System and method for determining distance in navigation of an electric aircraft is illustrated. The system and method comprise a sensor and a computing device. The sensor is configured to detect a surface and transmit at least a first signal and a first frequency and at least a second signal at a second frequency to a computing device, wherein the first signal and the second signal comprise a corresponding distance. The computing device is configured to receive a returned signal from the sensor, wherein the returned signal comprises an intermodulation product associated to the first signal and the second signal, detect an amplitude of the returned signal as a function of the frequency, identify a distance datum as a function of the amplitude and an amplitude threshold, determine an aircraft adjustment as a function of the distance datum, and transmit the distance datum and aircraft adjustment to a remote device.

System and method for determining distance in navigation of an electric aircraft is illustrated. The system and method comprise a sensor and a computing device. The sensor is configured to detect a surface and transmit at least a first signal and a first frequency and at least a second signal at a second frequency to a computing device, wherein the first signal and the second signal comprise a corresponding distance. The computing device is configured to receive a returned signal from the sensor, wherein the returned signal comprises an intermodulation product associated to the first signal and the second signal, detect an amplitude of the returned signal as a function of the frequency, identify a distance datum as a function of the amplitude and an amplitude threshold, determine an aircraft adjustment as a function of the distance datum, and transmit the distance datum and aircraft adjustment to a remote device.

Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.

A cooling system for cooling electronic aircraft equipment comprises a primary cooling arrangement configured to provide basic cooling energy for cooling the electronic aircraft equipment and a supplemental cooling arrangement configured to provide supplemental cooling energy for cooling the electronic aircraft equipment. The supplemental cooling arrangement comprises a coolant supply system and a coolant distribution system. The coolant supply system is configured to supply a compressed coolant to the electronic aircraft equipment to be cooled, and the coolant distribution system is configured to selectively direct the compressed coolant supplied by the coolant supply system to at least one of a plurality of components of the electronic aircraft equipment.

A cooling system for cooling electronic aircraft equipment comprises a primary cooling arrangement configured to provide basic cooling energy for cooling the electronic aircraft equipment and a supplemental cooling arrangement configured to provide supplemental cooling energy for cooling the electronic aircraft equipment. The supplemental cooling arrangement comprises a coolant supply system and a coolant distribution system. The coolant supply system is configured to supply a compressed coolant to the electronic aircraft equipment to be cooled, and the coolant distribution system is configured to selectively direct the compressed coolant supplied by the coolant supply system to at least one of a plurality of components of the electronic aircraft equipment.

A device may receive equipment information, associated with a first equipment, including information associated with anomalies identified based on operational information collected during operation of the first equipment, and messages generated during the operation of the first equipment. The device may receive maintenance information, associated with the first equipment, that identifies one or more part failures associated with one or more equipment parts. The device may identify associations between the one or more part failures and the first equipment information. The device may receive equipment information, associated with a second equipment, including information associated with anomalies identified based on operational information collected during operation of the second equipment, and messages generated during the operation of the second equipment. The device may generate and provide a prediction, associated with a future failure of an equipment part of the second equipment, based on the second equipment information and the associations.

An aircraft includes an engine and a system that is configured to detect an event associated with the engine during a take-off. The system is further configured to determine a speed of the aircraft a particular time after the event and to determine a remaining distance between the aircraft and an end of a runway at the particular time. The system is also configured to compare the speed of the aircraft to a take-off rejection speed threshold. The take-off rejection speed threshold indicates a maximum aircraft speed that would result in the aircraft stopping prior to a particular distance from the end of the runway. The take-off rejection speed threshold is selected from a plurality of aircraft speeds generated during aircraft deceleration simulations. The system is also configured to generate an indication recommending whether to continue the take-off based on comparison.

An aircraft includes an engine and a system that is configured to detect an event associated with the engine during a take-off. The system is further configured to determine a speed of the aircraft a particular time after the event and to determine a remaining distance between the aircraft and an end of a runway at the particular time. The system is also configured to compare the speed of the aircraft to a take-off rejection speed threshold. The take-off rejection speed threshold indicates a maximum aircraft speed that would result in the aircraft stopping prior to a particular distance from the end of the runway. The take-off rejection speed threshold is selected from a plurality of aircraft speeds generated during aircraft deceleration simulations. The system is also configured to generate an indication recommending whether to continue the take-off based on comparison.

Techniques to deploy a parachute are disclosed. In various embodiments, a first projectile is configured to be propelled in a first direction, causing the parachute to be deployed. A second projectile configured to be propelled in a second direction is coupled to a line tethered to the parachute in such a way that a force in a direction opposite the first direction is applied to the line of the parachute when the second projectile is propelled in the second direction.

A multi-modal aircraft recovery system is disclosed. In various embodiments, the system includes a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions and a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions different from the first.