A method for continuous in-flight management of a beam generator on board an aircraft, the aircraft comprising the beam generator, sensors, a calculator and a display device. After continuously acquiring a value of at least one parameter of the beam generator and a value of at least one parameter of the aircraft by means of the sensors, a step of continuously estimating a piece of information relating to the reliability of the beam generator over a predetermined time period is carried out using the calculator, as a function, at the very least, of the successive values of the parameters of the beam generator and the aircraft as well as data from a history of the beam generator. Finally, at least one indication relating to the beam generator and depending on the piece of information is displayed on the display device.

A system for impact detection capabilities includes a flight controller, wherein the flight controller is configured to receive an operational datum of a lift component as a function of a sensor, determine an impact element associated to the lift component, wherein determining the impact element further comprises receiving an expected datum, and determining the impact element as a function of the operational datum and the expected datum using an impact threshold, identify a corrective action as a function of the impact element, and transmit the corrective action to the lift component using an autonomous function.

A device attachable to an aerial vehicle that incorporates electronics to control sensor position data and verify safety of aerial vehicle landing area. The device may be easily attached to an existing aerial vehicle. The device monitors sensor data from one or more distance measuring sensors and pressure sensors to set an angle of incidence for the distance measuring sensors. This pressure sensor derived angle setting allows for a continual data mapping of the aerial vehicles landing area to enhance and improve the landing zone.

An aircraft tail skid energy absorption indicator including a crushable indicator cartridge disposed within the an outer shock absorber canister of the aircraft tail skid, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit, where the indicator rod extends through an aperture in a wall of the outer shock absorber canister, where the indicator rod includes at least one graduation that indicates an amount of remaining energy absorption of the aircraft tail skid energy absorption indicator.

The present invention realizes a medical material transport system that is low-cost, stable, and safe, the medical material transport system being such that even if a failure occurs in an individual specimen transport device, the failure does not extend to the system as a whole. Collection of a specimen is requested from a specimen collection request terminal 107, and a management unit (108) issues a reception command 110 for the specimen. A drone 101 that has received the reception command 110 for the specimen departs from a standby dock 105 on the basis of the received information and flies to a specimen recovery location 106, and a specimen tray for placing the specimen is taken out from a specimen holder 102. A specimen container is contained in the specimen tray, and the specimen tray is returned to the specimen holder 102 and locked using a lock mechanism. The drone 101 flies to an arrival station 104, and after arriving, uses an unlocking key, and the specimen tray is disengaged from the specimen holder 102. After the specimen container in the specimen tray is collected, the specimen tray is placed in the specimen holder 102, and the drone 101 returns to the standby dock 105.

A landing assembly and method of landing an aircraft. The landing assembly includes a landing gear, a charging circuit, a sampling circuit and a processor. The charging circuit applies a charge to the landing gear and the sampling circuit measures a discharge rate of the electrical charge from the landing gear. The processor determines a contact between the landing gear and a surface from the discharge rate.

The invention relates to a signal generator for unmanned aircraft comprising at least one light source and/or at least one sound source and at least one regulator/control for actuating the at least one source.

An aircraft undercarriage comprising a shock absorber further comprising first and second portions that are mounted to slide telescopically relative to each other and that can come into internal abutment in the event of the shock absorber being compressed, the undercarriage being fitted with a detector device for detecting the shock absorber coming into internal abutment, which comprises firstly a punch secured to the first portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the first portion of the shock absorber, and secondly a sacrificial piece secured to the second portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the second portion of the shock absorber, the punch and the sacrificial piece being arranged in such a manner that, in the event of the two portions of the shock absorber coming into internal abutment, the punch strikes the sacrificial piece so as to form an indentation therein.

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.

An apparatus for monitoring a tire and/or a wheel including a sensor system; a wireless communication interface; a processor connected to the sensor system and the wireless communication interface; a power source; and a mounting system for attaching the apparatus to a wheel. The mounting system is configured to allow movement of the sensor system relative to the wheel in use.