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System and method for determining local accelerations, dynamic load distributions and aerodynamic data in an aircraft

A technology of aerodynamics and load distribution, applied in general control systems, control/regulation systems, instruments, etc., can solve the problems of uncertain transmission of aerodynamic data, small physical accuracy, etc., to avoid vibration critical state, reduce Effect of small fatigue loads, design optimization avoidance

Inactive Publication Date: 2012-05-16
AIRBUS OPERATIONS GMBH
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Problems solved by technology

Of course the method described in DE 10 2005 058 081 A1 has the disadvantage that aerodynamic data containing important forces for the load distribution are not determined or transmitted, so the physical accuracy of this common method is relatively small, especially at the beginning of new aircraft types A system as modified here is used for systematic geophysical structural load identification during flight tests of

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  • System and method for determining local accelerations, dynamic load distributions and aerodynamic data in an aircraft
  • System and method for determining local accelerations, dynamic load distributions and aerodynamic data in an aircraft
  • System and method for determining local accelerations, dynamic load distributions and aerodynamic data in an aircraft

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Embodiment Construction

[0026] as from figure 1 It can be seen that the motion of the aircraft can be described by means of eigenvalues. Furthermore, flight mechanics describe the properties of an aircraft which moves in the atmosphere by means of aerodynamics. Flight mechanics describe the overall system or the behavior of the aircraft, the position, flight state and flight speed of the flying body being calculated at any point in time. This is achieved by means of equations of motion which form a system of coupled differential equations. Gust loads and structural loads occur on aircraft due to flight gusts and air turbulence. The gust loads can be described by means of non-linear equations of motion and based on a database which gives the aerodynamic forces. Especially in large aircraft the elastic deformation of the structure must be taken into account in addition to the nonlinear motion.

[0027] The motion of a rigid plane can be described by system values. Every three such values ​​are com...

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Abstract

The invention creates a method and a system (1) for the integrated determination of aerodynamic data, dynamic load distributions and local accelerations in an aircraft, in particular in an airplane, in flight. Sensors (2) for directly and indirectly detecting aerodynamic parameters, local acceleration and / or structural loads of the aircraft are provided at the aircraft. A calculation unit (3), which is provided within the aircraft or at the ground station, calculates based on a non-linear simulation model of the aircraft the aerodynamic data, local accelerations and dynamic load distributions of the aircraft depending on the detected aerodynamic parameters of the aircraft. The calculation may take place in real time.

Description

technical field [0001] The invention relates to a system and a method for the integrated determination of local accelerations (as indicators for comfort and passenger safety), dynamic load distribution and aerodynamic data of an aircraft, in particular an aircraft, during flight. Background technique [0002] Air vehicles, such as airplanes or helicopters, are subject to different forces in their flight. Important influencing values ​​are the buoyancy forces generated by the pressure-bearing surfaces, the aerodynamic drag of the aircraft, the gravitational force acting on the aircraft center of gravity, system forces such as thrust generated by the drive system or by the control surfaces of the aircraft or by on-board systems or The control force produced by the drive system and the torque induced by each force. Local and global mass properties, structural damping and structural stiffness of the aircraft component or the entire aircraft play a role in the overall force bala...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04G05D1/08
CPCG05B13/04
Inventor 米夏埃尔·科尔特马里安尼·雅科巴·莱耶科尔克
Owner AIRBUS OPERATIONS GMBH
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