Hoisting type astronomical inertial navigation mounting structure

Abstract

The invention provides a hoisting type astronomical inertial navigation mounting structure, and belongs to the technical field of aircraft inertial navigation equipment mounting, the hoisting type astronomical inertial navigation mounting structure comprises an astronomical inertial navigation, a heater, a structural frame, a connecting bracket, a mounting plate, a support frame and a positioning pin, the connecting bracket is fixed on the structural frame through a connecting piece, and the positioning pin is fixed on the mounting plate through a positioning screw; the mounting plate is fixed on the connecting bracket through a connecting piece, and the support frame is fixed on the mounting plate through a connecting piece; wherein an astronomical inertial navigation mounting lug and a heater mounting lug are arranged on the mounting plate, and when the astronomical inertial navigation and heater are mounted in place on the mounting plate, the astronomical inertial navigation and heater are fixed with the astronomical inertial navigation mounting lug and the heater mounting lug of the mounting plate through connecting pieces. The device only needs to be installed on a structural frame once, the influence of repeated installation of astronomical inertial navigation on the strength of an aircraft structure is reduced, 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 hoisting astronomical inertial navigation system installation structure. Background Technology

[0002] With the rapid development of aircraft in the aviation field, modern aircraft are often equipped with astronomical inertial navigation systems (a deep fusion system of inertial navigation and astronomical navigation systems), and their installation needs to meet requirements such as high strength, high precision, and high reliability. Due to the complex structure of aircraft and the limited space inside the fuselage, there are certain challenges in achieving the high-requirement installation of astronomical inertial navigation systems and ensuring good maintainability within the limited space. Summary of the Invention

[0003] The purpose of this application is to provide a suspended astronomical inertial navigation system installation structure to solve or mitigate at least one of the problems in the prior art.

[0004] The technical solution of this application is: a suspended astronomical inertial navigation system installation structure, including: an astronomical inertial navigation system, a heater, a structural frame, a connecting bracket, a mounting plate, a support frame and positioning pins. The connecting bracket is fixed to the structural frame by a connector, the positioning pin is fixed to the mounting plate by positioning screws, the mounting plate is fixed to the connecting bracket by a connector, and the support frame is fixed to the mounting plate by a connector.

[0005] The mounting plate is provided with astronomical inertial navigation system mounting ears and heater mounting ears. When the astronomical inertial navigation system and heater are installed in place on the mounting plate, the astronomical inertial navigation system and heater are fixed to the astronomical inertial navigation system mounting ears and heater mounting ears of the mounting plate by connectors.

[0006] Preferably, the mounting plate has a groove larger than the positioning pin, the positioning pin is installed in the groove, and the groove is provided with a through hole and threaded through holes on both sides of the through hole.

[0007] 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 engages with the through hole of the groove, and the upper cylindrical protrusion is used for positioning with the astronomical inertial navigation system.

[0008] 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.

[0009] Preferably, the positioning pin is fixed to the mounting plate by engaging a positioning screw that passes through the pin body with a threaded through hole in the groove.

[0010] Preferably, the astronomical inertial navigation system is provided with first mounting ears at its four corners, and each first mounting ear has a semi-circular positioning device. The semi-circular positioning device cooperates with the upper cylindrical protrusion to realize the positioning of the astronomical inertial navigation system and the mounting plate.

[0011] Preferably, the heater is provided with second mounting ears at its four corners for fixing the heater to the mounting plate.

[0012] Preferably, the first ear and the second mounting ear are provided with a polygonal anti-detachment structure.

[0013] Preferably, the connecting bracket, mounting plate, and support frame are all provided with multiple weight-reducing holes.

[0014] Preferably, the structural frame, connecting bracket, mounting plate, and support frame are all made of metal, and their surfaces are smooth and burr-free after processing.

[0015] Preferably, the surface finish and parallelism of the mounting surface on the mounting plate used for mounting the astronomical inertial navigation system meet high precision requirements.

[0016] The astronomical inertial navigation system (AINS) mounting structure of this application only needs to be installed once on the structural frame, reducing the impact of repeated AINS installations on the strength of the aircraft structure itself. The structural frame for installing the AINS 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 AINS equipment and reduces repeated installation errors. The design of the mounting ears for the AINS and heater reduces the risk of bolts falling off during bottom-up installation, while the design of the support frame ensures that even if bolts fall off due to vibration during aircraft flight, the equipment will not fall off. Furthermore, this AINS mounting structure, while meeting the limitations of installation space, provides a convenient method for subsequent disassembly, assembly, and maintenance. Attached Figure Description

[0017] 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.

[0018] Figure 1 This is a schematic diagram of the astronomical inertial navigation system installation structure of this application.

[0019] Figure 2 This is a schematic diagram of the positioning pin structure of this application.

[0020] Figure 3 This is an enlarged view of the positioning pin structure of this application.

[0021] Figure 4 This is a schematic diagram of the astronomical inertial navigation system used in this application.

[0022] Figure 5 Enlarged view of the astronomical inertial navigation system mounting ear for this application.

[0023] Figure 6 This is a schematic diagram of the heater in this application.

[0024] Figure 7 This is a schematic diagram of the heater mounting lugs for this application.

[0025] Figure 8 This is a schematic diagram of the mounting plate for this application.

[0026] Figure label:

[0027] 1-Astronomical inertial navigation;

[0028] 11- Semicircular positioning device;

[0029] 12-First mounting ear;

[0030] 13 - First fuse hole;

[0031] 2-Heater;

[0032] 21-Second mounting ear;

[0033] 22 - Second fuse hole;

[0034] 3-Structural frame;

[0035] 4-Connecting bracket;

[0036] 5-Mounting plate;

[0037] 51-groove;

[0038] 52-Astronomical inertial navigation system mounting ear;

[0039] 53 - Heater mounting ears;

[0040] 6-Support frame;

[0041] 7-Positioning pin;

[0042] 71 - Upper cylindrical protrusion;

[0043] 72 - Lower cylindrical protrusion;

[0044] 73-pin body;

[0045] 8-Fixing screws;

[0046] 9- Mounting bolts;

[0047] 10. Install the nuts. Detailed Implementation

[0048] 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.

[0049] This application provides a hoisting astronomical inertial navigation system (AINS) installation structure. This structure can avoid repeated disassembly of the components mounted on the aircraft structural frame, and can ensure the installation accuracy, repeatability error and reliability of the AINS, providing a convenient way for subsequent disassembly, assembly and maintenance.

[0050] like Figures 1 to 8 As shown, the hoisted astronomical inertial navigation system installation structure provided in this application includes: astronomical inertial navigation system 1, heater 2, structural frame 3, connecting bracket 4, mounting plate 5, support frame 6, positioning pin 7, fixing screw 8, mounting bolt 9, and mounting nut 10.

[0051] Structural frame 3 consists of structural components such as frames and beams in the aircraft structure, capable of bearing certain forces. The forces on the astronomical inertial navigation system 1 and the heater 2 are mainly borne by the structural frame.

[0052] The connecting bracket 4 comprises three parts, all of which are fixed to the structural frame 3. These parts can be fixed to the structural frame 3 by riveting or bolting. In a preferred embodiment of this application, the connecting bracket 4 is connected to the structural frame 3 by screws for easy disassembly. Furthermore, the connecting bracket 4 may be provided with multiple weight-reducing holes, which can be circular, elongated, or similar shapes.

[0053] The mounting plate 5 can be fixed to the connecting bracket 4 by riveting or bolting. In a preferred embodiment of this application, the mounting plate 5 is fixed to the connecting bracket 4 by riveting. Furthermore, the mounting plate 5 may also have multiple weight-reducing holes. The mounting plate 5 has a non-through groove 51 slightly larger than the positioning pin 7. The groove 51 has a through hole and threaded through holes located on both sides of the through hole. In some embodiments of this application, the specifications of the threaded through holes are slightly smaller than the specifications of the through holes. The mounting plate 5 is also provided with an astronomical inertial navigation mounting ear 52 and a heater mounting ear 53.

[0054] The support frame 6 is fixed to the mounting plate 5 by screws, and it is provided with multiple weight reduction holes.

[0055] The positioning pin 7 includes a pin body 73 and an upper cylindrical protrusion 71 and a lower cylindrical protrusion 72 located on the upper and lower sides of the pin body 73. The upper cylindrical protrusion 71 is used for positioning the astronomical inertial navigation system 1, and the lower cylindrical protrusion 72 is used for positioning with the mounting plate 5. The pin body 73 has through holes on both sides that are adapted to threaded through holes, and the lower cylindrical protrusion 72 is inserted into the through hole of the groove 51. A fixing screw 8, passing through the through holes on both sides of the pin body 73 and engaging with the threaded through hole of the groove 51, fixes the positioning pin 7 in the groove 51 of the mounting plate 5. In some embodiments of this application, the diameter of the upper cylindrical protrusion 71 is the same as the diameter of the lower cylindrical protrusion 72.

[0056] In a preferred embodiment of this application, the positioning pin 7 is made of a high-hardness metal material, such as 0Cr15Ni5Cu4Nb, and its surface is processed to meet high precision requirements. In some embodiments of this application, the upper cylindrical protrusion 71 has a diameter of 5mm, a roughness Ra of 0.8μm, a coaxiality of 0.05mm, an upper tolerance of -0.004mm, and a lower tolerance of -0.015mm; the lower cylindrical protrusion 72 has a diameter of 5mm, a roughness Ra of 0.8μm, a coaxiality of 0.05mm, an upper tolerance of 0mm, and a lower tolerance of -0.011mm; the pin body 73 has a surface roughness Ra of 1.6μm, a perpendicularity of 0.05, a flatness of 0.04mm, and the fixing screw 8 has a specification of 3mm.

[0057] The inertial navigation system 1 has first mounting ears 12 at its four corners, and each first mounting ear 12 has a semi-circular positioning device 11. Similarly, the heater 2 has second mounting ears 21 at its four corners. The second mounting ears 21 are L-shaped and are fixed to the four corner sides of the heater 2 by multiple connectors. In this application, the first mounting ears 12 of the inertial navigation system 1 and the second mounting ears 21 of the heater 2 are provided with polygonal anti-detachment structures. For example, the polygon can be hexagonal. The polygonal anti-detachment structure of the first mounting ear 12 can be provided with a first fuse hole 13, and the polygonal anti-detachment structure of the second mounting ear 21 can be provided with a second fuse hole 22 for installing a fuse.

[0058] The astronomical inertial navigation system 1 and the heater 2 are fixed to the astronomical inertial navigation mounting ears 52 and the heater mounting ears 53 of the mounting plate 5 by mounting bolts 9 and mounting nuts 10, respectively. The astronomical inertial navigation system 1 and the mounting plate 5 are positioned by the semi-circular positioning device 11 at the first mounting ear 12 cooperating with the upper cylindrical protrusion 71 of the positioning pin 7.

[0059] In a preferred embodiment of this application, the astronomical inertial navigation system 1, heater 2, structural frame 3, connecting bracket 4, mounting plate 5, support frame 6, positioning pin 7, fixing screw 8, mounting bolt 9, and mounting nut 10 are all made of metal, and their surfaces are machined to form a smooth, burr-free structure. The surface finish and parallelism of the mounting surface of the astronomical inertial navigation system 1 on the mounting plate 5 meet high-precision requirements. In some embodiments of this application, the specifications of the threaded through hole on the mounting plate 5 are 3mm, the through hole diameter is 5mm, the upper tolerance is 0.021mm, the lower tolerance is 0mm, the roughness Ra is 1.6μm, the perpendicularity is 0.05, the flatness is 0.06mm, and the parallelism is 0.05mm.

[0060] The installation process of the suspended astronomical inertial navigation system mounting structure of this application is as follows:

[0061] (1) Fix the connecting bracket 4 to the structural frame 3 by riveting or screwing (a peelable aluminum alloy shim can be used for leveling during installation).

[0062] (2) Fix the locating pin 7 to the mounting plate 5 using the locating screw 8;

[0063] (3) Fix the mounting plate 5 to the connecting bracket 4 by riveting or screwing. When fixing, use the positioning pin 7 as a reference and adjust the level with peelable shims.

[0064] (4) Secure the mounting nut 10 to the first mounting ear 12 and the second mounting ear 21 using a fuse;

[0065] (5) Push the astronomical inertial navigation system 1 from bottom to top into the left space formed by the connecting bracket 4 and the mounting plate 5, and then move it from left to right until the semi-circular positioning device 11 of the astronomical inertial navigation system 1 is inserted into the upper cylindrical protrusion of the positioning pin 7 and placed at the astronomical inertial navigation mounting ear 52 of the mounting plate 5. Then tighten and fix it from bottom to top by the mounting bolt 9.

[0066] (6) Push the heater 2 from bottom to top into the right space formed by the connecting bracket 4 and the mounting plate 5, and then move it from left to right until the second mounting ear 21 of the heater 2 is placed at the heater mounting ear 53 of the mounting plate 5, and then tighten it from bottom to top with the mounting bolt 9.

[0067] The astronomical inertial navigation system (AINS) mounting structure of this application only needs to be installed once on the structural frame, reducing the impact of repeated AINS installations on the strength of the aircraft structure itself. The structural frame for installing the AINS 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 AINS equipment and reduces repeated installation errors. The design of the mounting ears for the AINS and heater reduces the risk of bolts falling off during bottom-up installation, while the design of the support frame ensures that even if bolts fall off due to vibration during aircraft flight, the equipment will not fall off. Furthermore, this AINS mounting structure, while meeting the limitations of installation space, provides a convenient method for subsequent disassembly, assembly, and maintenance.

[0068] 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 suspended astronomical inertial navigation system installation structure, characterized in that, include: The components include an astronomical inertial navigation system (1), a heater (2), a structural frame (3), a connecting bracket (4), a mounting plate (5), a support frame (6), and a positioning pin (7). The connecting bracket (4) is fixed to the structural frame (3) by a connector. The positioning pin (7) is fixed to the mounting plate (5) by a positioning screw (8). The mounting plate (5) is fixed to the connecting bracket (4) by a connector. The support frame (6) is fixed to the mounting plate (5) by a connector. The mounting plate (5) is provided with an astronomical inertial navigation mounting ear (52) and a heater mounting ear (53). When the astronomical inertial navigation (1) and the heater (2) are installed on the mounting plate (5), the astronomical inertial navigation (1) and the heater (2) are fixed to the astronomical inertial navigation mounting ear (52) and the heater mounting ear (53) of the mounting plate (5) by means of connectors.

2. The suspended astronomical inertial navigation system installation structure as described in claim 1, characterized in that, The mounting plate (5) has a groove (51) larger than the positioning pin (7), and the positioning pin (7) is installed in the groove (51). The groove (51) is provided with a through hole and threaded through holes on both sides of the through hole.

3. The suspended astronomical inertial navigation system installation structure as described in claim 2, characterized in that, The positioning pin (7) includes a pin body (73) and an upper cylindrical protrusion (71) and a lower cylindrical protrusion (72) located on both sides of the pin body (73). The lower cylindrical protrusion (72) engages with the through hole of the groove (51), and the upper cylindrical protrusion (71) is used for positioning with the astronomical inertial navigation system (1).

4. The suspended astronomical inertial navigation system 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 (71) and the lower cylindrical protrusion (72) meet the high precision requirements.

5. The suspended astronomical inertial navigation system installation structure as described in claim 3, characterized in that, The positioning pin (7) is fixed to the mounting plate (5) by the positioning screw (8) passing through the pin body (73) and engaging with the threaded through hole in the groove (51).

6. The suspended astronomical inertial navigation system installation structure as described in claim 3, characterized in that, The astronomical inertial navigation system (1) has a first mounting ear (12) at each of its four corners. The first mounting ear (12) has a semi-circular positioning device (11). The semi-circular positioning device (11) cooperates with the upper cylindrical protrusion (71) to realize the positioning of the astronomical inertial navigation system (1) and the mounting plate (5).

7. The suspended astronomical inertial navigation system installation structure as described in claim 6, characterized in that, The heater (2) has a second mounting ear (21) at each of its four corners for fixing the heater (2) to the mounting plate (5).

8. The suspended astronomical inertial navigation system installation structure as described in claim 7, characterized in that, The first ear (11) and the second mounting ear (21) are provided with a polygonal anti-detachment structure.

9. The suspended astronomical inertial navigation system installation structure as described in claim 1, characterized in that, The connecting bracket (4), mounting plate (5) and support frame (6) are all provided with multiple weight reduction holes.

10. The suspended astronomical inertial navigation system installation structure as described in claim 1, characterized in that, The structural frame (3), connecting bracket (4), mounting plate (5) and support frame (6) are all made of metal, and their surfaces are smooth and burr-free after processing.

11. The suspended astronomical inertial navigation system installation structure as described in claim 10, characterized in that, The surface finish and parallelism of the mounting surface on the mounting plate (5) used for mounting the astronomical inertial navigation system (1) meet the high precision requirements.

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