembly that aligns to the direction of the runway upon landing. For example, the landing gear assembly can include a pin switch and a tear-through barrier that releases and deploys the landing gear assembly. Additionally, the landing gear assembly can include castering wheels that rotate (i.e., swivel) while the UAV is in flight. Furthermore, the landing gear assembly can include friction-disks to reduce the rotation of the castering wheels when the landing gear assembly contacts the ground and receives the weight of the UAV. Moreover, the landing gear assembly can detect that the UAV has landed and can signal the UAV to initiate a roll stop mechanism.

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 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.

A land-and-air vehicle configured to switch between a ground traveling mode and an aerial flight mode incudes a body, a wing, a wheel, a suspension, and a lock mechanism. The wing is attached to the body. The wheel is provided on a lower side of the body. The suspension is configured to support the body via the wheel on ground, and to contract due to self-weight of the land-and-air vehicle. The lock mechanism is configured to limit expansion of the suspension from a state in which the suspension has contracted due to the self-weight.

A nose landing gear system is disclosed. In various embodiments, the nose landing gear system includes an electric motor; a hydraulic pump connected to the electric motor; a gearbox connected to the electric motor; and a clutch configured to mechanically couple the gearbox to a steering collar.

Shield assemblies for an aircraft landing gear include an aerodynamic shield, a first support bracket assembly, and a second support bracket assembly. The first support bracket assembly is configured to couple with a structural member of the aircraft landing gear, to support a first end of the aerodynamic shield, and to have a first position that is fixed relative to the structural member in an x-direction, a y-direction, and a z-direction. The first support bracket assembly has a first clamp that is configured to fix the first support bracket assembly relative to the structural member in the x-direction. The second support bracket assembly is configured to support a second end of the aerodynamic shield and to have a second position that is fixed relative to the structural member in the y-direction and the z-direction.

Shield assemblies for an aircraft landing gear include an aerodynamic shield, a first support bracket assembly, and a second support bracket assembly. The first support bracket assembly is configured to couple with a structural member of the aircraft landing gear, to support a first end of the aerodynamic shield, and to have a first position that is fixed relative to the structural member in an x-direction, a y-direction, and a z-direction. The first support bracket assembly has a first clamp that is configured to fix the first support bracket assembly relative to the structural member in the x-direction. The second support bracket assembly is configured to support a second end of the aerodynamic shield and to have a second position that is fixed relative to the structural member in the y-direction and the z-direction.

A door fairing for a retractable landing gear leg of an aircraft is disclosed having an outer member which covers a portion of a landing gear bay of the aircraft when the landing gear leg is retracted. An inner member of the door fairing is coupled to the outer member via a number of configurable couplings which allow adjustment of the position of the outer member with respect to the inner member. The inner member has mounting points for mounting the door fairing to the landing gear leg. Prior to fitting the door fairing at the aircraft, measured or derived dimensional parameters of the landing gear bay are used to adjust the configurable couplings such that the door fairing is preconfigured to fit the landing gear bay of the aircraft.