Inertial navigation component mounting structure capable of compensating mounting reference

Abstract

The utility model provides an inertial navigation component mounting structure capable of compensating a mounting reference, and belongs to the technical field of inertial navigation equipment mounting and maintaining.The inertial navigation component mounting structure comprises a mounting support fixed to an aircraft structure through a connecting assembly; the transition plate is fixedly connected with the installation support through a connecting assembly, a positioning assembly is arranged on the transition plate, and an inertial navigation component is installed on the positioning assembly in a matched mode and fixedly connected with the transition plate through the connecting assembly; the strippable gasket is arranged between the mounting bracket and the transition plate, and the mounting direction and position of the inertial navigation component mounted on the transition plate are adjusted through the strippable gasket, so that the inertial navigation component meets the mounting requirement. The installation structure can be applied to installation of various types of aircraft inertial navigation equipment, the installation period and cost of the inertial navigation equipment can be reduced, and the maintainability is improved.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft inertial navigation component installation, and in particular relates to an inertial navigation component installation structure capable of compensating for an installation reference. Background Art

[0002] Inertial / satellite combined navigation systems are crucial for aircraft navigation. INS senses the aircraft's acceleration and angular rate, receives satellite navigation information (BDS, GPS) and atmospheric data from inertial navigation satellite antennas, and outputs information such as the aircraft's position, heading, attitude, velocity, acceleration, angular velocity, satellite altitude, global magnetic variation, and time to relevant equipment for use in aircraft navigation calculations, data display, flight control, parameter recording, and mission execution. The attitude output by the INS is a key input parameter for flight control. Therefore, obtaining accurate INS navigation information is crucial to an aircraft's operational capability and safety.

[0003] In order to obtain high-precision inertial navigation information, the installation accuracy of inertial navigation components is very high during the aircraft production process, and high requirements are placed on the production and manufacturing of the inertial navigation component mounting brackets on the fuselage, resulting in increased production cycle and cost. Utility Model Content

[0004] The purpose of the present application is to provide an inertial navigation component mounting structure capable of compensating for a mounting reference, so as to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: an inertial navigation component installation structure capable of compensating for an installation reference, comprising:

[0006] a mounting bracket, wherein the mounting bracket is fixed to the aircraft structure via a connecting assembly;

[0007] A transition plate, the transition plate being fixedly connected to the mounting bracket via a connecting assembly, wherein a positioning assembly is provided on the transition plate, and the inertial guidance component is cooperatively mounted on the positioning assembly and fixedly connected to the transition plate via the connecting assembly;

[0008] A peelable gasket is provided between the mounting bracket and the transition plate. The peelable gasket is used to adjust the mounting direction of the inertial guide component mounted on the transition plate so that the inertial guide component meets the mounting requirements.

[0009] In an optional embodiment of the present application, the connection assembly bracket mounting bolts, transition plate mounting bolts, transition plate mounting bracket nuts and equipment mounting bolts, equipment mounting bracket nuts;

[0010] The mounting bracket is fixed to the aircraft structure by bracket mounting bolts;

[0011] The transition plate mounting bracket nut is fixed to the mounting bracket by riveting, and the transition plate mounting bolt passes through the mounting bracket and the transition plate to fix the mounting bracket and the transition plate;

[0012] The equipment mounting support plate nut is fixed on the transition plate by riveting, and the equipment mounting bolt passes through the inertial guidance component and the transition plate, so that the inertial guidance component and the transition plate are fixedly connected.

[0013] In an optional embodiment of the present application, a waist-shaped hole is provided on the mounting bracket and / or the transition plate, and the heading of the transition plate is adjusted through the waist-shaped hole. The transition plate mounting bolt passes through the waist-shaped hole to fix the mounting bracket to the transition plate.

[0014] In an optional embodiment of the present application, there are four waist-shaped holes, and the four waist-shaped holes are distributed at the four corners of the mounting bracket and the transition plate.

[0015] In an optional embodiment of the present application, the thickness of a single layer of the peelable gasket does not exceed 1 mm.

[0016] In an optional embodiment of the present application, the positioning component is a cylindrical pin.

[0017] In an optional embodiment of the present application, the positioning assembly includes at least 2 pieces.

[0018] The installation structure of the present application can be applied to the installation of inertial navigation equipment of various types of aircraft, which can reduce the installation cycle and cost of inertial navigation equipment and improve maintainability. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0020] Figure 1 This is a schematic diagram of the inertial navigation component installation structure of this application. DETAILED DESCRIPTION

[0021] 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.

[0022] To overcome the existing issues of high precision requirements and long production cycles for mounting brackets for inertial navigation equipment, the present application provides an inertial navigation component mounting structure capable of compensating for mounting datums. This mounting structure can reduce the requirements for aircraft floor structures and the manufacturing of mounting brackets, shortening the production cycle and costs associated with the high precision of inertial navigation component installation. Furthermore, it facilitates the installation and adjustment of inertial navigation components under field conditions.

[0023] like Figure 1 As shown, the inertial navigation component mounting structure 10 with adjustable mounting reference provided in the present application includes a mounting bracket 1, a transition plate 2, a peelable gasket 3, a positioning assembly 4 and a connecting assembly 5.

[0024] Among them, the positioning component 4 is a cylindrical pin, and the connecting component 5 includes a bracket mounting bolt 51, a transition plate mounting bolt 52, a transition plate mounting support plate nut 53 and an equipment mounting bolt 54, and an equipment mounting support plate nut 55.

[0025] The mounting bracket 1 is fixed to a corresponding position on the aircraft structure 20 by bracket mounting bolts 51 .

[0026] The transition plate mounting bracket nut 53 is riveted to the mounting bracket 1, and the equipment mounting bracket nut 55 is riveted to the transition plate 2. The mounting bracket 1 and the transition plate 2 are fixedly connected by the cooperation of the transition plate mounting bolt 52 and the transition plate mounting bracket nut 53. The inertial navigation component 30 and the transition plate 2 are fixedly connected by the cooperation of the equipment mounting bolt 54 and the equipment mounting bracket nut 55.

[0027] The peelable gasket 3 is a gasket structure composed of multiple layers of sheet material bonded together. The peelable gasket 3 is positioned between the mounting bracket 1 and the transition plate 2. The peelable gasket 3 adjusts the installation angle of the transition plate 2 relative to the mounting bracket 1 so that the angle between the transition plate 2 and the horizontal plane of the aircraft structure meets a predetermined requirement, for example, an angle not exceeding ±3'. In some embodiments of the present application, the thickness of a single layer of the peelable gasket 3 does not exceed 0.1 mm. For example, a single layer of the peelable gasket 3 may have a thickness of 0.05 mm.

[0028] The positioning assembly 4 is set on the transition plate 2, and the inertial guide component 30 is pushed into the transition plate 2 and matched with the positioning assembly 4. The inertial guide component 30 is completely fixed by the equipment mounting bolts 54, thereby achieving the installation of the inertial guide component 30 in a precise position.

[0029] In some embodiments of the present application, at least two positioning components 4 are included between the transition plate 2 and the inertial guidance component 30. The fixed installation position of the transition plate 2 is determined by adjusting the angle of the transition plate 2 and the height of the installation direction X of the peelable gasket 3. The positioning component 4 is fixed on the transition plate 2. The lateral positioning component of the equipment installation angle piece cooperates with the concave groove to conveniently push the inertial guidance component into the positioning component 4. The equipment installation bolts 54 are used to fasten the inertial guidance component 30 and the transition plate 2.

[0030] In this application, the transition plate 2 and / or the mounting bracket 1 are provided with waist-shaped holes for the bracket mounting bolts 51 to pass through. The number of these waist-shaped holes can be set to four, distributed at the four corners of the transition plate 2 and the mounting bracket 1. The waist-shaped holes extend in the aircraft's heading Y. The transition plate 2 is rotated through the four waist-shaped holes to adjust its heading, ensuring that the angle between the line connecting the pin holes on the transition plate 2 for mounting the positioning assembly 4 and the aircraft's longitudinal axis is 90°, with an allowable error of ±3'.

[0031] If the aircraft is in use and the body deformation or other reasons cause the installation error of the inertial navigation component 30 to increase, the installation of the inertial navigation component 30 can be adjusted by simply adjusting the installation of the transition plate 2 to ensure the accuracy of the inertial navigation equipment data.

[0032] The installation structure of the present application can be applied to the installation of inertial navigation equipment of various types of aircraft, which can reduce the installation cycle and cost of inertial navigation equipment and improve maintainability.

[0033] 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 inertial navigation component installation structure capable of compensating for an installation reference, characterized in that: include: a mounting bracket, wherein the mounting bracket is fixed to the aircraft structure via a connecting assembly; A transition plate, the transition plate being fixedly connected to the mounting bracket via a connecting assembly, wherein a positioning assembly is provided on the transition plate, and the inertial guidance component is cooperatively mounted on the positioning assembly and fixedly connected to the transition plate via the connecting assembly; A peelable gasket is provided between the mounting bracket and the transition plate. The peelable gasket is used to adjust the mounting direction of the inertial guide component mounted on the transition plate so that the inertial guide component meets the mounting requirements.

2. The inertial navigation component mounting structure capable of compensating the mounting reference according to claim 1, wherein: The connecting component bracket mounting bolts, transition plate mounting bolts, transition plate mounting support plate nuts and equipment mounting bolts, equipment mounting support plate nuts; The mounting bracket is fixed to the aircraft structure by bracket mounting bolts; The transition plate mounting bracket nut is fixed to the mounting bracket by riveting, and the transition plate mounting bolt passes through the mounting bracket and the transition plate to fix the mounting bracket and the transition plate; The equipment mounting support plate nut is fixed on the transition plate by riveting, and the equipment mounting bolt passes through the inertial guidance component and the transition plate, so that the inertial guidance component and the transition plate are fixedly connected.

3. The inertial navigation component mounting structure capable of compensating the mounting reference according to claim 2, wherein: The mounting bracket and / or the transition plate are provided with waist-shaped holes, through which the heading of the transition plate is adjusted, and the transition plate mounting bolts pass through the waist-shaped holes to fix the mounting bracket and the transition plate.

4. The inertial navigation component mounting structure capable of compensating the mounting reference according to claim 3, wherein: There are four waist-shaped holes, which are distributed at four corners of the mounting bracket and the transition plate.

5. The inertial navigation component mounting structure capable of compensating the mounting reference according to claim 1, wherein: The thickness of a single layer of the peelable gasket does not exceed 1 mm.

6. The inertial navigation component mounting structure capable of compensating the mounting reference according to claim 1, wherein: The positioning component is a cylindrical pin.

7. The inertial navigation component mounting structure capable of compensating the mounting reference according to claim 6, wherein: The positioning assembly includes at least two parts.

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