A landing gear monitoring and alerting system includes a locking pin configured to be inserted into an aperture extending through a linkage of an extended landing gear assembly. When inserted into the aperture, the locking pin inhibits movement of the linkage to establish a locked state of the extended landing gear assembly. This system further includes a magnetic sensor and a communication module. The magnetic sensor is disposed proximate the aperture and is configured to sense a magnetic response indicative of the locking pin being disposed within the aperture. The magnetic sensor is configured to generate a sensor output indicative of the locking pin being disposed within the aperture. The communication module has a transmitter coupled to the magnetic sensor so as to receive the sensor output and is configured to responsively transmit a signal indicative of the locking pin being disposed within the aperture.

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 inspection system is disclosed herein. The inspection system includes a control system and a hub assembly. The control system includes a base having a top surface and configured to move horizontally forward and backward, an upright member extending orthogonally from the top surface of the base and configured to move vertically up and down, the upright member having a top surface, and an elongated member extending orthogonal to the upright member having a proximal end and a distal end, the proximal end connected to the top of the upright member, wherein the elongated member is configured to rotate. The hub assembly is connected to the distal end of the elongated member. The hub assembly includes a spring-loaded arm extending orthogonally from the hub assembly and a sensor connected to a distal end of the spring-loaded arm.

An inspection system is disclosed herein. The inspection system includes a control system and a hub assembly. The control system includes a base having a top surface and configured to move horizontally forward and backward, an upright member extending orthogonally from the top surface of the base and configured to move vertically up and down, the upright member having a top surface, and an elongated member extending orthogonal to the upright member having a proximal end and a distal end, the proximal end connected to the top of the upright member, wherein the elongated member is configured to rotate. The hub assembly is connected to the distal end of the elongated member. The hub assembly includes a spring-loaded arm extending orthogonally from the hub assembly and a sensor connected to a distal end of the spring-loaded arm.

Systems and methods for automatically controlling landing gear responsive to detected aerial vehicle conditions. A system can receive, from one or more sensors of the aerial vehicle, altitude information and speed information of the aerial vehicle. The system can determine to lower landing gear of the aerial vehicle based on a change in a state of the aerial vehicle, and identify a condition corresponding to a type of the aerial vehicle and the state of the aerial vehicle. The system can compare the speed information and the altitude information to the condition to determine that a condition to lower landing gear is satisfied. Responsive to determining that the condition to lower the landing gear is satisfied, the system can provide a signal to lower the landing gear.

Systems and methods for automatically controlling landing gear responsive to detected aerial vehicle conditions. A system can receive, from one or more sensors of the aerial vehicle, altitude information and speed information of the aerial vehicle. The system can determine to lower landing gear of the aerial vehicle based on a change in a state of the aerial vehicle, and identify a condition corresponding to a type of the aerial vehicle and the state of the aerial vehicle. The system can compare the speed information and the altitude information to the condition to determine that a condition to lower landing gear is satisfied. Responsive to determining that the condition to lower the landing gear is satisfied, the system can provide a signal to lower the landing gear.

An aircraft includes a frame body that includes an attaching unit on an upper portion thereof, that is formed into a frame-shape structure, and that couples an object to a lower portion thereof, the attaching unit being configured to be capable of adjusting a position in an up-down direction of the attaching unit. A main body including a flying mechanism is positioned on an upper portion of the frame body. A control unit controls a position in the up-down direction of the attaching unit such that a flying posture of the object is controlled in accordance with a posture of the flying mechanism.

An aircraft includes a frame body that includes an attaching unit on an upper portion thereof, that is formed into a frame-shape structure, and that couples an object to a lower portion thereof, the attaching unit being configured to be capable of adjusting a position in an up-down direction of the attaching unit. A main body including a flying mechanism is positioned on an upper portion of the frame body. A control unit controls a position in the up-down direction of the attaching unit such that a flying posture of the object is controlled in accordance with a posture of the flying mechanism.

An aircraft system for an aircraft, the aircraft system including a controller configured, during a take-off procedure, to determine that a one engine inoperative condition is met and determine that a predetermined take-off criterion is met. The controller is configured, on the basis of a determination that the one engine inoperative condition is met, and prior to receiving a command to retract a landing gear of the aircraft, to initiate automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position when the controller determines that the predetermined take-off criterion is met, and inhibit the automatic opening when the controller determines that the predetermined take-off criterion is not met.