An emergency localization device for initiating an emergency measure, wherein the emergency localization device comprises a control unit, at least one acceleration sensor and at least one position sensor, the control unit being configured to receive a plurality of motion and/or position parameters from the acceleration sensor and/or from the position sensor, and by evaluating the plurality of motion or position parameters to determine a risk level for an emergency using a predefined logic, and to initiate an emergency measure if the calculated risk level exceeds a predefined threshold. The emergency localization device is reliable, robust and largely independent of aircraft-mounted systems.

A yaw alleviation device for an aircraft containing rotatable wing roots attached to wings. The device includes a spring configured to operatively connect to a wing; and a buckling member to operatively connect to the wing. The spring is configured to extend from an original unstrained position upon the buckling member undergoing buckling from an original unbuckled position to cause rotation of one or both wings in rotationally opposite directions. The buckling member may be positioned parallel and at an offset distance to the spring.

A yaw alleviation device for an aircraft containing rotatable wing roots attached to wings. The device includes a spring configured to operatively connect to a wing; and a buckling member to operatively connect to the wing. The spring is configured to extend from an original unstrained position upon the buckling member undergoing buckling from an original unbuckled position to cause rotation of one or both wings in rotationally opposite directions. The buckling member may be positioned parallel and at an offset distance to the spring.

The present disclosure provides a system and device for drones with ducted rotors. In some aspects, drones may comprise one or more systems of ducted rotors. In some embodiments, ducted rotors may increase the durability of the drone, limiting exposure of the rotors to external conditions and objects. In some aspects, a drone with ducted rotors may comprise a control vane or cone that may direct airflow within the drone as a mechanism to control flight path. In some implementations, a drone may comprise expandable landing gear than may allow for controlled landing, even in the event of rotor failure. In some aspects, a drone may comprise rotatable ducted rotors.

The present disclosure provides a system and device for drones with ducted rotors. In some aspects, drones may comprise one or more systems of ducted rotors. In some embodiments, ducted rotors may increase the durability of the drone, limiting exposure of the rotors to external conditions and objects. In some aspects, a drone with ducted rotors may comprise a control vane or cone that may direct airflow within the drone as a mechanism to control flight path. In some implementations, a drone may comprise expandable landing gear than may allow for controlled landing, even in the event of rotor failure. In some aspects, a drone may comprise rotatable ducted rotors.

A linear detector element includes an outer sheath having a first end and a second end, one or more shape memory responsive elements within the outer sheath and between the first end and the second end and first and second conductive wires passing through at least a portion of the outer sheath and through the one or more shape memory responsive elements. The one more shape memory responsive elements include a shape memory actuator surrounding the first and second conductive wires and that has an expanded size and a contracted size and that is sized and arranged such that when the shape memory actuator is in the contracted state the first and second conductive wires contact one another and when the shape memory actuator is in the expanded state the first and second conductive wires do not contact one another.

A linear detector element includes an outer sheath having a first end and a second end, one or more shape memory responsive elements within the outer sheath and between the first end and the second end and first and second conductive wires passing through at least a portion of the outer sheath and through the one or more shape memory responsive elements. The one more shape memory responsive elements include a shape memory actuator surrounding the first and second conductive wires and that has an expanded size and a contracted size and that is sized and arranged such that when the shape memory actuator is in the contracted state the first and second conductive wires contact one another and when the shape memory actuator is in the expanded state the first and second conductive wires do not contact one another.

Provided is a parachute device capable of reliably opening a parachute. A parachute device includes a parachute, a parachute accommodation section formed in a tubular shape including an opening at one end and a bottom at another end, the parachute accommodation section being configured to accommodate the parachute inside the parachute accommodation section, at least one flying body formed in a tubular shape including an opening at one end and a bottom at another end, the flying body being connected to the parachute, a tubular ejection section fixed at the parachute accommodation section, and configured to hold the flying body and eject the held flying body, a gas generating device fixed at the parachute accommodation section, and configured to generate gas, and a gas introduction path configured to introduce the gas generated from the gas generating device to an interior of the ejection section, wherein at the ejection section, one open end portion of the ejection section is inserted into the flying body, and another open end portion of the ejection section communicates with the gas introduction path.

A control system for a rescue hoist attached to an aircraft is disclosed. In various embodiments, the control system includes a first bus extending between a control module of the rescue hoist and a control input device; and a second bus extending between the control module of the rescue hoist and the control input device. The first bus is configured to transmit a first signal from the control input device to the control module and the second bus is configured to transmit a second signal from the control input device to the control module, both the first signal and the second signal being generated by the control input device in response to a manipulation of the control input device.

An autonomous aerial vehicle for ventilating persons. The ventilation becomes necessary as a result of fires, accidents, or medical emergencies. In these and comparable cases, the aerial vehicle aids for ventilating a person quickly and independently of the transport links of a location or the traffic situation at the time so the state of the person is stabilized until the arrival of an emergency doctor or other rescue workers and the chances of survival improves. The aerial vehicle provides positional determination inside and/or outside buildings, recording of the surrounding area, ventilation of at least one person, and a communication method or mechanism.