System and method for compensating structural vibrations of an aircraft caused by outside disturbances
AssigneeDaimlerChrysler AG
InventorJuergen Becker
Life of this patent
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Abstract
Method for compensating structural vibrations of an aircraft caused by wind blasts and buffeting in an aircraft in flight includes the steps of: detecting the structural vibrations by measurement technology using roll rates determined in an inertial sensing system, supplying the determined disturbing values to a flight control system, producing phase- and amplitude-correct control flap movements by generating appropriate control signals in respective control drives to counteract the phases and amplitudes of the excited vibrations.
Claims10
A method for compensating structural vibrations of an aircraft caused by external disturbances acting on the aircraft in flight, the method comprising the acts of:
- detecting the structural vibrations via measurement technology using roll rates determined essentially by an inertial sensing system of the aircraft without requiring additional sensors;
- feeding disturbing parameters of the detected structural vibrations to a flight control system of the aircraft;
- and
- producing phase- and amplitude-correct control flap movements of the aircraft by generating appropriate control signals at respective drives to counteract phases and amplitudes of excited structural vibrations.
A system for compensating structural vibrations of an aircraft excited by wind blasts and buffeting on the aircraft in flight, the system comprising:
- an inertial sensing system of the aircraft, said inertial sensing system determining roll rates of the aircraft and detecting disturbing parameters of exciting structural vibrations using said roll rates essentially determined by the inertial sensing system without requiring additional sensors;
- a flight control system coupled with said inertial sensing system, said disturbing parameters being fed to said flight control system;
- and
- wherein said flight control system processes said disturbing parameters and generates appropriate control signals to produce phase- and amplitude-correct aircraft control flap movements for counteracting phases and amplitudes of the excited structural vibrations.
Dependencies are inferred from the claim text.