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.

A landing zone evaluation and rating sharing system includes a central processor unit (CPU), at least one sensor input operatively connected to the CPU, a communication controller operatively connected to the CPU, the communication controller being operable to pass data to other systems associated with the aerial vehicle, and a landing zone (LZ) evaluation controller operatively coupled to a non-volatile computer readable storage medium having computer readable program instructions embodied therewith. The computer readable program instructions are executable by the central processor unit to receive data received through the at least one sensor input, evaluate the data to determine a LZ rating for a particular landing zone, and communicate the LZ rating to one or more systems associated with the aerial vehicle.

A landing zone evaluation and rating sharing system includes a central processor unit (CPU), at least one sensor input operatively connected to the CPU, a communication controller operatively connected to the CPU, the communication controller being operable to pass data to other systems associated with the aerial vehicle, and a landing zone (LZ) evaluation controller operatively coupled to a non-volatile computer readable storage medium having computer readable program instructions embodied therewith. The computer readable program instructions are executable by the central processor unit to receive data received through the at least one sensor input, evaluate the data to determine a LZ rating for a particular landing zone, and communicate the LZ rating to one or more systems associated with the aerial vehicle.

A tactile signal seat belt sleeve has tactile signal producing elements arrayed along a sleeve that is adapted to fit over a seat belt for a vehicle, such as an aircraft. The elements may be arranged, for example, along the body-facing side of the belt. Each sleeve incorporates a signal-receiving element that allows for the activation of vibration-producing motors embedded in the fabric of the seat belt sleeve or belting. Vibration motors, such as piezoelectric devices, can be used to produce the tactile feedback. The haptic feedback assembly is connected to an interface unit that uses data from aircraft systems to sense, for example, the aircraft altitude and pitch, roll and yaw system. The interface unit generates signal to haptic devices to create appropriate vibrations patterns to the sleeve. The vibrations may be used to indicate directions of turn using output signals from various navigations systems.

A tactile signal seat belt sleeve has tactile signal producing elements arrayed along a sleeve that is adapted to fit over a seat belt for a vehicle, such as an aircraft. The elements may be arranged, for example, along the body-facing side of the belt. Each sleeve incorporates a signal-receiving element that allows for the activation of vibration-producing motors embedded in the fabric of the seat belt sleeve or belting. Vibration motors, such as piezoelectric devices, can be used to produce the tactile feedback. The haptic feedback assembly is connected to an interface unit that uses data from aircraft systems to sense, for example, the aircraft altitude and pitch, roll and yaw system. The interface unit generates signal to haptic devices to create appropriate vibrations patterns to the sleeve. The vibrations may be used to indicate directions of turn using output signals from various navigations systems.

A vertical landing vehicle including an airframe forming a hull and having at least one wing coupled to the airframe, at least one proximity sensor coupled to the airframe, and a flight control system including a control processor and an operator interface, wherein the at least one proximity sensor is coupled to the control processor, wherein the control processor, based on signals from the at least one proximity sensor, is configured to generate, for presentation through the operator interface, situational awareness indications corresponding to portions of the hull sensed by the at least one proximity sensor and obstacles sensed by the at least one proximity sensor, and wherein the situational awareness indications comprise a terrain map overlay including positional relationships between the hull and the obstacles.

A vertical landing vehicle including an airframe forming a hull and having at least one wing coupled to the airframe, at least one proximity sensor coupled to the airframe, and a flight control system including a control processor and an operator interface, wherein the at least one proximity sensor is coupled to the control processor, wherein the control processor, based on signals from the at least one proximity sensor, is configured to generate, for presentation through the operator interface, situational awareness indications corresponding to portions of the hull sensed by the at least one proximity sensor and obstacles sensed by the at least one proximity sensor, and wherein the situational awareness indications comprise a terrain map overlay including positional relationships between the hull and the obstacles.

A vertical landing vehicle including an airframe forming a hull and having at least one wing coupled to the airframe, at least one proximity sensor coupled to the airframe, and a flight control system including a control processor and an operator interface, the at least one proximity sensor being coupled to the control processor, the control processor being configured to receive proximity signals from the at least one proximity sensor and present, through the operator interface and based on the proximity signals, situational awareness information of obstacles within a predetermined distance of the vertical landing vehicle relative to the hull and/or the at least one wing.

A vertical landing vehicle including an airframe forming a hull and having at least one wing coupled to the airframe, at least one proximity sensor coupled to the airframe, and a flight control system including a control processor and an operator interface, the at least one proximity sensor being coupled to the control processor, the control processor being configured to receive proximity signals from the at least one proximity sensor and present, through the operator interface and based on the proximity signals, situational awareness information of obstacles within a predetermined distance of the vertical landing vehicle relative to the hull and/or the at least one wing.

Disclosed is a drone. The present invention includes a plurality of propellers creating a lift to prevent inclination and overturn of the drone due to a lift difference generated from uneven ground, a power driving unit providing a rotation power to each of a plurality of the propellers, a ground sensing unit measuring a distance to a first region of the ground and a shape of the first region, and a controller controlling the power driving unit to differentiate rotation ratios of a plurality of the propellers based on the measured distance and shape if receiving an input signal for landing at the first region.