Engine mounting rack
By combining a double-layer isolation vibration damping device and an anti-torsion device, the design challenge of engine mounting bracket stiffness was solved, achieving efficient vibration reduction and torsional limitation, thus ensuring the safe and stable flight of the UAV.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-25
- Publication Date
- 2026-04-21
AI Technical Summary
The existing engine mounting bracket has difficulties in stiffness design. If the stiffness is too large, the vibration reduction effect will be poor, while if the stiffness is too small, it may cause safety accidents and loosening of mechanical connections, and it cannot effectively isolate the vibration of the engine and propeller.
The system employs a double-layer isolation and vibration damping device and an anti-torsion device. Through the combined design of the main support plate, mounting ears, isolation and vibration damping components, and anti-torsion device, it achieves two-stage vibration attenuation and torsional limitation for the engine and propeller.
It significantly improves vibration reduction, prevents wide-amplitude vibration of the engine and propeller, ensures the safety and stability of power transmission, and avoids loosening of mechanical connections and structural wear.
Smart Images
Figure CN224146219U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to an engine mounting bracket. Background Technology
[0002] The engine is the power source of a drone. A well-designed engine mounting system not only ensures the drone's flight performance but also avoids safety hazards. The purpose of the engine mounting bracket is to reliably install the engine on the drone using a suitable mounting method and structure, enabling the engine to operate normally in various operating environments and flight conditions, and effectively converting the thrust or pull generated by the engine driving the propeller into the drone's flight power.
[0003] The engine mounting bracket must not only have sufficient strength and appropriate rigidity, but also be able to isolate or absorb the vibrations generated when the engine / propeller is working, to prevent the vibrations from interfering with the sensors and flight control system. It must also be especially prevented from resonating with the fuselage structure, which could cause damage to the UAV structure.
[0004] Currently, engine mounting brackets mostly employ vibration damping devices, such as installing elastic rubber pads on the engine mount joints or at the connection points between the engine mount and the UAV. Regardless of the method used, maintaining a certain level of rigidity in the engine mounting structure remains a challenge. If the engine mounting structure has high rigidity, the vibration damping effect is poor. If the engine mounting structure has low rigidity, it may effectively isolate or absorb and reduce the vibrations transmitted from the engine to the UAV, but excessive rigidity can cause the propeller thrust line to deviate, leading to a decline in power system performance and even safety accidents. Furthermore, insufficient rigidity can cause wide-amplitude vibrations in the engine and propeller. Long-term vibrations can lead to loosening and failure of mechanical connections, fuel systems, and engine electrical system connections, posing safety hazards. It can also exacerbate wear on internal bearings and gears, as well as the propeller mounting structure.
[0005] Therefore, there is a need to provide an engine mounting bracket to solve the above problems. Utility Model Content
[0006] In order to reduce the vibration transmitted from the engine to the fuselage and ensure that it does not cause wide-amplitude vibrations in the engine and propeller itself, this utility model provides an engine mounting bracket to solve the existing problems.
[0007] The engine mounting bracket of this utility model adopts the following technical solution, including:
[0008] The main support plate is vertically installed on the fuselage frame plate inside the fuselage and parallel to the longitudinal section of the fuselage. The engine is installed on it.
[0009] Multiple mounting ears are evenly distributed on the edge of the main support plate, and the plane normals of all mounting ears converge at the center of gravity of the engine after installation.
[0010] A double-layer isolation and vibration damping device is installed between each mounting lug and the corresponding inner wall of the fuselage to attenuate and isolate the vibration of the engine and propeller twice to achieve vibration reduction.
[0011] And an anti-torsion device, which is set between the two opposite edges of the inner wall of the fuselage and the main support plate, to limit the torsion of the main support plate around the length of the fuselage.
[0012] Preferably, the fuselage frame plate is provided with multiple mounting seats, wherein the double-layer isolation and vibration damping device is installed between each mounting ear and the corresponding mounting seat.
[0013] Preferably, the double-layer isolation vibration damping device includes:
[0014] The vibration damping strut has its ends inserted into the mounting holes opened on the mounting ears and mounting bases, and two baffles are symmetrically arranged on the vibration damping strut about its center.
[0015] Two vibration damping components are fitted onto the vibration damping support on opposite sides of the two baffles. One vibration damping component is fitted into the mounting hole of the mounting ear, and the other vibration damping component is fitted into the mounting hole on the mounting base.
[0016] And flat washers, which are screwed to the ends of the vibration damping struts to form an installation limiting structure with the corresponding baffles.
[0017] Preferably, the isolation and vibration damping assembly includes:
[0018] The vibration damping bushing has its inner ring fitted on the vibration damping support between the baffle and the corresponding vibration damping flat pad, its outer ring fitted in the mounting hole, and its axial end is concentrically provided with a connecting sleeve.
[0019] And vibration damping pads, which are fitted onto the connecting sleeve;
[0020] Both the vibration damping bushing and the vibration damping pad are made of rubber.
[0021] Preferably, the anti-torsion device includes:
[0022] The bracket assembly has two coaxially arranged torsion bars that are rotatably mounted along its length, and the opposite ends of the two torsion bars are connected by a coupling.
[0023] A torque arm is positioned at one end of two torque bars that are facing away from each other.
[0024] And a spherical bearing, one end of which is connected to the torque arm, and the other end of which is connected to the corresponding side of the connecting lug and the main support plate.
[0025] Preferably, the bracket assembly includes:
[0026] The bracket support plate has a torsion bar support lug along its length, and the torsion bar support lug has a bearing mounting hole. A nylon flange bearing is installed in the bearing mounting hole, and the torsion bar is fixed to the inner ring of the nylon flange bearing.
[0027] And bracket mounting holes are provided on the bracket support plate.
[0028] Preferably, the torque arm includes:
[0029] The torque arm body has a square hole and a clamping groove on its side, and the square hole and the clamping groove are connected. The square hole is used to insert into the torque rod.
[0030] The screw hole is located on the torque arm body and extends through the clamping groove.
[0031] A connecting hole is formed at the end of the torque arm body and passes through the clamping groove, used for connecting with the end of the spherical bearing.
[0032] Preferably, the spherical plain bearing includes:
[0033] External thread spherical plain bearings and internal thread spherical plain bearings, with a threaded connection between the external thread spherical plain bearings and the internal thread spherical plain bearings;
[0034] Both the external thread spherical plain bearing and the internal thread spherical plain bearing have universal ball joints at their ends; the universal ball joint at the end of the external thread spherical plain bearing is threaded to the connecting hole by a screw, and the universal ball joint of the internal thread spherical plain bearing is threaded to the connecting lug by a screw.
[0035] Preferably, the mounting base includes: a U-shaped component, the bottom of which has a first mounting hole for connecting the U-shaped component with a U-shaped groove, and a connecting corner piece is provided on each of the two opposite sides of the two ends, and the two connecting corner pieces are inclined, and the connecting corner pieces are used to connect with the fuselage frame.
[0036] Preferably, multiple weight-reducing holes are evenly distributed on the main support plate.
[0037] The beneficial effects of this utility model are:
[0038] By setting up a double-layer isolation vibration damping device, the vibration damping effect is significantly improved compared with the traditional single-layer isolation vibration damping device. It can also compensate for the thermal and mechanical deformation of the engine under various conditions. Secondly, through the anti-torsion device, the torsional vibration of the engine and propeller in the direction of fuselage length caused by aerodynamic fluctuations, imbalance or installation errors can be limited, ensuring the safety and stability of power transmission. Attached Figure Description
[0039] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0040] Figure 1 This is a schematic diagram of the overall structure of an engine mounting bracket according to the present invention;
[0041] Figure 2 yes Figure 1 The left view;
[0042] Figure 3 This is a schematic diagram of the installation of the engine mounting bracket of this utility model on a drone;
[0043] Figure 4 This invention is in Figure 3 Installation details diagram;
[0044] Figure 5 This is a structural schematic diagram of the main support plate of this utility model;
[0045] Figure 6 This is a schematic diagram of the structure of the double-layer isolation and vibration damping device of this utility model;
[0046] Figure 7 This is a structural schematic diagram of the vibration damping support column of this utility model;
[0047] Figure 8 This is a schematic diagram of the structure of the mounting base of this utility model;
[0048] Figure 9 This is a schematic diagram of the anti-torsion device of this utility model;
[0049] Figure 10 This is a structural schematic diagram of the bracket assembly of this utility model;
[0050] Figure 11 This is a schematic diagram of the structure of the torsion bar of this utility model;
[0051] Figure 12This is a schematic diagram of the structure of the torsion arm of this utility model;
[0052] Figure 13 This is a schematic diagram of the structure of the spherical bearing of this utility model;
[0053] Figure 14 This is a schematic diagram of the structure of the mounting support of this utility model;
[0054] Figure 15 This is a schematic diagram of the structure of the vibration damping bushing of the present invention;
[0055] Figure 16 This is a schematic diagram of the structure of the vibration damping pad of the present invention.
[0056] In the diagram: 1. Main support plate; 2. Vibration damping device; 3. Mounting base; 4. Anti-torsion device; 5. Mounting support column; 6. Fuselage frame plate; 7. Engine; 8. Propeller; 11. Weight reduction hole; 12. Weight reduction groove; 13. Mounting lug; 14. Vibration damping device mounting hole; 15. Mounting support column mounting hole; 16. Connecting lug mounting hole; 21. Flat washer; 22. Vibration damping support column; 23. Vibration damping pad; 24. Vibration damping bushing; 25. Screw; 31. Center mounting hole; 32. Mounting corner piece. 33. Mounting hole for mounting corner piece; 41. Bracket assembly; 42. Torsion bar; 43. Coupling; 44. Nylon flange bearing; 45. Torsion arm; 46. Spherical plain bearing; 47. Connecting lug; 411. Torsion bar support lug; 412. Nylon flange bearing mounting hole; 413. Bracket mounting hole; 451. Square hole; 452. Clamping groove hole; 453. Clamping threaded hole; 454. Connecting threaded hole; 461. External thread spherical plain bearing; 462. Internal thread spherical plain bearing. Detailed Implementation
[0057] 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, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0058] An embodiment of the engine mounting bracket of this utility model is provided for ease of explanation. Figure 1 and Figure 2As shown, the orientation of the engine mounting bracket is described using the following right-hand rectangular coordinate system: X-axis - along the longitudinal axis of the UAV fuselage (i.e., the length direction of the fuselage), pointing forward is positive; Y-axis - along the vertical axis of the UAV fuselage, pointing downward is positive; Z-axis - along the transverse axis of the UAV fuselage, pointing left is positive. It includes: a main support plate 1, a double-layer isolation and vibration damping device 2, and an anti-torsion device 4. The main support plate 1 is vertically mounted on the fuselage frame plate 6 inside the fuselage and parallel to the longitudinal section of the fuselage. The engine is mounted on the main support plate 1. Figure 5 As shown, four mounting ears 13 are evenly distributed along the edge of the main support plate 1. In this embodiment, the main support plate 1 extends four mounting ears 13 backward (in the negative X-axis direction) towards the UAV. The plane normals of the four mounting ears 13 form the same angle with the X-axis, and the plane normals of the four mounting ears 13 converge at a point, which is the center of gravity of the engine after installation. This design can absorb and reduce the vibration transmitted from the engine to the fuselage in the X, Y, and Z axes. A double-layer isolation and vibration damping device 2 is disposed between each mounting ear 13 and the corresponding inner wall of the fuselage, used to attenuate and isolate the vibration of the engine and propeller twice to achieve vibration reduction. An anti-torsion device 4 is disposed between the inner wall of the fuselage and two opposite edges of the main support plate 1, used to limit the torsion of the main support plate 1 around the length of the fuselage. It should be noted that... Figure 3 As shown, the engine 7 is mounted on the fuselage frame 6 inside the UAV via an engine mounting bracket, and a propeller 8 is mounted on the output shaft of the engine 7.
[0059] For example, in one specific embodiment, such as Figure 1 and Figure 4 As shown, four mounting bases 3 are fixedly installed on the fuselage frame plate 6. A double-layer isolation and vibration damping device 2 is installed between each mounting lug 13 and its corresponding mounting base 3. For example... Figure 8 As shown, in one specific embodiment, the mounting base 3 includes: a U-shaped component, the bottom of which has a first mounting hole 31 for connecting the U-shaped component to the U-shaped groove, and a connecting corner piece 32 is provided on each of the two opposite sides of the two ends of the component, and the two connecting corner pieces 32 are inclined. The connecting corner pieces 32 are used to connect with the fuselage frame 6. In this embodiment, two mounting corner pieces 32 extend forward (in the positive direction of the fuselage X-axis) from both ends of the mounting base 3, and the mounting corner pieces 32 of the four mounting bases 3 are all in the same plane. Each mounting corner piece 32 is designed with one mounting corner piece mounting hole 33, so that each mounting base 3 can be connected to the fuselage frame plate 6 by two screws passing through the corresponding mounting corner piece mounting hole 33.
[0060] For example, such as Figure 6 As shown, in one specific embodiment, the double-layer isolation vibration damping device 2 includes: a vibration damping support column 22, the end of which passes through the second mounting hole 14 opened on the mounting ear 13 and the first mounting hole 31 of the mounting base 3, as shown. Figure 7 As shown, two baffles are symmetrically arranged about its center on the vibration damping strut 22; an isolation vibration damping component is installed on each of the vibration damping struts 22 on the opposite side of the two baffles; the flat washer 21 is set at the end of the vibration damping strut 22 by screws 25, and the flat washer 21 is used to form an installation limiting structure with the corresponding baffle. It should be noted that the double-layer isolation vibration damping device attenuates and isolates the vibration of the engine and propeller twice, which significantly improves the vibration damping effect.
[0061] Among them, such as Figure 6 As shown, in one specific embodiment, the isolation and vibration damping assembly includes: a vibration damping bushing 24 and a vibration damping pad 23, wherein, as Figure 15 and Figure 16 As shown, both the vibration damping bushing 24 and the vibration damping pad 23 are made of rubber. The inner ring of the vibration damping bushing 24 is fitted onto the vibration damping support 22 between the baffle and the corresponding vibration damping flat pad 21. The outer ring of the vibration damping bushing 24 is fitted into the mounting hole, and a connecting sleeve is concentrically provided at the axial end of the vibration damping bushing 24. The vibration damping pad 23 is fitted onto the connecting sleeve. It should be noted that both the vibration damping bushing 24 and the vibration damping pad 23 are existing technical structures, and will not be described in detail in this embodiment.
[0062] It should be noted that, as Figure 2 As shown, the first isolation and vibration damping component in the double-layer isolation and vibration damping device 2 is located on the P-plane, and the second isolation and vibration damping component is located on the Q-plane. Compared with the single-layer isolation and vibration damping device, the double-layer isolation and vibration damping device significantly improves the vibration damping effect. Each layer of isolation and vibration damping component is composed of a vibration damping pad 23 and a vibration damping bushing 24 to complete the vibration damping function.
[0063] For example, such as Figure 9 As shown, in one specific embodiment of the double-layer isolation vibration damping device 2, the anti-torsion device 4 includes: a bracket assembly 41, a torque arm 45, and a spherical bearing 46. The bracket assembly 41 is rotatably provided with two coaxially arranged torque rods 42 along its length direction, and the opposite ends of the two torque rods 42 are connected by a coupling 43. The torque arm 45 is provided at one end of the two torque rods 42 that are opposite to each other. One end of the spherical bearing 46 is connected to the torque arm 45, and the other end of the spherical bearing 46 is connected to the corresponding side end face of the main support plate 1 through a connecting lug 47.
[0064] Among them, such as Figure 10As shown, in one specific embodiment, the bracket assembly 41 includes: a bracket support plate, with a torsion bar support lug 411 arranged along its length direction, and a bearing mounting hole 412 opened on the torsion bar support lug 411, a nylon flange bearing 44 installed in the bearing mounting hole 412, wherein the torsion bar 42 is fitted and fixed to the inner ring of the nylon flange bearing 44; a bracket mounting hole 413 is opened on the bracket support plate, and the bracket support plate is fixed to the machine frame 6 by screws passing through the bracket mounting hole 413.
[0065] Among them, such as Figure 12 As shown, in one specific embodiment, the torque arm 45 includes: a torque arm body, a screw hole 453, and a connecting hole 454. A square hole 451 and a clamping groove 45 are provided on the side of the torque arm body, and the square hole 451 and the clamping groove 45 are connected. The square hole 451 is used to insert into the torque rod 42. The screw hole 453 is provided on the torque arm body and passes through the clamping groove 452. The connecting hole 454 is provided at the end of the torque arm body and passes through the clamping groove 452, and is used to connect to the end of the spherical bearing 46.
[0066] Among them, such as Figure 13 As shown, in one specific embodiment, the spherical bearing 46 includes: an externally threaded spherical bearing 461 and an internally threaded spherical bearing 462, and the externally threaded spherical bearing 461 and the internally threaded spherical bearing 462 are threadedly connected; wherein, the ends of the externally threaded spherical bearing 461 and the internally threaded spherical bearing 462 are both ball joints; the ball joint at the end of the internally threaded spherical bearing 462 is threadedly connected to the connecting hole 454 by screws, and the ball joint of the externally threaded spherical bearing 461 is mounted on the connecting lug 47 by screws, wherein, as Figure 5 As shown, each side of the main support plate 1 has two mounting holes 16 for connecting lugs 47. The mounting holes 16 are used to install the connecting lugs 47 of the anti-torsion device 4, so as to connect the anti-torsion device 4 and the main support plate 1.
[0067] It should be noted that in this embodiment, the nylon flange bearing 44 is made of nylon, which is lightweight and provides support and lubrication during the rotation of the torsion bar. Figure 11As shown, one end of the torsion bar 42 is square and inserts into the square hole 451 on the torsion arm 45; the other end of the torsion bar 42 is wedge-shaped, with an included angle of 60° between the two faces of the wedge. During installation, the wedge-shaped end is inserted into the hole of the coupling 43, and a set screw is used to hold the two planes of the wedge-shaped end in place, preventing relative rotation between the torsion bar 42 and the coupling 43. Therefore, the two torsion bars 42 are connected by the coupling 43 into a single unit that does not rotate relative to each other. After the square end of the torsion bar 42 is inserted into the square hole 451 of the torsion arm 45, a screw is screwed into the screw hole 453 on the side of the torsion arm 45, causing a certain deformation of the clamping slot 452. At this time, the square hole 451 can clamp the torsion bar 42, thereby preventing the torsion bar 42 from moving or falling out of the torsion arm 25. The spherical bearing has three degrees of rotational freedom. Because the engine itself vibrates continuously, and the propeller is affected by aerodynamic fluctuations, imbalances, or installation errors, insufficient rigidity of the engine mounting bracket in the X-axis direction can cause wide-amplitude vibrations in the engine and propeller, posing a significant hazard. The anti-torsion device 4 in this embodiment connects the main support plate 1 to the fuselage frame 6, thus limiting the torsional vibration of the engine mounting bracket and the engine around the X-axis.
[0068] For example, such as Figure 1 and Figure 14 It also includes: mounting strut 5, which is cylindrical with a through hole in the middle, and connects the main support plate 1, mounting strut 5, and engine by screws and nuts. The length of mounting strut 5 can be determined according to the gap between the engine and the fuselage frame plate or the engine nacelle bulkhead. This reserved gap can ensure the engine's heat dissipation and the installation space for engine accessories.
[0069] For example, in one specific embodiment, a plurality of weight-reducing holes are evenly distributed on the main support plate 1.
[0070] Working principle
[0071] During the operation of the UAV, both the engine 7 and the propeller 8 generate vibrations. These vibrations are transmitted through the main support plate 1 to the double-layer isolation and vibration damping device. The vibrations are attenuated twice by the damping bushings 24 and damping pads 23 of the two isolation and vibration damping components of the double-layer isolation and vibration damping device, significantly reducing the vibration amplitude. This prevents the vibrations of the engine 7 and propeller 8 from being transmitted to the UAV's fuselage, thus preventing damage to the UAV's avionics and fuselage structure. Furthermore, the anti-torsion device of this invention connects the main support plate to the fuselage, limiting the torsional vibration of the engine mounting bracket and the engine around the propeller's rotation axis, increasing the rigidity of the engine mounting bracket.
[0072] In summary, the engine mounting bracket implemented by this invention possesses both sufficient strength and suitable rigidity. Compared to single-layer isolation and vibration damping devices, the double-layer isolation and vibration damping device of this invention significantly improves the vibration damping effect. Furthermore, this invention also incorporates an anti-torsion device, which can limit the torsional vibration of the engine and propeller around the X-axis, ensuring the safety and stability of power transmission.
[0073] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.
Claims
1. An engine mount characterized by, include: The main support plate is vertically installed on the fuselage frame plate inside the fuselage and parallel to the longitudinal section of the fuselage. The engine is installed on it. Multiple mounting ears are evenly distributed on the edge of the main support plate, and the plane normals of all mounting ears converge at the center of gravity of the engine after installation. A double-layer isolation and vibration damping device is installed between each mounting lug and the corresponding inner wall of the fuselage to attenuate and isolate the vibration of the engine and propeller twice to achieve vibration reduction. And an anti-torsion device, which is set between the two opposite edges of the inner wall of the fuselage and the main support plate, to limit the torsion of the main support plate around the length of the fuselage.
2. The engine mounting bracket according to claim 1, characterized in that, Multiple mounting bases are provided on the fuselage frame plate, among which, a double-layer isolation and vibration damping device is installed between each mounting ear and the corresponding mounting base.
3. An engine mount as claimed in claim 2, wherein The double-layer isolation and vibration damping device includes: The vibration damping strut has its ends inserted into the mounting holes opened on the mounting ears and mounting bases, and two baffles are symmetrically arranged on the vibration damping strut about its center. Two vibration damping components are fitted onto the vibration damping support on opposite sides of the two baffles. One vibration damping component is fitted into the mounting hole of the mounting ear, and the other vibration damping component is fitted into the mounting hole on the mounting base. And flat washers, which are screwed to the ends of the vibration damping struts to form an installation limiting structure with the corresponding baffles.
4. An engine mount as claimed in claim 3, wherein The vibration isolation and damping components include: The vibration damping bushing has its inner ring fitted on the vibration damping support between the baffle and the corresponding vibration damping flat pad, its outer ring fitted in the mounting hole, and a connecting sleeve concentrically provided at its axial end. And vibration damping pads, which are fitted onto the connecting sleeve; Both the vibration damping bushing and the vibration damping pad are made of rubber.
5. An engine mount as in claim 1, wherein, The anti-torsion device includes: The bracket assembly has two coaxially arranged torsion bars that are rotatably mounted along its length, and the opposite ends of the two torsion bars are connected by a coupling. A torque arm is positioned at one end of two torque bars that are facing away from each other. And a spherical bearing, one end of which is connected to the torque arm, and the other end of which is connected to the corresponding side of the connecting lug and the main support plate.
6. An engine mount as claimed in claim 5, wherein The bracket assembly includes: The bracket support plate has a torsion bar support lug along its length, and the torsion bar support lug has a bearing mounting hole. A nylon flange bearing is installed in the bearing mounting hole, and the torsion bar is fixed to the inner ring of the nylon flange bearing. And bracket mounting holes are provided on the bracket support plate.
7. An engine mount as defined in claim 5 wherein, Torque arms include: The torque arm body has a square hole and a clamping groove on its side, and the square hole and the clamping groove are connected. The square hole is used to insert into the torque rod. The screw hole is located on the torque arm body and extends through the clamping groove. A connecting hole is formed at the end of the torque arm body and passes through the clamping groove, used for connecting with the end of the spherical bearing.
8. An engine mount as claimed in claim 7, characterised in that Spherical plain bearings include: External thread spherical plain bearings and internal thread spherical plain bearings, with a threaded connection between the external thread spherical plain bearings and the internal thread spherical plain bearings; Both the external thread spherical plain bearing and the internal thread spherical plain bearing have universal ball joints at their ends; the universal ball joint at the end of the external thread spherical plain bearing is threaded to the connecting hole by a screw, and the universal ball joint of the internal thread spherical plain bearing is connected to the connecting lug by a screw.
9. An engine mount as in claim 2, wherein: The mounting base includes: The U-shaped component has a first mounting hole at its bottom for connecting the U-shaped component with a U-shaped groove. Each of its two opposite ends is provided with a connecting corner piece, and the two connecting corner pieces are set at an angle. The connecting corner pieces are used to connect with the fuselage frame.
10. An engine mount as in claim 1, wherein, Multiple weight-reducing holes are evenly distributed on the main support plate.