ENGINE INLET COVER DETECTION SYSTEM AND METHOD

The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, an engine cover assembly, and a controller. The engine has moving parts a...

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Bibliographische Detailangaben
1. Verfasser:	Hausmann, Jeffrey
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING CALCULATING COMBUSTION ENGINES COMPUTING CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS COUNTING DETECTING MASSES OR OBJECTS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS GEOPHYSICS GRAVITATIONAL MEASUREMENTS HANDLING RECORD CARRIERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MEASURING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS PHYSICS PRESENTATION OF DATA RECOGNITION OF DATA RECORD CARRIERS TESTING TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, an engine cover assembly, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The second sensor component is attached to the engine cover and is configured to interact with the first sensor component. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.