A helicopter load transfer and anti-sway structure and helicopter

Abstract

The invention discloses a helicopter load transfer and anti-sway structure and a helicopter, comprising an upper bearing beam, a lower bearing beam and a hanging plate; the upper bearing beam is located above the lower bearing beam, a bearing member is connected to the middle of the upper bearing beam, two ends of the upper bearing beam are bent toward two ends of the lower bearing beam, and the two ends of the upper bearing beam are rotatably connected with the two ends of the lower bearing beam, and the rotation direction is the circumferential direction of the lower bearing beam; a connecting member is nested in the middle of the lower bearing beam, and the connecting member extends toward the radial ends of the horizontal direction of the lower bearing beam, and the cross section of the extended end is circular; the top of the hanging plate is forked, and the two forks at the top of the hanging plate are respectively rotatably connected with the two extended ends of the connecting member, and the rotation direction is parallel to the length direction of the lower bearing beam. The damage to the helicopter hatch caused by the sway of cargo is effectively solved.

Description

Technical Field

[0001] The invention belongs to the field of helicopter hanging and dropping, and relates to a helicopter load transmission and anti-sway structure and a helicopter. Background Art

[0002] The helicopter hanging and delivery system can transport cargo quickly, flexibly and flexibly to designated locations because it does not require a dedicated airport and has no restrictions on the volume and shape of the cargo. It has advantages that cannot be matched by road, rail and fixed-wing aircraft transportation. In order to effectively reduce the weight of the fuselage, the main load-bearing point of the medium and heavy helicopter hanging and delivery system is designed on the base of the main reduction gearbox during structural design. In a domestic helicopter hanging and delivery system, the upper part of the cargo hook is connected to the lower end of the main reduction gearbox through a sling, and the lower end passes through the hatch of the helicopter's belly and uses a sling to hang the cargo. The swing of the cargo during the flight of the helicopter drives the swing of the sling, and the sling hanging the cargo constantly collides with the helicopter hatch, causing the helicopter hatch to deform or be damaged.

[0003] The existing load transfer mechanism transfers the load to the helicopter main reduction gearbox through a pull rod at the upper end. A set of crank mechanisms are designed on the rear hatch along the heading of the hatch. The cargo hook is installed on the rotating shaft at the front end of the crank through a spherical bearing. A set of connecting rods are installed on the rotating shaft of the cargo hook device and connected to the lower end of the pull rod installed at the lower end of the main reduction gearbox. When hanging cargo, the vertical load drives the crank to rotate around the crank shaft through the cargo hook and is transferred to the reduction gearbox base through the connecting rod. The load in the front, back, left and right directions is transferred to the crank through the rotating shaft where the cargo hook is installed, and then transferred to the helicopter hatch through the crank. The problem with this is that in order to balance the component force of the cargo perpendicular to the heading yaw, the crank and its mounting base must withstand a huge bending moment, so the strength of the crank and its mounting base design is extremely large and the weight is heavy. Summary of the invention

[0004] The purpose of the present invention is to overcome the above-mentioned shortcomings of the prior art and provide a helicopter load transfer and anti-sway structure and a helicopter, which effectively solves the damage to the helicopter hatch caused by the cargo sway.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A helicopter load transfer and anti-sway structure, comprising an upper bearing beam, a lower bearing beam and a hanging plate;

[0007] The upper bearing beam is located above the lower bearing beam, and a bearing member is connected to the middle part of the upper bearing beam. The two ends of the upper bearing beam are bent toward the two ends of the lower bearing beam, and the two ends of the upper bearing beam are rotatably connected to the two ends of the lower bearing beam, and the rotation direction is the circumferential direction of the lower bearing beam; a connecting member is nested in the middle part of the lower bearing beam, and the connecting member extends toward the radial ends of the horizontal direction of the lower bearing beam, and the cross-section of the extended end is circular; the top part of the hanging plate is forked, and the two forks on the top of the hanging plate are respectively rotatably connected to the two extended ends of the connecting member, and the rotation direction is parallel to the length direction of the lower bearing beam.

[0008] Preferably, U-shaped grooves are provided at both ends of the helicopter hatch, and both ends of the lower load-bearing beam are placed in the U-shaped grooves.

[0009] Furthermore, a cover plate is provided on the top of the U-shaped groove, and the cover plate is fixed to the helicopter hatch.

[0010] Preferably, annular grooves are provided at both ends of the helicopter hatch, and annular steps are provided at both ends of the lower bearing beam, and the annular steps are located in the annular grooves.

[0011] Preferably, both ends of the upper bearing beam and both ends of the lower bearing beam are connected by the first upper bearing shaft and the first lower bearing shaft, the lower bearing beam is nested in the middle of the first upper bearing shaft and the first lower bearing shaft, the first upper bearing shaft and the first lower bearing shaft both extend radially toward the horizontal direction of the lower bearing beam, the extended ends of the first upper bearing shaft and the first lower bearing shaft are fixedly connected, and the end of the upper bearing beam is connected to the first upper bearing shaft.

[0012] Furthermore, the end of the upper bearing beam is integrally arranged with the first upper bearing shaft.

[0013] Furthermore, the cross-section of the extended ends of the first upper bearing shaft and the first lower bearing shaft after being combined is circular, and threads are provided on the extended ends, and nuts are threadedly connected to the two extended ends.

[0014] Preferably, the bearing member is a metal rod, a steel wire rope or a fiber sling.

[0015] Preferably, the bearing member is a metal rod, and the metal rod is hinged to the upper bearing beam.

[0016] A helicopter comprises any one of the helicopter load transfer mechanism and anti-sway structure described above, wherein the bearing parts in the helicopter load transfer mechanism and the anti-sway structure are connected to the bearing seat of the helicopter main reduction box, and a cargo hook device is connected to the bottom of the hanging plate.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The present invention realizes a rotational connection between the two ends of the upper load-bearing beam and the two ends of the lower load-bearing beam, and a rotational connection between the hanging plate and the connecting piece. Both rotational directions are in the horizontal direction and are perpendicular to each other. When the cargo swings in any direction, the load can be partially offset by the rotation of the hanging plate or the rotation of the lower load-bearing beam, thereby preventing the main reduction gearbox of the helicopter from being subjected to forces along the heading or perpendicular to the heading.

[0019] Furthermore, when the cargo swings perpendicular to the heading, the two ends of the lower load-bearing beam can press against the side walls of the U-shaped groove on the helicopter hatch, transferring the heading load to the side walls of the U-shaped groove of the helicopter hatch.

[0020] Furthermore, the two ends of the lower bearing beam are restricted in the U-shaped groove by the cover plate, so as to prevent the lower bearing beam from escaping from the U-shaped groove and causing danger.

[0021] Furthermore, the annular step is located in the annular groove, which can limit the lower bearing beam. When the cargo has a heading load, the annular step on the lower bearing beam presses against the side wall of the helicopter hatch, transferring the heading load to the side wall of the helicopter hatch. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural schematic diagram of the present invention;

[0023] Figure 2 A diagram showing the connection relationship between the lower bearing beam and the upper bearing beam of the present invention;

[0024] Figure 3 This is a diagram showing the connection relationship between the hanger plate and the lower bearing beam of the present invention.

[0025] Among them: 1-load-bearing seat; 2-first pin; 3-first lifting ring; 4-bearing member; 5-second lifting ring; 6-second pin; 7-upper bearing beam; 8-first nut; 9-lower bearing beam; 10-annular step; 11-hanging plate; 12-cargo hook device; 13-second nut; 14-third pin; 15-annular groove; 16-first upper bearing; 17-first lower bearing; 18-second upper bearing; 19-second lower bearing; 20-U-shaped groove; 21-ring. DETAILED DESCRIPTION

[0026] The present invention is further described in detail below in conjunction with the accompanying drawings:

[0027] like Figure 1 As shown, the helicopter load transfer and anti-sway structure of the present invention includes a load-bearing seat 1 connected to the helicopter main reduction gearbox, a pull rod 4 is suspended on the load-bearing seat 1 through a first lifting ring 3 and a first pin 2 at the upper end, and the lower end of the pull rod 4 is connected to the middle part of the upper bearing beam 7 through a second lifting ring 5 and a second pin 6, so that the pull rod 4 can rotate flexibly.

[0028] The upper bearing beam 7 is located above the lower bearing beam 9. Figure 2 As shown, the lower bearing beam 9 is installed in the first upper bearing bush 16 and the first lower bearing bush 17 on the upper bearing beam 7. The lower bearing beam 9 is nested in the middle of the first upper bush shaft 16 and the first lower bush shaft 17. The first upper bush shaft 16 and the first lower bush shaft 17 both extend toward the radial ends of the horizontal direction of the lower bearing beam 9. The extended ends of the first upper bush shaft 16 and the first lower bush shaft 17 are fixedly connected. Specifically, the combined extended ends of the first upper bush shaft 16 and the first lower bush shaft 17 have a circular cross-section, and threads are provided on the extended ends. The two extended ends are threadedly connected with the first nut 8, and the first upper bearing bush 16 and the first lower bearing bush 17 are connected as a whole through the first nut 8. The end of the upper bearing beam 7 is integrally arranged with the first upper bush shaft 16. The upper bearing beam 7, the first upper bush shaft 16 and the first lower bush shaft 17 can be 3D printed as a complete part to be sleeved on the lower bearing beam 9.

[0029] There are shaft stops 10 at both ends of the lower bearing beam 9. Figure 3 As shown, the second upper bearing 18 and the second lower bearing 19 are encircled on the lower bearing beam 9, and the upper ends of the two hanging plates 11 are installed on the two-end round shafts formed by the second upper bearing 18 and the second lower bearing 19. There is a second nut 13 on the outer side of the hanging plate 11, which connects the second upper bearing 18 and the second lower bearing 19 into a whole. The lower end of the hanging plate 11 is connected to the cargo hook device 12 through the third pin 14. The second upper bearing 18 and the second lower bearing 19 can be 3D printed as a complete part and sleeved on the lower bearing beam 9, and the hanging plate 11 is also 3D printed as a complete part and sleeved on the extension shaft of the second upper bearing 18 and the second lower bearing 19.

[0030] U-shaped grooves 20 are provided at both ends of the helicopter hatch, and both ends of the lower bearing beam 9 are placed in the U-shaped grooves 20. A cover plate is provided on the top of the U-shaped groove 20, and the cover plate is fixed to the helicopter hatch. An annular groove is provided in the U-shaped groove 20, and an annular step 10 is provided at both ends of the lower bearing beam 9, and the annular step 10 is located in the annular groove; the annular step 10 can also be placed on the inner side of the hatch to limit the lower bearing beam 9. When the cargo has a load perpendicular to the heading, the annular step 10 on the lower bearing beam 9 presses against the side wall of the helicopter hatch, transferring the load perpendicular to the heading to the side wall of the helicopter hatch.

[0031] The lower bearing beam 9 can rotate in the first upper bearing bush 16 and the first lower bearing bush 17. The lower bearing beam 9 can also rotate in the second upper bearing bush 18 and the second lower bearing bush 19. At the same time, the hanging plate 11 can also rotate around the two-end circular shaft formed by the second upper bearing bush 18 and the second lower bearing bush 19. The cargo hook device 12 can rotate around the third pin shaft 14. The two ends of the lower bearing beam 9 can move up and down in the U-shaped grooves at the two ends of the helicopter hatch.

[0032] The pull rod 4, the first lifting ring 3 and the second lifting ring 5 can be three independent components or an integral component. The pull rod 4 can be a rod made of metal material, or a steel wire rope or a fiber sling.

[0033] The first pin 2, the second pin 6 and the third pin 14 can be quick-release pins or bolt-nut assemblies.

[0034] Annular grooves 15 are machined at both ends of the lower bearing beam 9 , and the first upper bearing shell 16 and the first lower bearing shell 17 are clamped in the annular grooves 21 .

[0035] Both ends of the first upper bearing shell 16 and the first lower bearing shell 17 are processed with semicircular threads, and the two bodies are combined to form a complete stud.

[0036] An annular groove 15 is machined in the middle of the lower bearing beam 9 , and the second upper bearing shell 18 and the second lower bearing shell 19 are clamped in the annular groove 15 .

[0037] Both ends of the second upper bearing bush 18 and the second lower bearing bush 19 are processed with semicircular threads and semicircular cylinders, and the two bodies are combined to form a complete stud and cylinder.

[0038] To facilitate assembly, a collar 21 may be installed inside the first nut 8 at both ends of the first upper bearing 16 and the first lower bearing 17 , and a collar 21 may be installed inside the hanger plate 11 at both ends of the second upper bearing 18 and the second lower bearing 19 .

[0039] The method for preventing deflection of the present invention is:

[0040] The load along the pull rod direction is transmitted to the third pin shaft 14 and the hanging plate 11 through the cargo hook device 12, and the load is transmitted to the second upper bearing 18 and the second lower bearing 19 through the hanging plate 11. The second upper bearing 18 and the second lower bearing 19 transmit the load to the lower load-bearing beam 9. The lower load-bearing beam 9 transmits the load to the first upper bearing 16 and the first lower bearing 17 and the upper load-bearing beam 7. The upper load-bearing beam transmits the load to the helicopter through the second pin shaft 6, the pull rod 4, the first lifting ring 3, the first lifting ring 3, the first pin shaft 2 and the load-bearing seat 1.

[0041] When the cargo has a load perpendicular to the heading, the cargo hook device 12 drives the entire mechanism to rotate around the first pin shaft 2, and the cargo hook device 12 drives the hanging plate 11 to rotate around the axes at both ends of the second upper bearing 18 and the second lower bearing 19, transferring the lateral load to the lower load-bearing beam 9. The lower load-bearing beam 9 is pressed against the side wall of the helicopter hatch, transferring the load perpendicular to the heading to the side wall of the helicopter hatch.

[0042] When the cargo swings along the heading, the cargo hook device 12 drives the entire mechanism to rotate around the first pin shaft 2, the cargo hook device 12 drives the hanging plate 11 to rotate around the circumference of the first upper bearing 16 and the first lower bearing 17, and drives the two ends of the lower load-bearing beam 9 to press against the side walls of the U-shaped groove 20 on the helicopter hatch, thereby transferring the heading load to the side walls of the U-shaped groove 20 of the helicopter hatch.

[0043] When the cargo swings in any direction, the load perpendicular to the heading is transferred to the side wall of the helicopter hatch through the annular step 10 on the lower load-bearing beam 9, and the heading load is transferred to the side wall of the U-shaped groove 20 on the helicopter hatch through the lower load-bearing beam 9.

[0044] The helicopter of the present invention comprises a helicopter load transfer mechanism and an anti-sway structure, wherein the bearing member 4 in the helicopter load transfer mechanism and the anti-sway structure is connected to the bearing seat 1 of the helicopter main reduction gearbox, and a cargo hook device 12 is connected to the bottom of the hanging plate 11.

[0045] The above contents are only for explaining the technical idea of ​​the present invention and cannot be used to limit the protection scope of the present invention. Any changes made on the basis of the technical solution in accordance with the technical idea proposed by the present invention shall fall within the protection scope of the claims of the present invention.

Claims

1. A helicopter load transfer and anti-sway structure, characterized in that: It comprises an upper bearing beam (7), a lower bearing beam (9) and a hanging plate (11); The upper bearing beam (7) is located above the lower bearing beam (9), the middle of the upper bearing beam (7) is connected to a bearing member (4), the two ends of the upper bearing beam (7) are bent toward the two ends of the lower bearing beam (9), and the two ends of the upper bearing beam (7) are rotatably connected to the two ends of the lower bearing beam (9), and the rotation direction is the circumferential direction of the lower bearing beam (9); a connecting member is embedded in the middle of the lower bearing beam (9), and the connecting member extends toward the radial ends of the lower bearing beam (9) in the horizontal direction, and the cross-section of the extended end is circular; the top of the hanging plate (11) is forked, and the two forks at the top of the hanging plate (11) are respectively rotatably connected to the two extended ends of the connecting member, and the rotation direction is parallel to the length direction of the lower bearing beam (9); Both ends of the upper bearing beam (7) and the lower bearing beam (9) are connected by a first upper bearing shaft (16) and a first lower bearing shaft (17); the lower bearing beam (9) is nested in the middle of the first upper bearing shaft (16) and the first lower bearing shaft (17); the first upper bearing shaft (16) and the first lower bearing shaft (17) both extend toward both ends of the lower bearing beam (9) in a horizontal radial direction; the extended ends of the first upper bearing shaft (16) and the first lower bearing shaft (17) are fixedly connected; and the end of the upper bearing beam (7) is connected to the first upper bearing shaft (16); The end of the upper bearing beam (7) is integrally arranged with the first upper bushing shaft (16); The cross-section of the extended ends of the first upper bushing shaft (16) and the first lower bushing shaft (17) after being combined is circular, and threads are provided on the extended ends, and nuts are threadedly connected to the two extended ends.

2. The helicopter load transfer and anti-sway structure according to claim 1, characterized in that: U-shaped grooves (20) are provided at both ends of the helicopter hatch, and both ends of the lower load-bearing beam (9) are placed in the U-shaped grooves (20).

3. The helicopter load transfer and anti-sway structure according to claim 2, characterized in that: A cover plate is provided on the top of the U-shaped groove (20), and the cover plate is fixed to the helicopter hatch.

4. The helicopter load transfer and anti-sway structure according to claim 1, characterized in that: Annular grooves are arranged at both ends of the helicopter hatch, and annular steps (10) are arranged at both ends of the lower bearing beam (9), and the annular steps (10) are located in the annular grooves.

5. The helicopter load transfer and anti-sway structure according to claim 1, characterized in that: The bearing member (4) is made of a metal rod, a steel wire rope or a fiber sling.

6. The helicopter load transfer and anti-sway structure according to claim 1, characterized in that: The bearing member (4) is a metal rod, and the metal rod is hinged to the upper bearing beam (7).

7. A helicopter, characterized in that: It comprises the helicopter load transfer and anti-sway structure as claimed in any one of claims 1 to 6, wherein the bearing member (4) in the helicopter load transfer mechanism and anti-sway structure is connected to the bearing seat (1) of the helicopter main reduction gearbox, and the bottom of the hanging plate (11) is connected to a cargo hook device (12).

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