Evto aircraft inertial navigation installation support

Abstract

The utility model relates to unmanned plane spare part technical field especially, it relates to a kind of evtol airplane inertial navigation installation support, including support body, the support body is used to install on aircraft;The support body includes the middle mounting plate for installing inertial navigation and the side mounting plate of middle mounting plate side edge, the middle mounting plate and side mounting plate whole are several character type structures, improve support body rigidity, the utility model several character type support body's first natural frequency is big, vibration deformation is small, rigidity is big, equipment is easily installed, satisfies design demand.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) component technology, and in particular to an EVTOL aircraft inertial navigation system mounting bracket. Background Technology

[0002] eVTOL typically operates in low-altitude airspace below 300 meters (not exceeding 3000 meters when extension is required). This airspace is subject to interference from buildings, terrain, meteorological activities, and dense electromagnetic signals, leading to frequent loss or distortion of Global Navigation Satellite System (GNSS) signals. Inertial Navigation Systems (INS), on the other hand, do not rely on external signals and can maintain continuous positioning capabilities when GNSS fails.

[0003] Since inertial navigation systems (INS) are greatly affected by vibration, some existing INS systems are fixed to the aircraft during installation to reduce inaccurate data caused by vibration. However, this method has the problem that the mounting hole spacing of the INS itself does not match the existing thread hole spacing of the aircraft, so an INS support needs to be designed. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the existing technology and provide an EVTOL aircraft inertial navigation system mounting bracket, which has the advantages of large first-order natural frequency, small vibration deformation, large stiffness, and easy equipment installation.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] An EVTOL aircraft inertial navigation system mounting bracket includes:

[0007] A bracket body for mounting on an aircraft;

[0008] The support body includes a central mounting plate for mounting the inertial navigation system and side mounting plates on the sides of the central mounting plate. The central mounting plate and the side mounting plates are generally in a U-shape to improve the rigidity of the support body.

[0009] Preferably, the central mounting plate has at least one set of mounting holes for mounting the inertial navigation system.

[0010] Furthermore, the side mounting plate is provided with mounting holes two for fixing the bracket body to the aircraft.

[0011] Furthermore, the side mounting plate is provided with a clearance groove that communicates with the second mounting hole.

[0012] Furthermore, the length of the bracket body is 200-220mm, the width is 75-95mm, the width of the middle mounting plate is 40-60mm, the thickness of the middle mounting plate is 1-4mm, and the height of the middle mounting plate is 9-15mm.

[0013] Furthermore, the length of the bracket body is 205, 210, or 215 mm, the width is 80, 86, or 90 mm, the width of the middle mounting plate is 47, 52, or 57 mm, the thickness of the middle mounting plate is 1.5, 2, or 3 mm, and the height of the middle mounting plate is 11, 12, or 14 mm.

[0014] Furthermore, the second mounting hole has a diameter of 4.8 mm, which is used to cooperate with four fasteners with a diameter of 4 mm to fix the bracket body on the aircraft.

[0015] Furthermore, the clearance groove has a diameter of 13mm and a depth of 1.5mm.

[0016] The beneficial effects of this utility model are:

[0017] The Z-shaped support body of this utility model has a large first-order natural frequency, small vibration deformation, high stiffness, and is easy to install, thus meeting design requirements. Attached Figure Description

[0018] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a three-dimensional schematic diagram of the present invention;

[0020] Figure 2 This is a bottom view of the present invention;

[0021] Figure 3 This is a schematic diagram of the bracket body of this utility model installed on an aircraft.

[0022] Figure 4 This is a utility model Figure 3 Schematic diagram of cross-section at point AA;

[0023] Figure 5 This is a utility model Figure 4 Enlarged schematic diagram of the structure at point A;

[0024] Figure 6 This is a deformed cloud diagram of the bracket according to Embodiment 1 of this utility model;

[0025] Figure 7 This is a deformation cloud diagram of the bracket according to Embodiment 2 of this utility model;

[0026] Figure 8This is a deformed cloud diagram of the bracket in Embodiment 3 of this utility model;

[0027] Figure 9 These are the first four vibration mode diagrams of Embodiment 1 of this utility model;

[0028] Figure 10 These are the first four vibration modes of Embodiment 2 of this utility model;

[0029] Figure 11 These are the first four vibration modes of Embodiment 3 of this utility model;

[0030] Figure 12 This is a schematic diagram of the PSD spectrum of the vibration test curve of this utility model;

[0031] Figure 13 This is a vibration deformation cloud diagram in the X direction of Embodiment 1 of this utility model;

[0032] Figure 14 This is a vibration deformation cloud diagram in the X direction of Embodiment 2 of this utility model;

[0033] Figure 15 This is a vibration deformation cloud diagram in the X direction of Embodiment 3 of this utility model;

[0034] Figure 16 This is a vibration deformation cloud diagram in the Y direction of Embodiment 1 of this utility model;

[0035] Figure 17 This is a vibration deformation cloud diagram in the Y direction of Embodiment 2 of this utility model;

[0036] Figure 18 This is a vibration deformation cloud diagram in the Y direction of Embodiment 3 of this utility model;

[0037] Figure 19 This is a vibration deformation cloud diagram in the Z-direction of Embodiment 1 of this utility model;

[0038] Figure 20 This is a vibration deformation cloud diagram in the Z-direction of Embodiment 2 of this utility model;

[0039] Figure 21 This is a vibration deformation cloud diagram in the Z-direction of Embodiment 3 of this utility model.

[0040] The markings in the diagram are as follows: 1. Bracket body; 2. Inertial navigation system; 101. Middle mounting plate; 102. Side mounting plate; 1011. Mounting hole one; 1021. Mounting hole two; 1022. Clearance groove; 201. Screw; 202. Nut; 203. Screw hole shoulder bushing. Detailed Implementation

[0041] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0042] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0043] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the scope of the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0044] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0045] Example 1

[0046] Please see Figure 1-5 As shown, an EVTOL aircraft inertial navigation system mounting bracket includes a bracket body 1, which is mounted on the aircraft.

[0047] In this embodiment, the support body 1 includes a central mounting plate 101 for mounting the inertial navigation system 2 and side mounting plates 102 mounted on the sides of the central mounting plate 101. There are two side mounting plates 102, which are located on both sides of the central mounting plate 101. Both side mounting plates 102 and the central mounting plate 101 are integrally formed. The central mounting plate 101 and the two side mounting plates 102 are in the form of a U-shaped structure. The design of the U-shaped structure can improve the rigidity of the support body 1.

[0048] In this embodiment, the central mounting plate 101 has at least one set of mounting holes 1011 for mounting the inertial navigation system 2. In this embodiment, two sets of mounting holes 1011 are designed, and the two sets of mounting holes 1011 are used to mount two inertial navigation systems 2 respectively. Each set of mounting holes 1011 has four holes. When installing the inertial navigation system 2, the inertial navigation system 2 is placed on the central mounting plate 101, and the holes opened at the four corners of the inertial navigation system 2 correspond to the positions of the four mounting holes 1011 respectively. It is fixed by four fasteners (including but not limited to screws) with a diameter of 3mm. The two inertial navigation systems 2 are symmetrically mounted on the central mounting plate 101 along the flight direction.

[0049] In this embodiment, the side mounting plate 102 is provided with mounting holes 1021 for fixing the bracket body 1 to the aircraft. The bracket body 1 is installed using existing nail holes on the aircraft. Specifically:

[0050] Place the bracket body 1 on the aircraft, ensuring that the mounting hole 1021 on the side mounting plate 102 corresponds to and connects with the existing nail holes on the aircraft. After passing the screw 201 through the mounting hole 1021 and the nail holes on the aircraft, the side mounting plate 102 is fixed by the cooperation of the nut 202, thereby fixing the bracket body 1. The specific installation position is at the location of the guide rail nail on the floor inside the aircraft cabin, because this location has greater rigidity, less vibration during flight, and is also far from the vibration source of the arm motor. That is, during installation, the mounting hole 1021 corresponds to and connects with the existing nail holes on the guide rail.

[0051] In this embodiment, the side mounting plate 102 is provided with a clearance groove 1022 that communicates with the mounting hole 1021. The clearance groove 1022 has a diameter of 13mm and a depth of 1.5mm. A nail hole shoulder bushing 203 is also provided between the aircraft and the side mounting plate 102. The nail hole shoulder bushing 203 is located in the nail hole opened on the aircraft, and the protruding end of the nail hole shoulder bushing 203 extends to the outside of the aircraft. The clearance groove 1022 can accommodate the nail hole shoulder bushing 203, so that the bottom of the side mounting plate 102 is horizontal and in contact with the aircraft.

[0052] In this embodiment, the length of the bracket body 1 is 205mm, the width is 80mm, the width of the middle mounting plate 101 is 47mm, the thickness of the middle mounting plate 101 is 3mm, and the height of the middle mounting plate 101 is 11mm.

[0053] Example 2

[0054] The similarities with Embodiment 1 will not be repeated here. The differences from Embodiment 1 are as follows: the length of the bracket body 1 is 210mm, the width is 86mm, the width of the middle mounting plate 101 is 52mm, the thickness of the middle mounting plate 101 is 2mm, and the height of the middle mounting plate 101 is 14mm.

[0055] Example 3

[0056] The similarities with Embodiment 1 will not be repeated here. The differences from Embodiment 1 are as follows: the length of the bracket body 1 is 215mm, the width is 90mm, the width of the middle mounting plate 101 is 57mm, the thickness of the middle mounting plate 101 is 1.5mm, and the height of the middle mounting plate 101 is 14mm.

[0057] A concentrated downward load of 50N is applied at the center of the support. The deformation cloud diagram of the support with the dimensions and shape of Example 1 is shown below. Figure 6 As shown, the maximum deformation is 0.0061mm; the deformation cloud diagram of the bracket dimensions in Example 2 is shown below. Figure 7 As shown, the maximum deformation is 0.0066mm; the deformation cloud diagram of the bracket dimensions in Example 3 is shown below. Figure 8 As shown, the maximum deformation is 0.0108 mm.

[0058] Modal analysis was performed on the support body 1 of Embodiment 1. Four nail holes were fixed in place. The first four natural frequencies are shown in Table 1. The first natural frequency is 1127Hz, which is much higher than the blade drive frequency. The mode shapes of the first four natural frequencies are shown below. Figure 9 As shown.

[0059] Table 1

[0060]

[0061] Modal analysis was performed on the support body 1 of Embodiment 2. Four nail holes were fixed in place. The first four natural frequencies are shown in Table 2. The first natural frequency is 1135Hz, which is much higher than the blade drive frequency. The mode shapes of the first four natural frequencies are shown below. Figure 10 As shown.

[0062] Table 2

[0063]

[0064] Modal analysis was performed on the support body 1 of Embodiment 3. Four nail holes were fixed in place. The first four natural frequencies are shown in Table 3. The first natural frequency is 1047Hz, which is much higher than the blade drive frequency. The mode shapes of the first four natural frequencies are shown below. Figure 11 As shown.

[0065] Table 3

[0066]

[0067] Random vibration analysis was performed on the Z-shaped support body 1, referring to the PSD spectrum of random vibration test curves of helicopter fuselage and instrument panel in DO-160G, as shown in Table 4 and Figure 12 As shown. Random vibrations in the X, Y, and Z directions were calculated respectively, and the vibration deformation contour plots are shown below. Figures 13-21As shown. Random vibration revealed that the vibration in the Z direction was greater than the deformation in the X and Y directions, with the maximum deformation occurring at the flange of the support, where the deformation was very small.

[0068] Table 4

[0069]

[0070] In summary, the Z-shaped support body 1 of this application has a large first-order natural frequency, small vibration deformation, high stiffness, and is easy to install, thus meeting the design requirements.

[0071] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this utility model, and these modifications or substitutions should all be covered within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.

Claims

1. An EVTOL aircraft inertial navigation system mounting bracket, characterized in that, include: The bracket body (1) is used for installation on an aircraft; The support body (1) includes a central mounting plate (101) for mounting the inertial navigation system (2) and a side mounting plate (102) on the side of the central mounting plate (101). The central mounting plate (101) and the side mounting plate (102) are in a U-shape structure to improve the rigidity of the support body (1).

2. The EVTOL aircraft inertial navigation system mounting bracket according to claim 1, characterized in that, At least one set of mounting holes (1011) for mounting the inertial navigation system (2) are provided on the central mounting plate (101).

3. The EVTOL aircraft inertial navigation system mounting bracket according to claim 1, characterized in that, The side mounting plate (102) is provided with mounting holes (1021) for fixing the bracket body (1) to the aircraft.

4. The EVTOL aircraft inertial navigation system mounting bracket according to claim 3, characterized in that, The side mounting plate (102) is provided with a clearance groove (1022) that communicates with the second mounting hole (1021).

5. The EVTOL aircraft inertial navigation system mounting bracket according to claim 1, characterized in that, The length of the bracket body (1) is 200-220mm and the width is 75-95mm. The width of the middle mounting plate (101) is 40-60mm, the thickness of the middle mounting plate (101) is 1-4mm, and the height of the middle mounting plate (101) is 9-15mm.

6. The EVTOL aircraft inertial navigation system mounting bracket according to claim 1, characterized in that, The length of the bracket body (1) is 205, 210 or 215 mm, the width is 80, 86 or 90 mm, the width of the middle mounting plate (101) is 47, 52 or 57 mm, the thickness of the middle mounting plate (101) is 1.5, 2 or 3 mm, and the height of the middle mounting plate (101) is 11, 12 or 14 mm.

7. The EVTOL aircraft inertial navigation system mounting bracket according to claim 3, characterized in that, The second mounting hole (1021) has a diameter of 4.8 mm and is used to cooperate with four fasteners with a diameter of 4 mm to fix the bracket body (1) on the aircraft.

8. The EVTOL aircraft inertial navigation system mounting bracket according to claim 4, characterized in that, The clearance groove (1022) has a diameter of 13 mm and a depth of 1.5 mm.

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