A system and method for automated vertical takeoff and landing (VTOL) aircraft emergency landing is disclosed. The system receives a plurality of inputs from onboard modules including aircraft state, vehicle health, acceptable landing zone (LZ), emergency landing path, and 3D world model to prepare an emergency landing procedure when necessary. If functional onboard an unmanned VTOL aircraft, the vehicle health module determines an emergency landing requirement, the system commands a damage tolerant autopilot to perform the emergency procedure and automatically control the VTOL aircraft. If functional onboard a manned VTOL aircraft, an operator or the vehicle health module initiates the emergency landing. Regardless of initiation, the emergency landing system controls, or provides guidance for manned control of, the VTOL aircraft from the point of initiation through touchdown at a threat differentiated preferred LZ via failure-based flight control inputs for automatic landing, or autonomous autorotation entry, glide, and flare.

Aspects of the disclosure provide methods for determining a likelihood of failure of an aerial vehicle. In one instance, the method may include receiving a first rotation rate of an impeller of an altitude control system of the aerial vehicle. A model may be used to determine a second impeller rotation rate, wherein the second rotation rate is an idealized impeller rotation rate. The first rotation rate may be compared to the second rotation rate. Based on the comparison, the likelihood of failure may be determined.

A system and method for automated vertical takeoff and landing (VTOL) aircraft emergency landing is disclosed. The system receives a plurality of inputs from onboard modules including aircraft state, vehicle health, acceptable landing zone (LZ), emergency landing path, and 3D world model to prepare an emergency landing procedure when necessary. If functional onboard an unmanned VTOL aircraft, the vehicle health module determines an emergency landing requirement, the system commands a damage tolerant autopilot to perform the emergency procedure and automatically control the VTOL aircraft. If functional onboard a manned VTOL aircraft, an operator or the vehicle health module initiates the emergency landing. Regardless of initiation, the emergency landing system controls, or provides guidance for manned control of, the VTOL aircraft from the point of initiation through touchdown at a threat differentiated preferred LZ via failure-based flight control inputs for automatic landing, or autonomous autorotation entry, glide, and flare.

Disclosed are methods, systems, and non-transitory computer-readable medium for controlling an automatic descent of a vehicle. For instance, the method may include: determining whether a descent trigger condition is present; and in response to determining the descent trigger condition is present, performing an automatic descent process. The automatic descent process may include: obtaining clearance data from an on-board system of the vehicle; generating a descent plan based on the clearance data, the descent plan including a supersonic-to-subsonic transition and/or a supersonic-descent to a target altitude; and generating actuator instructions to a control the vehicle to descend to the target altitude based on the descent plan.

To provide a structure capable of further improving safety of a device that autonomously moves in an emergency situation. Provided is a circuit including: a report unit configured to report action-allowable time information regarding an action-allowable time to a base station; and an action control unit configured to control an action of a moving object on the basis of an action instruction decided on the basis of the reported action-allowable time information and notified of by the base station and to control an action with reference to a map in which a danger level for each place is defined in an emergency situation.

Provided is a circuit including a report unit that reports action-allowable time information regarding an action-allowable time to a base station, and an action control unit that controls an action of a moving object on the basis of an action instruction. The action instruction is decided on the basis of the reported action-allowable time information and notified of by the base station. The action control unit further controls the action with reference to a map in which a danger level for each place is defined in an emergency situation.

An aerial vehicle is programmed to proceed to a safe landing area upon a loss of GPS signals or other navigational signals. The aerial vehicle is programmed with a location of the safe landing area, and a visual descriptor of a landmark at the safe landing area. The landmark may be any natural or man-made structure or feature associated with the safe landing area, and the visual identifier may be any set of data corresponding to one or more contours, outlines, colors, textures, silhouettes or shapes of the landmark. Upon determining that a GPS position may not be determined, or shortly thereafter, the aerial vehicle proceeds on a course toward the location of the safe landing area, and begins to capture imaging data. The aerial vehicle confirms that it has arrived at the safe landing area upon detecting the visual identifier within the imaging data, and initiates a landing operation.

Systems and methods for determining, prior to deployment of a landing assist device onboard an aircraft, the positions of potential landing sites for the aircraft. The positions of the potential landing sites are determined by a computer based at least in part on respective landing assist device deployment times and current wind data. The computed positions of potential landing sites are received by another computer or processor onboard that aircraft that is configured to control operation of a cockpit display unit within the field of view of the pilot. The display unit displays a map showing the respective positions of the aircraft at the respective landing assist device deployment times and the corresponding respective positions of the potential landing sites.

Disclosed are methods, systems, and non-transitory computer-readable medium for controlling an automatic descent of a vehicle. For instance, the method may include: determining whether a descent trigger condition is present; and in response to determining the descent trigger condition is present, performing an automatic descent process. The automatic descent process may include: obtaining clearance data from an on-board system of the vehicle; generating a descent plan based on the clearance data, the descent plan including a supersonic-to-subsonic transition and/or a supersonic-descent to a target altitude; and generating actuator instructions to a control the vehicle to descend to the target altitude based on the descent plan.

A flight management device for managing a flying device which includes an identification unit configured to identify that the flying device is likely to fall and a communication unit configured to transmit the notification information representing that the flying device is likely to fall to the flight management device together with the position information representing a position in flight when the flying device is likely to fall. a notification unit configured to transmit warning information to a vehicle at a position corresponding to position information when notification information has been received from the flying device in flight.