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Modeling and testing of hinged flight control surfaces of aircraft

A control surface and aircraft technology, applied in the field of flight control surfaces, can solve the problems of time-consuming and expensive development and use

Active Publication Date: 2019-07-23
BOMBARDIER INC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The development and use of a physical test harness representing the actual structure can also be time consuming and expensive

Method used

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  • Modeling and testing of hinged flight control surfaces of aircraft
  • Modeling and testing of hinged flight control surfaces of aircraft
  • Modeling and testing of hinged flight control surfaces of aircraft

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Embodiment Construction

[0112] The following disclosure relates to the design and testing of a system including articulated flight control surfaces for an aircraft. The apparatus and methods disclosed herein employ a structural model that represents the structural environment of a system in a relatively simple manner while providing sufficient accuracy for certain purposes such as modeling and testing. For example, in some embodiments, the structural models disclosed herein can be adapted to model the static and dynamic performance of a system to facilitate tasks such as system identification, servo loop design, performance and stability assessment. In some embodiments, the simplicity and accuracy of the structural models disclosed herein can facilitate analytical studies and numerical simulations of systems. Additionally, in some embodiments, the structural models disclosed herein may be used as a specification for fabricating a suitable physical test harness for testing a system or components there...

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Abstract

Methods and systems relating to the design and testing of systems that include hinged flight control surfaces of aircraft are disclosed. The systems and methods disclosed herein make use of a structural model representing a structural environment of the system in a relatively simple manner. In various embodiments, the structural model comprises one or more actuation branches having a common linearactuation direction, a load mass, and a massless connector representative of a hinge line of the flight control surface. The massless connector is connected to and disposed between the one or more actuation branches and the load mass and is movable along the common linear actuation direction so that linear movement of the massless connector is correlated to rotational movement of the hinged flight control surface.

Description

[0001] Cross References to Related Applications [0002] This International PCT Patent Application relies on the priority of U.S. Provisional Patent Application No. 62 / 437,156, filed December 21, 2016, which is hereby incorporated by reference in its entirety. technical field [0003] The present disclosure relates generally to aircraft flight control surfaces, and more particularly to the design and testing of systems that include aircraft flight control surfaces. Background technique [0004] The design and testing of actuation systems for flight control surfaces of aircraft may involve the development of virtual finite element models for modeling aspects of such systems, and also involve the development of virtual finite element models for testing components of such systems. Development of physical test harnesses. Finite element structural models may contain a large number of nodes and associated parameters, and accordingly may be relatively complex and time-consuming to...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCB64F5/60B64C9/02B64C13/00G06F30/15G06F30/20G06F2113/28
Inventor 克洛德·泰西耶加布里尔·默尼耶
Owner BOMBARDIER INC
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