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A leading edge structure for a flow control system of an aircraft

A technology of airflow control and aircraft, applied in the direction of aircraft control, affecting the air flow flowing through the surface of the aircraft, boundary layer control, etc., can solve the problem of increasing the total weight of the aircraft

Active Publication Date: 2019-01-18
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

known leading edge structures include multiple separate parts that must be fitted together and add to the overall weight of the aircraft

Method used

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  • A leading edge structure for a flow control system of an aircraft
  • A leading edge structure for a flow control system of an aircraft
  • A leading edge structure for a flow control system of an aircraft

Examples

Experimental program
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Embodiment Construction

[0032] figure 1 with figure 2 An embodiment of the leading edge structure 1 of the airflow control system for an aircraft according to the present invention is shown. The front edge structure 1 includes a double-walled front edge plate 3 and a rear wall 5.

[0033] The leading edge plate 1 surrounds the plenum 7 in a curved manner, wherein the plenum 7 extends in the spanwise direction 9. The front edge plate 3 has a first side 11 and an opposite second side 13. The first side portion 11 extends from the front edge point 15 to the first attachment end 17. The second side portion 13 extends from the leading edge point 15 to the second attachment end 19, such as image 3 Shown.

[0034] The rear wall 5 is formed as a film of CFRP material, and connects the first attachment end 17 to the second attachment end 19 of the front edge plate 3. In this way, the rear wall 5 encloses the plenum 7 together with the front edge plate 3 on the side opposite to the front edge point 15.

[0035]...

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PUM

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Abstract

The present invention relates to a leading edge structure (1) for a flow control system of an aircraft, comprising a double-walled leading edge panel (3) that surrounds a plenum (7), wherein the leading edge panel (3) comprises an inner wall element (21) facing the plenum (7) and an outer wall element (23) in contact with the ambient flow (25), wherein between the inner and outer wall elements (21, 23) the leading edge panel (3) comprises a plurality of elongate stiffeners (27) spaced apart from one another, so that between each pair of adjacent stiffeners (27) a hollow chamber (29) is formedbetween the inner and outer wall elements (21, 23), wherein the outer wall element (23) comprises a plurality of micro pores (31) forming a fluid connection between the hollow chambers (29) and an ambient flow (25), and wherein the inner wall element (21) comprises openings (33) forming a fluid connection between the hollow chambers (29) and the plenum (7). The object, to provide a simple and lightweight leading edge structure that meets the mechanic requirements, is achieved in that the stiffeners (27) are formed integrally with the inner wall element (21).

Description

Technical field [0001] The present invention relates to a leading edge structure for an airflow control system of an aircraft, particularly for a mixed laminar flow control system, in which air is sucked or blown out of the porous surface of an airflow member to expand the laminar flow area along the airflow member. Other aspects of the present invention relate to a vertical tail fin including such a leading edge structure, an aircraft including such a leading edge structure or such a vertical tail, and a method for manufacturing such a leading edge structure. [0002] The front edge structure includes a double-walled front edge plate, which surrounds the same plenum in a curved, that is, arcuate manner. The plenum extends through the leading edge structure in the spanwise direction. [0003] When viewed in a cross section across the span direction, the leading edge plate has a first side portion that extends from the leading edge point (ie from the front end of the leading edge st...

Claims

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Application Information

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IPC IPC(8): B64C21/02
CPCB64C21/02B64C3/26Y02T50/10B64C5/02B64C2230/08B64C2230/20B64C2230/22F15D1/12
Inventor 格察·施劳夫克里斯蒂安·哈克
Owner AIRBUS OPERATIONS GMBH