High-precision high-inherent-frequency inertial navigation mounting structure

Abstract

The invention provides a high-precision high-inherent-frequency inertial navigation mounting structure, and belongs to the technical field of aircraft inertial navigation equipment mounting, the high-precision high-inherent-frequency inertial navigation mounting structure comprises an inertial navigation, a structural frame, a support frame, a mounting plate and a positioning pin, the support frame is fixedly mounted on the structural frame through a plurality of support parts, the mounting plate is fixed on the support frame through a connecting piece, and the positioning pin is fixed on the mounting plate. The positioning pin is arranged on the mounting plate, and when the inertial navigation device is fixed on the mounting plate through the mounting bolt, the inertial navigation device is positioned on the mounting plate through the positioning pin. The inertial navigation mounting structure only needs to be mounted on the structural frame once, so that the influence of repeated mounting of the inertial navigation on the strength of an aircraft structure is reduced, the structural frame for mounting the inertial navigation does not need to be frequently disassembled and assembled, and repeated loading and unloading of structural stress are avoided.

Description

Technical Field

[0001] This application belongs to the field of aircraft inertial navigation equipment installation technology, and specifically relates to a high-precision, high-natural-frequency inertial navigation installation structure. Background Technology

[0002] With the rapid development of aircraft in the aviation field, modern aircraft are often equipped with high-precision inertial navigation systems (INS), the installation of which must meet requirements such as high natural frequency, high precision, and high reliability. Due to the complex structure of aircraft and the limited space inside the fuselage, achieving the high-precision installation requirements and ensuring good maintainability within a limited space presents certain challenges. Summary of the Invention

[0003] The purpose of this application is to provide a high-precision, high-natural-frequency inertial navigation system mounting structure to solve or mitigate at least one of the problems in the prior art.

[0004] The technical solution of this application is: a high-precision, high-natural-frequency inertial navigation system mounting structure, comprising: an inertial navigation system, a structural frame, a support frame, a mounting plate, and positioning pins. The support frame is fixedly mounted on the structural frame by multiple support parts. The mounting plate is fixed to the support frame by connectors. The positioning pins are disposed on the mounting plate. When the inertial navigation system is fixed to the mounting plate by mounting bolts, the inertial navigation system is positioned on the mounting plate by the positioning pins.

[0005] Preferably, the mounting plate has a groove larger than the positioning pin, the positioning pin is installed in the groove, wherein the groove is provided with a through hole and threaded through holes on both sides of the through hole.

[0006] Preferably, the positioning pin includes a pin body and an upper cylindrical protrusion and a lower cylindrical protrusion located on both sides of the pin body. The lower cylindrical protrusion mates with a groove through hole on the mounting plate, and the upper cylindrical protrusion is used for positioning with the inertial navigation system.

[0007] Preferably, the positioning pin is made of a high-hardness metal material, and the upper cylindrical protrusion and the lower cylindrical protrusion meet high precision requirements.

[0008] Preferably, the positioning pin is fixed to the mounting plate by a fixing screw passing through the pin body and engaging with the threaded through hole in the groove.

[0009] Preferably, the inertial navigation system has mounting ears at its four corners, and each mounting ear has a semi-circular positioning device. The semi-circular positioning device cooperates with the upper cylindrical protrusion to achieve positioning of the inertial navigation system and the mounting plate.

[0010] Preferably, both the mounting plate and the support frame are provided with multiple weight-reducing holes.

[0011] Preferably, the structural frame, mounting plate, and support frame are all made of metal, and their surfaces are smooth and burr-free after processing.

[0012] Preferably, the surface finish and parallelism of the mounting surface on the mounting plate used for mounting the inertial navigation system meet high precision requirements.

[0013] The inertial navigation system (INS) mounting structure of this application only needs to be installed once on the structural frame, reducing the impact of repeated INS installation on the strength of the aircraft structure itself. The structural frame for mounting the INS does not need to be frequently disassembled and reassembled, avoiding repeated loading and unloading of structural stress. The use of positioning pins ensures the installation accuracy of the INS equipment and reduces repeated installation errors. At the same time, the natural frequency of the INS mounting structure of this application (together with the structural frame) is not less than 180Hz, which greatly reduces the impact of factors such as airframe vibration on the accuracy of the INS. Furthermore, while meeting the limitations of installation space, this INS mounting structure provides a convenient method for subsequent disassembly, assembly, and maintenance. Attached Figure Description

[0014] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0015] Figure 1 This is a schematic diagram of the high-precision, high-natural-frequency inertial navigation system installation structure of this application.

[0016] Figure 2 This is an enlarged view of the high-precision, high-natural-frequency inertial navigation system installation structure of this application.

[0017] Figure 3 This is a schematic diagram of the positioning pin in this application.

[0018] Figure 4 This is a schematic diagram of the inertial navigation system used in this application.

[0019] Figure 5 This is a schematic diagram of the mounting plate for this application.

[0020] Figure label:

[0021] 1-Inertial navigation;

[0022] 11- Install ear;

[0023] 2-Structural frame;

[0024] 3-Support frame;

[0025] 31-First Support Section

[0026] 32-Second Support Section

[0027] 33-Third Support Section

[0028] 34-Fourth Support Section

[0029] 35-Fifth Support Section

[0030] 36-Sixth Support Section

[0031] 37-Seventh Support Section

[0032] 4-Mounting plate;

[0033] 41-Groove;

[0034] 5-Positioning pin;

[0035] 51 - Upper cylindrical protrusion;

[0036] 52 - Lower cylindrical protrusion;

[0037] 53-pin body;

[0038] 6-Fixing screws;

[0039] 7- Mounting bolts. Detailed Implementation

[0040] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0041] This application provides a high-precision, high-natural-frequency inertial navigation system (INS) mounting structure. This structure can avoid repeated disassembly of the mounting components on the aircraft structural frame, and can ensure the installation accuracy, repeatability error, and reliability of the INS, providing a convenient way for subsequent disassembly, assembly, and maintenance.

[0042] like Figures 1 to 5 As shown, the high-precision, high-natural-frequency inertial navigation system mounting structure provided in this application includes: inertial navigation system 1, structural frame 2, support frame 3, mounting plate 4, positioning pins 5, fixing screws 6, and mounting bolts 7.

[0043] Structural frame 2 consists of structural components such as frames and beams in the aircraft structure, capable of bearing certain forces. The forces on inertial navigation system 1 are ultimately borne by structural frame 2.

[0044] The support frame 3 has multiple support parts—including a first support part 31 to a seventh support part 37—distributed on the left and right sides and the lower part of the support frame 3. The support frame 3 is fixed to the structural frame 2 by the multiple support parts, and the two can be connected by riveting or bolting. Preferably, the two can be fixed by high-strength bolts. The support frame 3 is provided with multiple weight-reducing holes, which can be circular, rectangular, or strip-shaped, for example.

[0045] Mounting plate 4 can be fixed to support frame 3 by riveting or bolting, preferably by screwing. Mounting plate 4 is provided with multiple weight-reducing holes and operation through holes. Among them, mounting plate 4 has a recessed groove slightly larger than positioning pin 5, which is used to install positioning pin 5. The recessed groove is provided with a through hole and threaded through holes on both sides of the through hole.

[0046] In a preferred embodiment of this application, the surface finish and parallelism of the mounting surface on the mounting plate 4 used to fix the inertial navigation system 1 meet high precision requirements. In some embodiments of this application, the threaded through hole on the groove has a specification of 3mm, a through hole diameter of 8mm, an upper tolerance of 0.021mm, a lower tolerance of 0, Ra 1.6μm, a perpendicularity of 0.05, a parallelism of 0.05mm, and a flatness of 0.06mm.

[0047] The positioning pin 5 is fixed in the groove 41 of the mounting plate 4 by the fixing screw 6. The positioning pin 5 includes a pin body 53 and an upper cylindrical protrusion 51 and a lower cylindrical protrusion 52 located on the upper and lower sides of the pin body 53. The upper cylindrical protrusion 51 is used for positioning the inertial navigation system 1, and the lower cylindrical protrusion 52 is used for positioning with the mounting plate 4. The pin body 53 has through holes on both sides that are adapted to threaded through holes, and the lower cylindrical protrusion 52 is inserted into the through hole of the groove. The fixing screw 6, which passes through the through holes on both sides of the pin body 53 and mates with the threaded through hole of the groove, fixes the positioning pin 5 in the groove of the mounting plate 4.

[0048] In a preferred embodiment of this application, the diameter of the upper cylindrical protrusion 51 is the same as the diameter of the lower cylindrical protrusion 52. Furthermore, the positioning pin 5 is made of a high-hardness metal material, such as 0Cr15Ni5Cu4Nb, and its surface is machined to meet high precision requirements. In some embodiments of this application, the upper cylindrical protrusion 51 has a diameter of 8mm, a surface roughness Ra of 0.8μm, a coaxiality of 0.05mm, an upper tolerance of -0.005mm, and a lower tolerance of -0.016mm; the lower cylindrical protrusion 52 has a diameter of 8mm, a surface roughness Ra of 0.8μm, a coaxiality of 0.05mm, an upper tolerance of 0, and a lower tolerance of -0.011; the pin body 53 has a surface roughness Ra of 1.6μm, a perpendicularity of 0.05, a flatness of 0.04mm, and the fixing screw 6 has a diameter of 3mm.

[0049] The inertial navigation system 1 is fixed to the mounting plate 4 by mounting bolts 7. The inertial navigation system 1 has mounting ears 11 at its four corners, and each mounting ear 11 has a semi-circular positioning device that mates with a positioning pin 5. When the inertial navigation system 1 is installed on the mounting plate 4, the semi-circular positioning device on the mounting ear 11 engages with the upper cylindrical protrusion 51 of the positioning pin 5 to achieve positioning of the inertial navigation system 1.

[0050] In the preferred embodiment of this application, the housings of the inertial navigation system 1, structural frame 2, support frame 3, mounting plate 4, positioning pin 5, fixing screw 6 and fixing bolt 7 are all made of metal, and their surfaces are processed to form a flat, burr-free structure.

[0051] The installation process of the high-precision natural frequency inertial navigation structure of this application is as follows:

[0052] (1) Fix the support frame 3 to the structural frame 2 by riveting or screwing (a peelable aluminum alloy shim can be used for leveling during installation).

[0053] (2) Fix the mounting plate 4 to the support frame 3 by riveting or screwing;

[0054] (3) Fix the positioning pin 5 to the mounting plate 4 using the positioning screw 6;

[0055] (4) Position the inertial navigation system 1 on the mounting plate 4 using the positioning pins 5;

[0056] (5) Fix the inertial navigation system 1 to the mounting plate 4 using fixing bolts 7.

[0057] The inertial navigation system (INS) mounting structure of this application only needs to be installed once on the structural frame, reducing the impact of repeated INS installation on the strength of the aircraft structure itself. The structural frame for mounting the INS does not need to be frequently disassembled and reassembled, avoiding repeated loading and unloading of structural stress. The use of positioning pins ensures the installation accuracy of the INS equipment and reduces repeated installation errors. At the same time, the natural frequency of the INS mounting structure of this application (together with the structural frame) is not less than 180Hz, which greatly reduces the impact of factors such as airframe vibration on the accuracy of the INS. Furthermore, while meeting the limitations of installation space, this INS mounting structure provides a convenient method for subsequent disassembly, assembly, and maintenance.

[0058] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A high-precision, high-natural-frequency inertial navigation system mounting structure, characterized in that, include: The inertial navigation system (1), structural frame (2), support frame (3), mounting plate (4) and positioning pin (5) are provided. The support frame (3) is fixedly installed on the structural frame (3) by multiple support parts. The mounting plate (4) is fixed to the support frame (3) by connectors. The positioning pin (5) is set on the mounting plate (4). When the inertial navigation system (1) is fixed to the mounting plate (4) by mounting bolts (7), the inertial navigation system (1) is positioned on the mounting plate (4) by the positioning pin (5).

2. The high-precision, high-natural-frequency inertial navigation system mounting structure as described in claim 1, characterized in that, The mounting plate (4) has a groove larger than the positioning pin (5), and the positioning pin (5) is installed in the groove. The groove is provided with a through hole and threaded through holes on both sides of the through hole.

3. The high-precision, high-natural-frequency inertial navigation system mounting structure as described in claim 2, characterized in that, The positioning pin (5) includes a pin body (53) and an upper cylindrical protrusion (51) and a lower cylindrical protrusion (52) located on both sides of the pin body (53). The lower cylindrical protrusion (52) cooperates with the groove through hole on the mounting plate (4), and the upper cylindrical protrusion (51) is used for positioning with the inertial navigation system (1).

4. The high-precision, high-natural-frequency inertial navigation installation structure as described in claim 3, characterized in that, The positioning pin (7) is made of high-hardness metal material, and the upper cylindrical protrusion (51) and the lower cylindrical protrusion (52) meet the high precision requirements.

5. The high-precision, high-natural-frequency inertial navigation system mounting structure as described in claim 3, characterized in that, The positioning pin (5) is fixed to the mounting plate (4) by the fixing screw (6) passing through the pin body (53) and engaging with the threaded through hole in the groove.

6. The high-precision, high-natural-frequency inertial navigation system mounting structure as described in claim 3, characterized in that, The inertial navigation system (1) has mounting ears (1) at its four corners. The mounting ears (11) have semi-circular positioning devices. The semi-circular positioning devices cooperate with the upper cylindrical protrusion (51) to achieve positioning of the inertial navigation system (1) and the mounting plate (4).

7. The high-precision, high-natural-frequency inertial navigation system mounting structure as described in claim 1, characterized in that, The mounting plate (4) and the support frame (3) are provided with multiple weight reduction holes.

8. The high-precision, high-natural-frequency inertial navigation system mounting structure as described in claim 1, characterized in that, The structural frame (2), mounting plate (4) and support frame (3) are all made of metal, and their surfaces are smooth and burr-free after processing.

9. The high-precision, high-natural-frequency inertial navigation system mounting structure as described in claim 8, characterized in that, The surface finish and parallelism of the mounting surface on the mounting plate (4) used for mounting the inertial navigation system (1) meet the high precision requirements.

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