Link component for aircraft engine mounting systems

A link (34) for use in an aircraft engine mounting system includes a span section (38) having a first connector (40) formed at one end thereof and a second connector (40) formed at another end thereof. A lumped mass (46) is disposed on the span section (38) for placing the resonant frequency of the...

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Bibliographische Detailangaben
Hauptverfasser:	FRANCESCHELLI, ANTHONY JOHN, BOGER, ETHAN, TROUP, ROBERT EUGENE, MANTEIGA, JOHN ALAN, WILUSZ, CHRISTOPHER JAMES, DYKHUIZEN, CORNELIUS HARM, JOSEPH, THOMAS PETER
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MEANS FOR DAMPING VIBRATION MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS SHOCK-ABSORBERS SPRINGS STEAM ENGINES THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A link (34) for use in an aircraft engine mounting system includes a span section (38) having a first connector (40) formed at one end thereof and a second connector (40) formed at another end thereof. A lumped mass (46) is disposed on the span section (38) for placing the resonant frequency of the link (34) away from engine excitation frequencies.