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US 5,167,385 AGranted
Aircraft and system and method for operating thereof
AssigneePfister GmbH
InventorHans W. Hafner
Life of this patent
Estimating the term…
Abstract
An aircraft and a method and system for operating thereof as force/moment sensors integrated in elastic connecting joints of parts and units of the aircraft. The various force/moment components determined by the sensors are processed in order to generate control signals for optimizing the operation of the aircraft.
Claims9
An aircraft having a plurality of essentially rigid parts elastically connected with each other, comprising:
- elastomeric material provided in connecting joints between said rigid parts;
- at least one sensor integrated in said connecting joints for determining forces and/or moments acting at said connecting joints and for generating signals representing said forces and/or moments, wherein said sensors are integrated in connecting joints between struts of a landing gear of said aircraft and a body of said aircraft, further wherein said sensors are integrated in connecting joints incorporated in said struts, and further wherein said sensors are integrated in connecting joints between support bars of said landing gear of said aircraft and said body of said aircraft, said support bars extending at an oblique angle relative to the horizontal.
A system for controlling the operation of an aircraft having a plurality of essentially rigid parts elastically connected with each other, comprising:
- force/moment sensor means integrated in elastic connecting joints between said rigid parts for determining forces and/or moments, respectively, acting at said connecting joints and generating signals representing said forces and/or moments, wherein said force/moment sensors are embedded in elastomeric material in said elastic connecting joints, said elastic connecting joints being incorporated within support elements for supporting a body of said aircraft on landing gear means, wherein at least one of said support elements extends in a vertical direction and at least one of said other support elements extends at an oblique angle relative to said vertical direction;
- and
- a system control unit connected to said sensors for having signals of said sensors applied thereto, evaluating and processing said signals and providing output signals for controlling the operation of various units of said aircraft based on said forces/moment measured by said sensors.
Dependencies are inferred from the claim text.