An aircraft tail skid energy absorption indicator including a crushable indicator cartridge disposed within the an outer shock absorber canister of the aircraft tail skid, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit, where the indicator rod extends through an aperture in a wall of the outer shock absorber canister, where the indicator rod includes at least one graduation that indicates an amount of remaining energy absorption of the aircraft tail skid energy absorption indicator.

A landing gear system for an aircraft is presented. The landing gear system comprises a composite flex beam having through-thickness stitching and a curvature having a radius greater than 5 inches; and a trunnion connected to the composite flex beam and offset from a neutral surface of the composite flex beam.

A shock strut is disclosed. The shock strut may include a shock strut cylinder, a shock strut piston that is slidably disposed within the shock strut cylinder, a metering pin, and a percolation seal configured to restrict a flow of liquid between the shock strut cylinder and the shock strut piston.

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 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.

An airplane emergency escape drone is shown and described. The airplane emergency escape drone includes a life support system secured within a housing with a compressed air tank that controls the amount of oxygen from an oxygen tank and air from an air tank released into the housing. The airplane emergency escape drone also includes an inflatable floatation device secured to the housing. The airplane emergency escape drone also includes propellers having safety grates underneath the propellers. The airplane emergency escape drone also includes a CPU that is in connection with a video control system that includes a video input component and a signal transmitter.

An airplane emergency escape drone is shown and described. The airplane emergency escape drone includes a life support system secured within a housing with a compressed air tank that controls the amount of oxygen from an oxygen tank and air from an air tank released into the housing. The airplane emergency escape drone also includes an inflatable floatation device secured to the housing. The airplane emergency escape drone also includes propellers having safety grates underneath the propellers. The airplane emergency escape drone also includes a CPU that is in connection with a video control system that includes a video input component and a signal transmitter.

A load detection system detects loads applied to a landing gear assembly during landing. The landing gear assembly includes an axle coupled to a piston rod of a compressible shock strut and a wheel rotatably mounted the axle. A torque link includes a lower link coupled to the piston rod of the shock strut so that compression of the shock strut rotates the link about a first axis. The load detection system includes a probe rotatably coupled about a second axis. The probe engages a ground surface when the shock strut is uncompressed and the wheel contacts the ground surface. The lower link rotates the probe as the shock strut compresses. A sensor senses a position of the probe, which corresponds to a load on the wheel when the shock strut is uncompressed and the wheel is in contact with the ground surface.

A load detection system detects loads applied to a landing gear assembly during landing. The landing gear assembly includes an axle coupled to a piston rod of a compressible shock strut and a wheel rotatably mounted the axle. A torque link includes a lower link coupled to the piston rod of the shock strut so that compression of the shock strut rotates the link about a first axis. The load detection system includes a probe rotatably coupled about a second axis. The probe engages a ground surface when the shock strut is uncompressed and the wheel contacts the ground surface. The lower link rotates the probe as the shock strut compresses. A sensor senses a position of the probe, which corresponds to a load on the wheel when the shock strut is uncompressed and the wheel is in contact with the ground surface.

A landing gear assembly is disclosed having a trailing arm for carrying a wheel, a shock absorber pivotally coupled to the arm for damping movement of the arm, and an articulated lock mechanism. The mechanism includes an upper and lower lock links each with a distal end respectively pivotally coupled to the shock and arm. Proximal ends of the lock links are pivotally coupled about a common axis to enable a distance between the distal ends to vary. The mechanism is lockable to lock the assembly in an extended or retracted configuration. When the assembly is in the extended or retracted configuration, the mechanism is locked respectively in an extended or retracted locking configuration, such that the distance between the distal ends of the lock links is substantially the same in either extended or retracted locking configuration.