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.

A falling-resistant and anti-drifting unmanned aerial vehicle has a main body and at least one rotor wing thereon. Both sides of the main body have a wing with an airbag filled with gas lighter than air. Bulges protruding downwards are arranged at the bottoms of the airbag. The two airbags are at the same height symmetrically arranged based on the main body. The airbag can function as an undercarriage when the aircraft lands down, and as a buffer when crash landing and then reduce damage to the main body. If the aircraft falls in water, the aircraft can float on the water to avoid damage caused by sinking. As bulges protruding downwards are arranged at the bottoms of the airbags, in spraying operation, side wing can be relatively well baffled by the bulges in case of side wing blowing in the flying process, resulting in less droplets draft.

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.

Disclosed is a visual tool for determining the spatial orientation of an aircraft relative to a level plane, including a closed container constructed of a material that permits the passage of light therethrough. An indicator body is fixed within the container and viewable through the container. An indicator fluid is provided including a liquid that fills the container a selected amount. The indicator fluid presents a fluid surface that is viewable through the container and free to move within the container. When the visual tool is affixed to an aircraft the indicator body and the fluid surface are parallel to the level plane when the aircraft is level. The indicator body is moved out of the level plane and the fluid surface remains parallel to the level plane when the aircraft deviates from the level plane to generate a visual signal representative of the orientation of the aircraft.

Disclosed is a visual tool for determining the spatial orientation of an aircraft relative to a level plane, including a closed container constructed of a material that permits the passage of light therethrough. An indicator body is fixed within the container and viewable through the container. An indicator fluid is provided including a liquid that fills the container a selected amount. The indicator fluid presents a fluid surface that is viewable through the container and free to move within the container. When the visual tool is affixed to an aircraft the indicator body and the fluid surface are parallel to the level plane when the aircraft is level. The indicator body is moved out of the level plane and the fluid surface remains parallel to the level plane when the aircraft deviates from the level plane to generate a visual signal representative of the orientation of the aircraft.

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.

Controlled energy absorption of seats for impact is described herein. One disclosed example method includes determining a weight of an occupant of a seat of an aircraft, and calculating, using a processor, a stroke load of a seat energy absorber operatively coupled to the seat based on the weight of the occupant. The example method also includes setting the seat energy absorber to the calculated stroke load.