Structure, suspension system, engine assembly and aircraft
A technology of structure and aircraft, applied in the field of aircraft, can solve the problems of increased fairing disassembly/installation, local stress concentration, complex operation, etc., achieve low processing accuracy, reduce overall weight, and reduce overall weight.
Pending Publication Date: 2020-03-27
AIRBUS BEIJING ENG CENT
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Problems solved by technology
This makes the heat protection panel not able to expand freely when subjected to high temperature, so it may generate high-intensity thermal stress, which may lead to local stress concentration
[0008] In addition, the rigid connection of the existing technology may cause the vibration generated when the base plate is subjected to the high temperature jet of the engine to be directly transmitted to the adjacent structure
[0009] In particular, in most cases, the heat protection panels are rigidly connected to the main body of the fairing by fasteners such as rivets, which requires the installation of a large number of fasteners, thereby generating a large weight and increasing the cost of the fairing. The complexity of removal / installation of
[0010] It is also known to those skilled in the art that when the floor or any other structure in the rear hanger fairing needs to be repaired or replaced, the operation is complicated and thus leads to higher costs
Method used
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[0050] The invention will be described in detail below by means of exemplary embodiments with reference to the drawings. The following detailed description of the present invention is for the purpose of illustration only, and in no way limits the present invention and its application or use.
[0051] The terms first, second, third, etc. are used herein to describe various elements, components, regions, layers and / or sections, but these elements, components, regions, layers and / or sections should not be referred to by these terms. restricted. These terms may be only used to distinguish one element, component, region, layer or section from another element, component, region, layer or section. Terms such as "first," "second," and other numerical terms do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without dep...
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The present invention provides a structure of an aircraft (in particular, a rear pylon fairing), the structure comprising: a fixing member; a plate-shaped member which is an outer member of the structure; and a plurality of connection units, with each of the plurality of connection units hingedly connecting the plate-shaped member to the fixing member, in which the plurality of connection units collectively achieve reliable connection of the plate-shaped member and the fixing member so that the structure forms a geometrically invariant structure. The invention further provides a suspension system comprising the structure body, an engine assembly and an aircraft. According to the invention, the reliable connection mode is provided. A bottom plate of a rear hanging bracket fairing is allowedto freely expand without influencing other parts, so that the thermal stress level of the bottom plate is effectively reduced, the good aerodynamic performance of the whole fairing is maintained, thestructural weight is reduced, and the rear hanging bracket fairing has the advantages of reducing the cost, simplifying the structure, being convenient to install and maintain and the like.
Description
technical field [0001] The invention relates to the field of aircraft, in particular to a rear pylon fairing with a statically determinate connection, a suspension system, an engine assembly and an aircraft. [0002] More particularly, it relates to the connection of a panel in an aircraft, where the panel may be the outermost member of a structure (in particular, the outermost member of an aircraft), or is in use relative to the surrounding structure It has a large amount of deformation, or it has the requirements of light weight, low cost, easy disassembly and maintenance, etc. Background technique [0003] In aircraft engineering, external panels are mainly fixed by rigid connections. As a typical form of rigid connection, the connection by means of fasteners such as screws and rivets has been widely used in the fixing of aircraft structures. However, in an application environment such as an aircraft, which has strict requirements on weight, precision, cost and maintena...
Claims
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IPC IPC(8): B64D27/26B64D29/02B64D29/06B64D27/40
CPCB64D29/02B64D29/06B64D27/404B64D27/40B64D27/18B64D33/04B64C7/00Y02T50/40B64D27/402
Inventor 郭立黄玉昆
Owner AIRBUS BEIJING ENG CENT