Static test supporting piece for aircraft fairing

Abstract

The utility model belongs to the technical field of aviation, and relates to an aircraft fairing static test supporting piece which comprises a lower supporting piece, a lower transition piece, a side transition piece and a side supporting back plate, the lower transition piece is arranged on the surface of the lower supporting piece and connected with the lower portion of an aircraft fairing, the side transition piece is vertically arranged on the lower supporting piece, and the side supporting back plate is arranged on the side transition piece. The side transition piece is located at one end of the lower transition piece and is supported by a side supporting back plate, and the top profile of the side transition piece is matched with the inner profile of the root of the aircraft fairing; the device is used for supporting and fixing the aircraft fairing in the static test of the triangular-structure aircraft fairing, and is high in bearing capacity, convenient to disassemble and assemble, high in material utilization rate and capable of reducing expenditure.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the aviation technology field relates to a kind of aircraft fairing static test supporting element, and the static test piece of aircraft fairing is supported and fixed. BACKGROUND

[0002] The holding edge of general fairing is annular, and the supporting tool is correspondingly provided as an integral annular supporting element. However, the fairing of a certain aircraft is in a right triangle structure, and the size is large. If the real load state on the aircraft is simulated, a real body mechanism is generally combined as a support to perform a test, or two right-angle edges are clamped to perform a test. If the supporting tool is directly used as an integral right-angle supporting tool, the material utilization rate is low, and the cost is too high. UTILITY MODEL CONTENT

[0003] The utility model solves the technical problem: the utility model overcomes the insufficient in the prior art, provides a kind of aircraft fairing static test supporting element, for when the support and fixed of its in triangular structure aircraft fairing static test, carrying capacity is stronger, easy to disassemble and assemble, material utilization rate is high, reduces fund.

[0004] TECHNICAL SCHEME

[0005] An aircraft fairing static test supporting element includes a lower supporting element, a lower transition element, a side transition element and a side supporting back plate. The lower transition element is arranged on the surface of the lower supporting element and connected with the lower part of the aircraft fairing. The side transition element is vertically arranged on the lower supporting element and located at one end of the lower transition element, and is supported by the side supporting back plate. The top surface of the side transition element is matched with the inner surface of the root part of the aircraft fairing.

[0006] Further, the lower transition element is horizontally arranged on the lower supporting element and includes an upper panel and a lower panel. The upper and lower panels are connected by a plurality of vertical ribs.

[0007] Further, the upper panel and the lower panel are both provided with connecting holes. The upper panel is matched with the lower flange of the aircraft fairing and connected by bolts. The lower panel is matched with the lower supporting element and connected by bolts.

[0008] Further, the side transition element is vertically arranged on the lower supporting element and includes a curved profile plate and a bottom plate. The bottom plate is arranged at the bottom of the curved profile plate, and the curved surface of the curved profile plate is matched with the inner surface of the side of the fairing.

[0009] Further, the side supporting back plate is arranged on the side of the side transition element away from the lower transition element. One end of the side supporting back plate is connected with the side transition element, and the other end is connected with the lower supporting element.

[0010] Further, the side support back plate comprises an I-shaped plate and two I-shaped long inclined rods, one side of the I-shaped plate is connected with the side transition piece, and the other side is connected with one end of the I-shaped long inclined rod, and the other end of the I-shaped long inclined rod is supported on the upper surface of the lower support piece.

[0011] Advantages

[0012] The utility model provides a kind of airplane fairing static test support, for supporting and fixing when the static test of triangular structure airplane fairing, it is a kind of static test support tool for airplane fairing, adopt multi-section, static test support tool of shape combination, carrying capacity is stronger, it is easy to disassemble and assemble, material utilization is high, reduce expenses. BRIEF DESCRIPTION OF DRAWINGS

[0013] Fig. 1 It is the support tool schematic diagram for the static test of fairing;

[0014] Fig. 2 It is the schematic diagram of triangular structure airplane fairing;

[0015] Fig. 3 It is the sectional view of triangular structure airplane fairing.

[0016] Wherein: 1, lower support piece, 2, lower transition piece, 3, side transition piece, 4, side support back plate, 5, airplane fairing lower edge, 6, airplane fairing root inner surface, 7, I-shaped plate, 8, I-shaped long inclined rod. DETAILED DESCRIPTION

[0017] The features and illustrative examples of the various aspects of the present application will be described below in detail. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be apparent to one skilled in the art that the present application can be practiced without some or all of these specific details. The description of the embodiments is merely meant to provide a better understanding of the present application. The present application is not limited to any particular specific details in the following description, but covers any modifications, equivalents, and alternatives falling within the spirit of the present application. In the drawings and the following description, well-known structures and techniques are not shown in order to avoid unnecessary obscurity of the present application.

[0018] It should be noted that the features of the embodiments of the present application and the embodiments can be combined with each other without conflict, and each embodiment can be mutually referenced and quoted. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0019] As Figs. 1-3The utility model provides a kind of aircraft fairing static test support shown, including lower support 1, lower transition piece 2, side transition piece 3, side support backplate 4, the lower transition piece 2 is set on the surface of lower support 1, is connected with aircraft fairing lower part, the side transition piece 3 is vertically set on lower support 1, is located lower transition piece 2 one end, and is supported by side support backplate 4, the side transition piece 3 top profile surface is cooperated with aircraft fairing root inner profile 6.

[0020] Wherein, the lower transition piece 2 is transversely placed on the lower support 1, including upper panel and lower panel, the upper and lower panel is connected by multiple vertical ribs;The upper panel and lower panel are provided with connecting holes, the upper panel is attached with aircraft fairing lower part flanging 5, and is connected by bolt, the lower panel is attached with lower support 1 and is connected by bolt.

[0021] Wherein, the side transition piece 3 is vertically arranged on the lower support 1, including curved profile plate and bottom plate, the bottom plate is arranged at the bottom of the curved profile plate, and the arc surface of the curved profile plate is attached with the fairing side root inner profile 6;The side of the side transition piece 3 away from the lower transition piece is provided with the side support backplate 4, one end of the side support backplate 4 is connected with the side transition piece, and the other end is connected with the lower support 1;The side support backplate 4 includes I-shaped plate 7 and two I-shaped inclined long rods 8, one side of the I-shaped plate 7 is attached with the side transition piece 3, the other side is connected with one end of the I-shaped inclined long rod 8, and the other end of the I-shaped inclined long rod 8 is inclinedly supported on the upper surface of the lower support 1.

[0022] The lower support 1, the lower transition piece 2, the side transition piece 3 and the side support backplate 4 are connected with each other, to form the support for the static test of the entire fairing.

[0023] Finally, it should be noted that: the above examples are only used to illustrate the technical scheme of the utility model, but the protection scope of the utility model is not limited to this, any skilled person in the art can easily think of various equivalent modifications or replacements within the technical range disclosed by the utility model, and these modifications or replacements should be covered in the protection scope of the utility model.

Claims

1. An aircraft cowling static test support, comprising: The lower support, the lower transition piece, the side transition piece and the side support back plate are provided.

2. The aircraft static test support of Claim 1, wherein, The lower transition piece is horizontally arranged on the lower support and comprises an upper panel and a lower panel.

3. The aircraft static test support of Claim 2, wherein, The upper panel and the lower panel are provided with connecting holes.

4. The aircraft static test support of Claim 3, wherein, The side transition piece is vertically arranged on the lower support and comprises a curved profile plate and a bottom plate.

5. The aircraft static test support of Claim 4, wherein, The side support back plate is provided on the side away from the lower transition piece.

6. The aircraft static test support of Claim 5, wherein, The side support back plate comprises an I-shaped plate and two I-shaped long inclined rods.

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