Rigid vibration isolation mounting mechanism for medical cabin of unmanned helicopter

Abstract

The utility model relates to a rigid vibration isolation mounting mechanism for a medical cabin of an unmanned helicopter, belongs to the technical field of unmanned helicopters, and solves the technical problems in the prior art that the medical cabin is hung by using a flexible rope, the swing amplitude of the medical cabin is large, the wounded person feels uncomfortable, the change range of the gravity center of the unmanned helicopter is large, and the flight safety is reduced. The device comprises a fixed cross beam which is arranged at the lower part of a medical cabin; connecting parts are arranged at two ends of the fixed beam; a fuselage cross beam; one end of the rigid pull rod is fixed to the connecting part, and the other end is fixed to the fuselage beam; one end of the vibration isolation assembly is fixed to the undercarriage longitudinal pry, and the other end of the vibration isolation assembly is provided with a vibration isolation groove which is arranged at the end of the fixed cross beam in a sleeving mode. Rigid connection between the medical cabin and the unmanned helicopter is achieved through the rigid pull rod, the structure is simple, mounting, mounting and dismounting are rapid, vibration of the medical cabin is reduced, and comfort and safety of the medical cabin loaded on the unmanned helicopter are improved.

Description

Technical Field

[0001] The utility model relates to the fields of aviation technology and medical rescue, in particular to a rigid vibration isolation mounting mechanism for a medical cabin of an unmanned helicopter. Background Art

[0002] In the existing field of aviation medical rescue, manned helicopters are mainly used. Manned helicopters have a spacious cabin where the wounded can lie flat.

[0003] With the rapid development of unmanned helicopters, it is necessary to build an unmanned intelligent medical rescue support system. In the existing unmanned helicopters, the transportation of materials mainly relies on flexible rope suspension. The medical cabin suspended by the flexible rope has a large swing amplitude, which easily causes discomfort to the wounded and is not suitable for transporting the wounded. The center of gravity of the unmanned helicopter changes within a large range, reducing the safety of the unmanned helicopter during flight. Summary of the Utility Model

[0004] In view of the above analysis, the embodiment of the utility model aims to provide a rigid vibration isolation mounting mechanism for a medical cabin of an unmanned helicopter. A fixed crossbeam is arranged at the lower part of the medical cabin, and the fixed crossbeam fixing the medical cabin is rigidly connected to the unmanned helicopter by using a rigid pull rod. At the same time, a vibration isolation component is arranged between the fixed crossbeam and the landing gear of the unmanned helicopter to solve the problems of discomfort and insecurity caused by suspending the medical cabin with a flexible rope in the prior art.

[0005] The purpose of the utility model is mainly achieved by the following technical solutions:

[0006] A rigid vibration isolation mounting mechanism for a medical cabin of an unmanned helicopter, which comprises:

[0007] A fixed crossbeam, which is arranged at the lower part of the medical cabin; connection parts are arranged at both ends of the fixed crossbeam;

[0008] A fuselage crossbeam, which is fixed at the lower part of the unmanned helicopter;

[0009] A rigid pull rod, one end of which is fixed to the connection part; the other end of the rigid pull rod is fixed to the fuselage crossbeam;

[0010] A vibration isolation component, one end of which is fixed on the longitudinal skid of the landing gear, and the other end of the vibration isolation component is a vibration isolation groove provided with vibration isolation rubber, and the vibration isolation groove sleeves the end of the fixed crossbeam.

[0011] Further, a first assembly hole for fixing the connection part is opened at one end of the rigid pull rod, and a second assembly hole for fixing the fuselage crossbeam is opened at the other end of the rigid pull rod.

[0012] Further, the connection part comprises:

[0013] A connecting piece is fixed on the fixed cross beam, and a first fixing hole is opened at a position corresponding to the first assembly hole of the connecting piece;

[0014] A fixing piece passes through the first fixing hole and the first assembly hole to fix one end of the rigid pull rod to the connecting part.

[0015] Furthermore, the connecting part further includes a damping rubber, which is arranged between the fixing piece and the connecting piece, and between the fixing piece and the rigid pull rod.

[0016] Furthermore, it further includes:

[0017] A first flange is arranged on the fuselage cross beam;

[0018] A second flange is arranged opposite to the first flange, and the second flange is fixedly connected to the first flange;

[0019] A connecting rod, one end of which is arranged on the end face of the second flange away from the first flange; the other end of the connecting rod passes through the second assembly hole.

[0020] Furthermore, it further includes an opening pin;

[0021] A limiting hole is opened at the other end of the connecting rod; the opening pin is inserted into the limiting hole to fix the other end of the rigid pull rod to the fuselage cross beam.

[0022] Furthermore, the vibration isolation component includes two relatively arranged vibration isolation pieces and a fastener for fixedly connecting the two vibration isolation pieces.

[0023] Furthermore, the vibration isolation piece includes a semi-circular clamp;

[0024] The fastener is arranged at both ends of the two semi-circular clamps, and the two semi-circular clamps are clamped and fixed to the landing gear longitudinal skid.

[0025] Furthermore, the vibration isolation groove is formed by splicing two L-shaped groove structures; one end of the L-shaped groove structure is fixed to the semi-circular clamp.

[0026] Furthermore, it further includes a fuselage longitudinal beam arranged at the lower part of the unmanned helicopter, and the fuselage cross beam is fixed to the fuselage longitudinal beam.

[0027] Compared with the prior art, the present utility model can at least achieve one of the following beneficial effects:

[0028] (1) The rigid vibration isolation mounting mechanism of the medical cabin for an unmanned helicopter of the present utility model sets a fixed crossbeam at the lower part of the medical cabin, and realizes the rigid connection between the medical cabin and the unmanned helicopter by using rigid tie rods. The structure is simple, which realizes the rapid mounting, installation and disassembly of the medical cabin, reduces the vibration of the medical cabin, prolongs the service life of the medical cabin, and improves the comfort and safety of carrying the medical cabin on the unmanned helicopter.

[0029] (2) The rigid vibration isolation mounting mechanism of the medical cabin for an unmanned helicopter of the present utility model sets a vibration isolation component between the fixed crossbeam and the landing gear of the unmanned helicopter. The vibration isolation groove provided with vibration isolation rubber is sleeved on the end of the fixed crossbeam to limit the front-back, left-right swing of the medical cabin, and increases the operation stability when the unmanned helicopter carries the medical cabin in flight.

[0030] (3) The rigid vibration isolation mounting mechanism of the medical cabin for an unmanned helicopter of the present utility model sets damping rubber on the connecting parts at both ends of the fixed crossbeam, which can reduce the vibration transmission of the unmanned helicopter to the medical cabin, lower the vibration level in the medical cabin, and increase the comfort of transporting the wounded.

[0031] In the present utility model, the above technical solutions can also be combined with each other to realize more preferred combined solutions. Other features and advantages of the present utility model will be described in the following content. Moreover, some advantages can be made obvious from the description, or can be understood by implementing the present utility model. The purpose and other advantages of the present utility model can be achieved and obtained through the content specifically pointed out in the text and the drawings. Brief Description of the Drawings

[0032] The drawings are only for the purpose of showing specific embodiments, and are not considered as a limitation to the present utility model. Throughout the drawings, the same reference signs represent the same components.

[0033] Figure 1 It is a schematic structural diagram of an unmanned helicopter using the rigid vibration isolation mounting mechanism of the medical cabin for an unmanned helicopter of the present utility model to mount the medical cabin;

[0034] Figure 2 It is a schematic structural diagram of the rigid vibration isolation mounting mechanism of the medical cabin for an unmanned helicopter in a specific embodiment;

[0035] Figure 3 For Figure 2 The partial enlarged structural diagram of A in

[0036] Figure 4 For Figure 2 The partial enlarged structural diagram of B in

[0037] Figure 5 It is the partial enlarged structural diagram of the vibration isolation component in a specific embodiment.

[0038] Reference Signs:

[0039] 1 - Unmanned helicopter; 2 - Medical cabin; 3 - Fixed crossbeam; 31 - Connection part; 311 - Connecting piece; 312 - Fixing piece; 313 - Vibration damping rubber; 4 - Fuselage crossbeam; 5 - Rigid tie rod; 51 - First assembly hole; 52 - Second assembly hole; 6 - Vibration isolation assembly; 61 - Vibration isolation groove; 611 - L-shaped groove structure; 62 - Vibration isolation rubber; 63 - Semi-circular clamp; 7 - First flange; 8 - Second flange; 9 - Connecting rod; 91 - Split pin; 10 - Fuselage longitudinal beam. Detailed Embodiment

[0040] The following will specifically describe the preferred embodiments of the present invention in conjunction with the accompanying drawings. Among them, the accompanying drawings form a part of the present invention and are used together with the embodiments of the present invention to explain the principle of the present invention, rather than to limit the scope of the present invention.

[0041] A specific embodiment of the present invention, as Figure 1 and Figure 2 shown, discloses a rigid vibration isolation mounting mechanism for the medical cabin of an unmanned helicopter, which includes:

[0042] A fixed crossbeam 3, which is arranged at the lower part of the medical cabin 2; both ends of the fixed crossbeam 3 are provided with connection parts 31;

[0043] A fuselage crossbeam 4, which is fixed at the lower part of the unmanned helicopter 1;

[0044] A rigid tie rod 5, one end of which is fixed to the connection part 31; the other end of the rigid tie rod 5 is fixed to the fuselage crossbeam 4;

[0045] A vibration isolation assembly 6, one end of which is fixed on the landing gear skid, and the other end of the vibration isolation assembly 6 is a vibration isolation groove 61 internally provided with vibration isolation rubber 62, and the vibration isolation groove 61 is sleeved on the end of the fixed crossbeam 3.

[0046] In this embodiment, the two ends of the rigid tie rod 5 are respectively fixedly connected to the fuselage crossbeam 4 at the lower part of the unmanned helicopter 1 and the fixed crossbeam 3 at the lower part of the medical cabin 2, so as to rigidly fix the medical cabin 2 to the unmanned helicopter 1. Its structure is simple, and rapid mounting, installation and disassembly can be realized; by adopting the rigid vibration isolation mounting mechanism, the vibration of the medical equipment in the medical cabin 2 can be reduced, and the service life of the medical cabin 2 can be prolonged. At the same time, by using the vibration isolation assembly 6, the vibration of the medical cabin 2 during transportation can be reduced, the service life of the medical cabin 2 can be prolonged, and the comfort and safety of the transportation of the medical cabin 2 can be ensured.

[0047] One end of the rigid pull rod 5 is provided with a first assembly hole 51 for fixing the connecting part 31, and the other end of the rigid pull rod 5 is provided with a second assembly hole 52 for fixing the fuselage cross beam 4. The first assembly hole 51 and the second assembly hole 52 are used to complete the quick assembly connection and disassembly with the medical cabin 2 and the unmanned helicopter 1.

[0048] As Figure 3 shown, the connecting part 31 includes:

[0049] A connecting piece 311, which is fixed on the fixed cross beam 3, and a first fixing hole is provided at a position corresponding to the first assembly hole 51 on the connecting piece 311;

[0050] A fixing piece 312, which passes through the first fixing hole and the first assembly hole 51 to fix one end of the rigid pull rod 5 to the connecting part 31.

[0051] The connecting part 31 further includes a damping rubber 313, which is arranged between the fixing piece 312 and the connecting piece 311, and between the fixing piece 312 and the rigid pull rod 5.

[0052] The fixing piece 312 passes through the first fixing hole and the first assembly hole 51 to fixedly connect the rigid pull rod 5 and the fixed cross beam 3, thereby realizing the fixed connection between the medical cabin 2 and the rigid pull rod 5. At the same time, the damping rubber 313 is provided to reduce the vibration transmission from the unmanned helicopter 1 to the medical cabin 2.

[0053] As Figure 4 shown, it further includes a flange assembly, which includes:

[0054] A first flange 7, which is arranged on the fuselage cross beam 4;

[0055] A second flange 8, which is arranged opposite to the first flange 7, and the second flange 8 is fixedly connected to the first flange 7;

[0056] A connecting rod 9, one end of which is arranged on the end face of the second flange 8 away from the first flange 7; the other end of the connecting rod 9 passes through the second assembly hole 52;

[0057] An opening pin 91;

[0058] Wherein, a limiting hole is provided at the other end of the connecting rod 9; the opening pin 91 is inserted into the limiting hole to fix the other end of the rigid pull rod 5 to the fuselage cross beam 4.

[0059] The rigid pull rod 5 is connected to the flange assembly through a transition fit, fixed by bolts, and the opening pin 91 is used to prevent loosening. By using the connection between the rigid pull rod 5 and the flange assembly, the fixed connection between the rigid pull rod 5 and the fuselage cross beam 4 is realized.

[0060] The rigid tie rod 5 is a rod-shaped structure, one end of which is connected to the connecting part 31, and the other end of which is connected to a flange assembly provided on the fuselage cross beam 4. The rigid tie rod 5 is used to rigidly mount the medical cabin 2 to the unmanned helicopter 1.

[0061] As Figure 5 As shown, the vibration isolation assembly 6 includes two oppositely arranged vibration isolators and fasteners for fixedly connecting the two vibration isolators.

[0062] The vibration isolator includes a semi-circular clamp 63; the fasteners are arranged at both ends of the two semi-circular clamps 63, and the two semi-circular clamps 63 are clamped and fixed to the landing gear longitudinal skid.

[0063] The vibration isolation groove 61 is formed by splicing two L-shaped groove structures 611; one end of the L-shaped groove structure 611 is fixed to the semi-circular clamp 63.

[0064] The two semi-circular clamps 63 are clamped to the landing gear longitudinal skid, one fastener is fixed to one end of the two semi-circular clamps 63, the other fastener is fixed to the other end of the two semi-circular clamps 63, and the other fastener is located between the semi-circular clamp 63 and the L-shaped groove structure 611. The other fastener can not only fasten the two semi-circular clamps 63, but also adjust the distance between the L-shaped groove structures 611, and further adjust the size of the vibration isolation groove 61 to match different fixed cross beams 3.

[0065] In some embodiments, it further includes a fuselage longitudinal beam 10 provided at the lower part of the unmanned helicopter 1, and the fuselage cross beam 4 is fixed to the fuselage longitudinal beam 10.

[0066] The fuselage longitudinal beam 10 is fixed to the lower part of the unmanned helicopter 1, and the fuselage cross beam 4 is fixed to the fuselage longitudinal beam 10. The fuselage longitudinal beam 10 is a thin-walled circular tube structure and is connected to other structures of the fuselage by welding; the fuselage cross beam 4 is a thin-walled circular tube structure and is connected to the fuselage longitudinal beam 10 in the middle by welding. The fuselage longitudinal beam 10, the fuselage cross beam 4 and the rigid tie rod 5 provide a mounting force-bearing structure for the medical cabin 2.

[0067] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered by the protection scope of the present invention.

Claims

1. A rigid vibration isolation mounting mechanism for a medical cabin of an unmanned helicopter, characterized in that, Comprising: A fixed crossbeam (3), which is arranged at the lower part of the medical cabin (2); connection parts (31) are arranged at both ends of the fixed crossbeam (3); A fuselage crossbeam (4), which is fixed at the lower part of the unmanned helicopter (1); A rigid pull rod (5), one end of which is fixed to the connection part (31); the other end of the rigid pull rod (5) is fixed to the fuselage crossbeam (4); A vibration isolation assembly (6), one end of which is fixed on the landing gear skid, and the other end of the vibration isolation assembly (6) is a vibration isolation groove (61) internally provided with vibration isolation rubber (62), and the vibration isolation groove (61) sleeves the end of the fixed crossbeam (3).

2. The rigid vibration isolation mounting mechanism for the medical cabin of the unmanned helicopter according to claim 1, characterized in that One end of the rigid pull rod (5) is provided with a first assembly hole (51) for fixing the connection part (31), and the other end of the rigid pull rod (5) is provided with a second assembly hole (52) for fixing the fuselage crossbeam (4).

3. The rigid vibration isolation mounting mechanism for the medical cabin of the unmanned helicopter according to claim 2, characterized in that, The connection part (31) comprises: A connecting piece (311), which is fixed on the fixed crossbeam (3), and a first fixing hole is arranged at a position of the connecting piece (311) corresponding to the first assembly hole (51); A fixing piece (312), which passes through the first fixing hole and the first assembly hole (51) to fix one end of the rigid pull rod (5) to the connection part (31).

4. The rigid vibration isolation mounting mechanism for the medical cabin of the unmanned helicopter according to claim 3, wherein, The connection part (31) further comprises vibration isolation rubber (313), which is arranged between the fixing piece (312) and the connecting piece (311), and between the fixing piece (312) and the rigid pull rod (5).

5. The rigid vibration isolation mounting mechanism for the medical cabin of an unmanned helicopter according to claim 2, characterized in that, Further comprising: A first flange (7), which is arranged on the fuselage crossbeam (4); A second flange (8), which is arranged opposite to the first flange (7), and the second flange (8) is tightly connected to the first flange (7); A connecting rod (9), one end of which is arranged on the end face of the second flange (8) away from the first flange (7); the other end of the connecting rod (9) passes through the second assembly hole (52).

6. The rigid vibration isolation mounting mechanism for the medical cabin of the unmanned helicopter according to claim 5, wherein Further comprising an opening pin (91); A limiting hole is arranged at the other end of the connecting rod (9); the opening pin (91) is inserted into the limiting hole to fix the other end of the rigid pull rod (5) to the fuselage crossbeam (4).

7. The rigid vibration isolation mounting mechanism for the medical cabin of the unmanned helicopter according to claim 1, characterized in that The vibration isolation assembly (6) comprises two oppositely arranged vibration isolation parts and a fastener for fixedly connecting the two vibration isolation parts.

8. The rigid vibration isolation mounting mechanism for the medical cabin of the unmanned helicopter according to claim 7, characterized in that, The vibration isolation part comprises a semi-circular clamp (63), the fastener is arranged at both ends of the two semi-circular clamps (63), and the two semi-circular clamps (63) are clamped and fixed to the landing gear skid.

9. The rigid vibration isolation mounting mechanism for the medical cabin of the unmanned helicopter according to claim 8, characterized in that, The vibration isolation groove (61) is formed by splicing two L-shaped groove structures (611); One end of the L-shaped groove structure (611) is fixed to the semi-circular clamp (63).

10. The rigid vibration isolation mounting mechanism for the medical cabin of the unmanned helicopter according to claim 1, characterized in that, Further comprising a fuselage longitudinal beam (10) arranged at the lower part of the unmanned helicopter, and the fuselage crossbeam (4) is fixed to the fuselage longitudinal beam (10).

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