Integrated mounting bracket for main-standby brake integrated control valve of airplane

Abstract

The utility model belongs to the field of structural design of mounting brackets, and particularly relates to an integrated mounting bracket for a main-standby brake integrated control valve of an airplane. A plurality of mounting holes for bolt assembly are formed in a structure mounting panel, and the structure mounting panel is provided with a mounting surface front side and a mounting surface back side; the supports are provided with first connecting parts and second connecting parts, the first connecting parts are fixedly mounted on the back side of the mounting surface of the structure mounting panel through bolts, and the second connecting parts are fixedly mounted on the machine body through bolts; the double-lug supporting plate nuts are fixedly installed on the back side of the installation face of the structure installation panel through screws, and the main-standby brake integrated control valve is fixedly installed on the front side of the installation face of the structure installation panel through the cooperation of the double-lug supporting plate nuts and the bolts. Installation of the main brake integrated control valve and the standby brake integrated control valve is integrally designed, installation is flexible, the needed installation space is small, the weight is reduced, the installation flatness is good, and the MTBS index of the system is increased.

Description

Technical Field

[0001] The present application relates to the field of mounting bracket structure design, and in particular to an integrated mounting bracket for an aircraft main-standby brake integrated control valve. Background Art

[0002] Aircraft braking systems are crucial to aircraft safety. Depending on the aircraft model or airworthiness requirements, a primary and backup brake system must be installed to meet the aircraft's normal operating requirements. The backup system's fundamental function is to replace the primary system in the event of a failure or performance degradation. However, due to factors such as aircraft structural characteristics, installation space limitations, and installation flatness requirements, it is not possible to install the primary and backup brake integrated control valves on two brackets. Instead, they must be installed on a single bracket. This necessitates a special bracket for mounting the primary and backup brake integrated control valves, making the mounting bracket for the primary and backup brake integrated control valves extremely important.

[0003] The current design of the mounting bracket for the master-slave integrated control valve still has problems such as inflexible installation, large space occupied, heavy weight, and poor installation flatness.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned deficiencies of the prior art. Utility Model Content

[0005] The purpose of the present application is to provide an integrated mounting bracket for an aircraft main-standby brake integrated control valve to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] An integrated mounting bracket for an aircraft main and standby brake integrated control valve, comprising:

[0008] A structural mounting panel, wherein the structural mounting panel is provided with a plurality of mounting holes for bolt assembly, and the structural mounting panel has a front mounting surface side and a back mounting surface side;

[0009] The supports include a plurality of supports, each having a first connecting portion and a second connecting portion, wherein the first connecting portion is fixedly mounted on the back side of the mounting surface of the structural mounting panel by bolts, and the second connecting portion is fixedly mounted on the body by bolts;

[0010] The double-ear support plate nut includes multiple ones, and the double-ear support plate nuts are fixedly installed on the back side of the mounting surface of the structural mounting panel by screws. The double-ear support plate nuts cooperate with bolts to fix the main-standby brake integrated control valve on the front side of the mounting surface of the structural mounting panel.

[0011] In at least one embodiment of the present application, the panel size and shape of the structural installation panel are adapted to the installation space.

[0012] In at least one embodiment of the present application, the structural mounting panel is T-shaped.

[0013] In at least one embodiment of the present application, the outer edge of the structural mounting panel is provided with a reinforcement edge, and the reinforcement edge extends toward the back side of the mounting surface.

[0014] In at least one embodiment of the present application, the reinforcement edge has a variety of different thickness specifications.

[0015] In at least one embodiment of the present application, a plurality of lightening holes are provided on the structural mounting panel.

[0016] In at least one embodiment of the present application, a wire harness bracket is installed on the front side of the mounting surface of the structural mounting panel, and a wire harness through hole is provided on the wire harness bracket.

[0017] In at least one embodiment of the present application, a pipe bracket is installed on the front side of the mounting surface of the structural mounting panel, and a pipe through hole is opened on the pipe bracket.

[0018] The utility model shall have at least the following beneficial technical effects:

[0019] The integrated mounting bracket of the aircraft main-standby brake integrated control valve of the present application integrates the installation design of the main-standby brake integrated control valve into an integrated manner, is flexible to install, requires a small installation space, reduces weight, has good installation flatness, and increases the MTBS index of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of an integrated mounting bracket for an aircraft main-standby brake integrated control valve according to one embodiment of the present application;

[0021] Figure 2 This is a schematic diagram of the support arrangement of one embodiment of the present application;

[0022] Figure 3 This is a schematic diagram of the support arrangement of another embodiment of the present application;

[0023] Figure 4 This is a schematic diagram of the arrangement of the wiring harness bracket and the pipeline bracket according to one embodiment of the present application.

[0024] in:

[0025] 1-Support; 2-Structural mounting panel; 3-Reinforcement edge; 4-Mounting hole; 5-Lightening hole. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be understood as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0027] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be understood as limiting the scope of protection of this application.

[0028] The following is combined with Figures 1 to 4 This application is described in further detail.

[0029] The present application provides an integrated mounting bracket for an aircraft main-standby brake integrated control valve, comprising: a structural mounting panel 2, a support 1, and a double-ear support plate nut.

[0030] Specifically, such as Figure 1 As shown, the structural mounting panel 2 is provided with a plurality of mounting holes 4 for bolt assembly. The structural mounting panel 2 has a front mounting surface and a rear mounting surface. The size and shape of the structural mounting panel 2 are adapted to the installation space. The plurality of mounting holes 4 are distributed at different locations on the structural mounting panel 2. The arrangement and number of the mounting holes 4 can be designed based on the position of the corresponding support 1 and the master-slave integrated brake control valve, facilitating the installation of the support 1 and the master-slave integrated brake control valve via bolts.

[0031] The brackets 1 comprise multiple components, each having a first connecting portion and a second connecting portion. The first connecting portion is bolted to the back of the mounting surface of the structural mounting panel 2, while the second connecting portion is also bolted to the fuselage. The brackets 1 secure the structural mounting panel 2 to the fuselage structure and can be added, removed, or modified to suit the onboard installation environment, depending on the mounting area, space available, and installation requirements. They offer flexible installation, ease of construction, and minimal space constraints.

[0032] There are multiple double-ear support plate nuts, which are fixed on the back side of the mounting surface of the structural mounting panel 2 by screws. The main-standby brake integrated control valve is fixed on the front side of the mounting surface of the structural mounting panel 2 by the double-ear support plate nuts and bolts.

[0033] In a preferred embodiment of the present application, the structural mounting panel 2 designed according to the installation space is T-shaped, and a reinforcing edge 3 is preferably provided at the outer edge of the structural mounting panel 2. The reinforcing edge 3 extends toward the back side of the mounting surface to ensure the flatness of the front side of the mounting surface of the structural mounting panel 2. The reinforcing edge 3 can enhance the rigidity of the structural mounting panel 2. The reinforcing edge 3 is designed to have a variety of different thickness specifications, and the reinforcing edge 3 can be thickened or thinned according to the rigidity to meet the rigidity requirements under different stress conditions.

[0034] In a preferred embodiment of the present application, taking into account the weight reduction requirements of aircraft, lightening holes 5 are designed on the structural mounting panel 2 to reduce the overall weight of the bracket. In this embodiment, three lightening holes 5 are opened on the T-shaped structural mounting panel 2, which are adapted to the size and shape of the panel.

[0035] The integrated mounting bracket of the aircraft main-standby brake integrated control valve of the present application can increase, decrease or modify the bracket 1 according to the actual situation in the subsequent work when a certain bracket 1 in the bracket fails, so that two systems with multiple mounting points are arranged at the same time, ensuring that when any one of the systems fails, the other system can work stably and reliably, such as Figure 2 、 Figure 3 shown.

[0036] The integrated mounting bracket of the aircraft master-standby brake integrated control valve of the present application can also be arranged on the structural mounting panel 2 with other wiring harness brackets and pipe brackets in addition to the master-standby brake integrated control valve, thus achieving multiple uses on one panel. The wiring harness bracket and pipe bracket are respectively installed at appropriate positions on the structural mounting panel 2 and cannot interfere with the installation of the master-standby brake integrated control valve. In the preferred embodiment of the present application, if Figure 4 As shown, a wire harness bracket and a pipe bracket are mounted on the front side of the mounting surface of the structural mounting panel 2. In this embodiment, the wire harness bracket comprises a first wire harness bracket portion and a second wire harness bracket portion. The first wire harness bracket portion is welded to the structural mounting panel 2, and the second wire harness bracket portion is screwed to the first wire harness bracket portion. A wire harness through hole is formed between the first and second wire harness bracket portions. One end of the pipe bracket is fixedly connected to the structural mounting panel 2 by bolts, and the other end is provided with a pipe through hole.

[0037] The integrated mounting bracket of the aircraft main-standby brake integrated control valve of the present application is designed as an integrated structure. First, the support 1 is designed as two systems with multiple installation points arranged at the same time to ensure that when any one of the systems fails, the other system can work stably and reliably; secondly, the integrated bracket can avoid the problems of two independent brackets occupying a large space, being heavy, and having poor installation flatness, which can be avoided through conscious arrangement; thirdly, the layout of the support 1 can be designed according to the different shapes and different spaces of the installation part of the body structure. The integrated structural mounting panel 2 cooperates with the independent support 1 to make the installation method and installation sequence of the bracket flexible and changeable, and can adapt to different installation layout requirements, so that its installation can be as far as possible without being restricted by the position and installation space; finally, according to the actual layout requirements, other wiring harnesses and pipelines in the same area can be arranged on the structural mounting panel 2, so that one board can be used for multiple purposes and the appearance of too many brackets can be avoided. Through this design, the installation of the main-standby brake integrated control valve can be integrated, the weight can be reduced, and the MTBS index of the system can be increased.

[0038] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An integrated mounting bracket for an aircraft main and standby brake integrated control valve, characterized in that: include: A structural mounting panel (2), wherein a plurality of mounting holes (4) for bolt assembly are provided on the structural mounting panel (2), and the structural mounting panel (2) has a front mounting surface side and a back mounting surface side; The support (1) comprises a plurality of supports, wherein the support (1) has a first connection portion and a second connection portion, wherein the first connection portion is fixedly mounted on the back side of the mounting surface of the structural mounting panel (2) by means of bolts, and the second connection portion is fixedly mounted on the machine body by means of bolts; The double-ear support plate nut comprises a plurality of nuts, the double-ear support plate nuts being fixedly mounted on the back side of the mounting surface of the structural mounting panel (2) by means of screws, and the double-ear support plate nuts cooperating with bolts are used to fix the main-standby brake integrated control valve on the front side of the mounting surface of the structural mounting panel (2).

2. The integrated mounting bracket for the aircraft main and standby brake integrated control valve according to claim 1, characterized in that: The panel size and shape of the structural installation panel (2) are adapted to the installation space.

3. The integrated mounting bracket for the aircraft main and standby brake integrated control valve according to claim 2, characterized in that: The structural mounting panel (2) is T-shaped.

4. The integrated mounting bracket for the aircraft main and standby brake integrated control valve according to claim 1, characterized in that: The outer edge of the structural installation panel (2) is provided with a reinforcement edge (3), and the reinforcement edge (3) extends toward the back side of the installation surface.

5. The integrated mounting bracket for the aircraft main and standby brake integrated control valve according to claim 4, characterized in that: The reinforcing edge (3) has a variety of different thickness specifications.

6. The integrated mounting bracket for the aircraft main and standby brake integrated control valve according to claim 1, characterized in that: A plurality of lightening holes (5) are provided on the structural mounting panel (2).

7. The integrated mounting bracket for the aircraft main and standby brake integrated control valve according to claim 1, characterized in that: A wiring harness bracket is installed on the front side of the installation surface of the structural installation panel (2), and a wiring harness through hole is provided on the wiring harness bracket.

8. The integrated mounting bracket for the aircraft main and standby brake integrated control valve according to claim 7, characterized in that: A pipeline bracket is installed on the front side of the installation surface of the structural installation panel (2), and a pipeline passing hole is opened on the pipeline bracket.

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