A flexible landing gear system for a vertical take-off and landing (VTOL) aircraft is disclosed. The flexible landing gear system may comprise a mounting bracket, a plurality of flexible supports, and plurality of surface contactors. The mounting bracket may be configured to couple to the VTOL aircraft. Each of the plurality of flexible supports comprising a proximal end and a distal end. The plurality of flexible supports may be coupled to the mounting bracket at a proximal end. A surface contactor may be positioned at the distal end of each of the plurality of flexible supports. The low-friction contactor may be a lightweight spherical ball, while the flexible support may be a flexible semi-rigid wire comprising a tempered high-carbon steel.

Disclosed is a technique for landing a drone using a parachute. The technique includes a parachute deployment system (PDS) that can deploy a parachute installed in a drone and land the drone safely. The parachute may be deployed automatically, e.g., in response to a variety of failures such as a free fall, or manually from a base unit operated by a remote user. For example, the PDS can determine the failure of the drone based on data obtained from an accelerometer, a gyroscope, a magnetometer and a barometer of the drone and automatically deploy the parachute if any failure is determined. In another example, the remote user can “kill” the drone, that is, cut off the power supply to the drone and deploy the parachute by activating an onboard “kill” switch from the base unit.

Disclosed is a technique for landing a drone using a parachute. The technique includes a parachute deployment system (PDS) that can deploy a parachute installed in a drone and land the drone safely. The parachute may be deployed automatically, e.g., in response to a variety of failures such as a free fall, or manually from a base unit operated by a remote user. For example, the PDS can determine the failure of the drone based on data obtained from an accelerometer, a gyroscope, a magnetometer and a barometer of the drone and automatically deploy the parachute if any failure is determined. In another example, the remote user can “kill” the drone, that is, cut off the power supply to the drone and deploy the parachute by activating an onboard “kill” switch from the base unit.

There is provided an energy absorbing landing gear system for attachment to a vertical landing apparatus. The energy absorbing landing gear system includes a linear damper assembly, and a load limiter assembly coupled to the linear damper assembly, the load limiter assembly having at least one deformable element to enhance an energy absorption capability. When the energy absorbing landing gear system is attached to the vertical landing apparatus, during a landing phase, the linear damper assembly contacts a landing surface, and a piston assembly of the linear damper assembly moves a first compression distance toward the load limiter assembly, and when the linear damper assembly reaches a maximum compression, the linear damper assembly moves a second compression distance into the load limiter assembly, and the at least one deformable element deforms.

Disclosed is a self-taxiing apparatus for an aircraft, the self-taxiing apparatus including an aircraft support body configured to support a body of an aircraft in a state in which the body of the aircraft is spaced apart from a ground surface, the aircraft support body having a motor mounting unit provided at a lower end thereof, an electric motor mounted in the motor mounting unit, a cover fixedly coupled to the motor mounting unit and configured to protect the electric motor, and an aircraft wheel configured to roll in a state of being in contact with the ground surface.

Disclosed is a self-taxiing apparatus for an aircraft, the self-taxiing apparatus including an aircraft support body configured to support a body of an aircraft in a state in which the body of the aircraft is spaced apart from a ground surface, the aircraft support body having a motor mounting unit provided at a lower end thereof, an electric motor mounted in the motor mounting unit, a cover fixedly coupled to the motor mounting unit and configured to protect the electric motor, and an aircraft wheel configured to roll in a state of being in contact with the ground surface.

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.

An example method includes receiving pitch angle sensor information indicative of a pitch angle of a vehicle, wherein the vehicle comprises a main landing gear having a strut and a pitch control surface configured to control the pitch angle of the vehicle; determining a trailing-edge-up limit for upward movement of the pitch control surface to control a de-rotation rate of the vehicle as the vehicle lands; receiving load sensor information indicative of a load on the strut of the main landing gear of the vehicle; based on the pitch angle of the vehicle being below a pitch angle threshold, determining an updated trailing-edge-up limit based on the load on the strut; and controlling the pitch control surface based on the updated trailing-edge-up limit.

An example method includes receiving pitch angle sensor information indicative of a pitch angle of a vehicle, wherein the vehicle comprises a main landing gear having a strut and a pitch control surface configured to control the pitch angle of the vehicle; determining a trailing-edge-up limit for upward movement of the pitch control surface to control a de-rotation rate of the vehicle as the vehicle lands; receiving load sensor information indicative of a load on the strut of the main landing gear of the vehicle; based on the pitch angle of the vehicle being below a pitch angle threshold, determining an updated trailing-edge-up limit based on the load on the strut; and controlling the pitch control surface based on the updated trailing-edge-up limit.

A landing gear including an outer cylinder, a shock strut assembly, and a passive shrink mechanism. The outer cylinder is coupled to a frame of an aircraft about a trunnion axis of rotation. The shock strut assembly is coupled to the outer cylinder for reciprocation along a longitudinal axis of the outer cylinder. The passive shrink mechanism includes: a first shrink link member coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member coupled to the outer cylinder, a first connecting link coupling the crank member to a walking beam of a landing gear retract mechanism, and a second connecting link coupling the crank member to the first shrink link member. The passive shrink mechanism is passively extended and shortened through actuation of the landing gear retract mechanism with deployment and retraction of the landing gear.