A system including an aircraft, and a computing system remote from the aircraft. The aircraft includes a sensor, an aircraft component associated with the sensor, a first transmitter, and a first receiver. The computing system includes a processor, a second transmitter, and a second receiver. The aircraft transmits sensor data sensed by the sensor to the computing system. The computing system is configured to process the received sensor data to generate status data indicative of an operational mode of the aircraft component, and to transmit, when the status data is indicative of an altered operational mode of the aircraft component, the status data to the aircraft via the second transmitter. The aircraft is configured to indicate, based at least partially on the status data received by the first receiver, the altered operational mode of the aircraft component.

Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing a Runway Awareness Advisory System (RAAS) envelope for the designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter of the RAAS envelope is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter of the RAAS envelope is decreased. Otherwise, an alert is generated if the aircraft is outside of the RAAS envelope.

An impact detection device includes an impact detector, a wireless communication device, an energy storage device, an autonomous electrical energy generation device, a device for receiving energy by radio frequency, the device being configured to adopt the following two modes: a first mode, referred to as autonomous mode, in which the autonomous electrical energy generation device is configured to supply the impact detector and the wireless communication device; a second mode, referred to as external mode, in which the device for receiving energy by radio frequency is configured to supply the impact detector and the wireless communication device.

A method of monitoring the condition of an aircraft landing gear shock absorber, the shock absorber including at least one spring chamber containing a gas, the method comprising taking a plurality of measurements of the gas pressure and temperature, each gas pressure and temperature measurement pair being taken of at the same instant relative to an operating cycle of the shock absorber; calculating, based on each pair of gas pressure and temperature measurements, a first value; storing the first value in a log; determining a value trend based on the log; and in response to determining that the value trend is outside a first range of values, generating a first notification signal.

This application discloses a drone control method and device and a drone and pertains to the technical field of drone control. The method includes: monitoring a running status of each power motor in a drone; determining according to the running status of each power motor whether the drone is in a crashed state; and controlling the drone to alarm when determining that the drone is in the crashed state. The drone control method and device and the drone can rapidly locate a crashed drone, greatly increasing the probability of finding back the crashed drone.

A hard landing indicator mountable to a landing gear of an aircraft is provided. The landing gear has components displaceable toward each other upon the aircraft experiencing a landing. The hard landing indicator includes a first portion securable to one of these components and a second portion that projects outwardly from the first portion and oriented toward another component of the landing gear to be positioned within a path of displacement of the second component toward the first component. The second portion is impacted by this component upon this component being displaced during a hard landing of the aircraft. The impact leaves a visual mark on the second portion of the hard landing indicator to indicate that a hard landing has occurred. A landing gear equipped with and a method of installing such indicator are also provided.

The methods and systems provide for increasing the accuracy of aircraft weight and center of gravity determination through the use of filtered strut pressure measurements. Aircraft vertical and horizontal accelerations are determined as the aircraft is taxiing, and used to identify and reduce the number of significantly distorted pressure measurements, to allow the lesser distorted pressure measurements to be averaged, and a lesser number of distorted pressure measurements to be averaged; further identifying the aircraft in near-neutral acceleration and strut pressure values near-neutral of strut seal friction distortions. Pressure sensors, accelerometers, and an inclinometer are mounted in relation to landing gear struts to monitor, measure and record strut pressure as related to strut telescopic movement, rates of strut telescopic movement and aircraft vertical and horizontal accelerations; experienced by landing gear struts, as the aircraft proceeds through typical ground and taxi operations.

Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing an altitude parameter and a safety envelope for a designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter is decreased. Otherwise, an alert is generated if the aircraft is outside of the safety envelope.

A flight condition determination device, in particular for autonomous use in an aircraft without connection to avionics systems, includes a housing, a triaxial acceleration sensor installed in the housing, a processor, which is coupled to the triaxial acceleration sensor and installed in the housing, a working memory coupled to the processor, and a power supply unit integrated in the housing, having a power supply socket, via which the flight condition determination device is connectable to an electrical energy supply source of an aircraft. The processor is configured to evaluate acceleration values continuously received from the triaxial acceleration sensor and to determine a flight condition signal from the evaluated acceleration values.

A measuring system and method that computes and analyzes sensor data fused with multiple mechanical and thermally induced strain measurements is provided. Further, the measuring system and method realizes physics-based relations between sensor readings due to mechanical and thermal sources by optimally de-coupling a total strain into its mechanical and thermal components. The measuring system and method also auto-tunes coefficients involved in the optimal de-coupling equations using sensor specification data and previous system test results for initialization.