Aircraft mechanical loading vehicle

Abstract

The utility model discloses an aircraft mechanical loading vehicle, which comprises a traction mechanism, a base, a pitching mechanism, a lifting swing mechanism, a lifting mechanism, a supporting device and a power device, the traction mechanism is connected with the base, the lifting swing mechanism is connected with the lifting mechanism through a mounting seat, the pitching mechanism is arranged on the lifting swing mechanism, and the supporting device is arranged on the lifting swing mechanism. The lifting mechanism and the power device are arranged on the base, the lifting mechanism is connected with the power device, and the supporting device is arranged on the pitching mechanism. According to the multi-diameter mechanical loading vehicle, a manual traction mode is adopted, the problem that a traction machine cannot pass through a narrow position is solved, and rapid transfer is achieved. According to the multi-diameter mechanical filling vehicle, the design that the hydraulic system and the shear type lifting mechanism are combined is adopted, the problems that a filling vehicle is high in failure rate and poor in maintainability in a severe environment are solved, cost is reduced, and economical efficiency is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of loading vehicles, and particularly relates to a mechanical loading vehicle for aircrafts. Background Art

[0002] At present, the loading of aircrafts mostly adopts the manual method. Due to the wide variety of aircraft models and different types of aircrafts to be mounted, general loading vehicles cannot meet the mounting requirements of multiple types of aircrafts, and it is very easy to collide between the aircraft and the landing gear. In addition, the working environment of the loading vehicle is harsh, and its safety and reliability cannot be guaranteed. The loading vehicle is the main equipment for aircraft transportation and mounting, and its mounting efficiency and safety are related to the deployment efficiency. In the specific use process, there are the following problems: First, the working environment on the training ground and in the wild is harsh, and the failure rate of the loading vehicle is high; Second, it is impossible to quickly and efficiently mount the aircraft during use; Third, there are few directions for attitude adjustment; Fourth, the loading vehicle cannot transport and mount aircrafts with various diameters.

[0003] The patent document with the publication number CN217294927U discloses a launch rack for facilitating the loading of on-vehicle unmanned aerial vehicles. The patent includes a bottom plate assembly, a lifting assembly, and a launching assembly; two symmetrical lifting assemblies are fixedly arranged on the top of the bottom plate assembly; the launching assembly is clamped and arranged on the top of the lifting assembly. However, the structures of the lifting assembly and the supporting device of this patent are different from those of the present application, and the present application controls the lifting of the supporting device through hydraulic pressure.

[0004] The patent document with the publication number CN108216682A discloses a six-degree-of-freedom portable universal attitude-adjusting docking cart for unmanned aerial vehicle wings and V-shaped tails, including: a hydraulic lifting vehicle, a rhombic tilting mechanism assembly, a hinge support, a tilting support plate, a worm gear and worm elevator, an elevator transmission connecting rod, a vertical and horizontal support plate assembly, a wing support plate, a high-density sponge, a universal ball head assembly, a support frame, a first handwheel assembly, and a plurality of universal casters. Although this patent discloses a structure similar to the lifting mechanism of the present application, it does not disclose the relevant structures of the supporting device and the power device, and cannot be used to load the entire aircraft. Content of the Utility Model

[0005] To solve the above technical problems, the utility model provides a mechanical loading vehicle for aircrafts.

[0006] The utility model is realized through the following technical solutions.

[0007] A mechanical loading vehicle for an aircraft provided by the utility model includes a traction mechanism, a base, a pitching mechanism, a lifting and slewing mechanism, a lifting mechanism, a supporting device and a power device. The traction mechanism is connected to the base. The lifting and slewing mechanism is connected to the lifting mechanism through a mounting seat. The pitching mechanism is arranged on the lifting and slewing mechanism. The lifting mechanism and the power device are arranged on the base. The lifting mechanism is connected to the power device. The supporting device is arranged on the pitching mechanism.

[0008] Preferably, the traction mechanism includes a connecting rod, a handle and a hinge part. One end of the connecting rod is connected to the handle, and the other end of the connecting rod is connected to the hinge part. The base includes a connecting part, a supporting part and wheels. One end of the connecting part is hinged to the hinge part, and the other end of the connecting part is connected to the supporting part. The wheels are rotatably connected to the connecting part.

[0009] Preferably, the pitching mechanism includes a pitching support disc, a pitching knob, a pitching scale disc, a worm gear and a worm. The pitching support disc is connected to the pitching scale disc. One end of the pitching knob is connected to the worm. The worm gear is arranged on the pitching scale disc. The worm is arranged on the support disc, and the worm meshes with the worm gear.

[0010] Preferably, the supporting device includes a bracket fixing mechanism and a support frame. The bracket fixing mechanism is arranged on the support frame, and the support frame is connected to the pitching mechanism.

[0011] Preferably, the bracket fixing mechanism includes an aircraft clamp, a chute, a limit bolt and a fixing bolt. The aircraft clamp is arranged in the chute. The aircraft clamp is fixedly connected to the chute through the fixing bolt. The chute is connected to the support frame. The limit bolt is arranged on one side of the opening of the chute.

[0012] Preferably, rollers are rotatably connected to the top of the aircraft clamp. Limit columns are arranged on both sides of the chute. The height of the top of the rollers is greater than the height of the top of the limit columns.

[0013] Preferably, the lifting and slewing mechanism includes a slewing mounting disc, a disc bearing and a slewing support disc. The slewing mounting disc is connected to the mounting seat. The disc bearing is arranged on the slewing mounting disc. The slewing support disc is arranged on the slewing mounting disc. The slewing support disc is connected to the supporting device.

[0014] Preferably, a slewing limit pin is arranged on the slewing mounting disc. An outer ring is arranged on the disc bearing. A limit groove is arranged on the outer ring. The slewing limit pin penetrates through the outer ring through the limit groove.

[0015] Preferably, the power device includes an oil tank, a manual pump and an oil cylinder. The oil tank is connected to the manual pump through a pipeline. The manual pump is connected to the oil cylinder through an oil circuit. A manual pump handle is arranged on the manual pump.

[0016] Preferably, a one-way throttle valve and a stop valve are arranged on the oil path.

[0017] The beneficial effects of the present utility model are as follows:

[0018] 1. A multi-diameter mechanical loading vehicle proposed by the patent of the present utility model adopts the method of manual traction, overcomes the problem that traction machinery cannot pass through narrow positions, and realizes rapid transfer.

[0019] 2. A multi-diameter mechanical loading vehicle proposed by the patent of the present utility model adopts the design of combining a hydraulic system with a scissor lifting mechanism, solves the problems of high failure rate and poor maintainability of the loading vehicle in harsh environments, and reduces costs and improves economy.

[0020] 3. A multi-diameter mechanical loading vehicle proposed by the patent of the present utility model realizes multi-pose and direction adjustment of the loading vehicle through a slewing mechanism and a pitching mechanism, and improves the hanging efficiency.

[0021] 4. A multi-diameter mechanical loading vehicle proposed by the patent of the present utility model adopts a multi-diameter aircraft bracket fixing mechanism, effectively solves the problem of single loading of the loading vehicle, and improves the transportation and loading efficiency.

[0022] 5. The present utility model realizes the lifting of the loading vehicle by controlling the opening and closing of the one-way throttle valve and the manual stop valve and the pressing of the manual pump. The structure is simple, can be used in harsh and complex environments, reduces the failure rate and improves the maintainability. Description of the Drawings

[0023] Figure 1 is the structural schematic diagram of the present utility model;

[0024] Figure 2 is the structural schematic diagram of the lifting and slewing mechanism of the present utility model;

[0025] Figure 3 is the structural schematic diagram of the pitching mechanism of the present utility model;

[0026] Figure 4 is the structural schematic diagram of the bracket fixing mechanism of the present utility model;

[0027] In the figure: 1 - traction mechanism, 101 - connecting rod, 102 - handle, 103 - hinge part, 2 - base, 201 - connecting part, 202 - supporting part, 203 - wheel, 3 - bracket fixing mechanism, 301 - aircraft clamp, 302 - chute, 303 - limit bolt, 304 - fixing bolt, 305 - roller, 306 - opening, 307 - limit post, 4 - support frame, 5 - pitching mechanism, 501 - support disc, 502 - pitching knob, 503 - pitching scale, 504 - worm gear, 505 - worm, 6 - lifting and slewing mechanism, 601 - slewing mounting disc, 602 - disc bearing, 603 - slewing limit pin, 604 - slewing support disc, 605 - outer ring, 606 - limit groove, 7 - mounting seat, 8 - fuel tank, 9 - manual pump handle, 10 - manual pump, 11 - one-way throttle valve, 12 - oil circuit, 13 - manual stop valve, 14 - lifting mechanism, 15 - oil cylinder. Detailed implementation mode

[0028] The technical solution of the present invention will be further described below, but the scope of protection is not limited thereto.

[0029] Embodiment:

[0030] As Figures 1 to 4 shown, a mechanical loading vehicle for aircraft includes a traction mechanism 1, a base 2, a pitching mechanism 5, a lifting and slewing mechanism 6, a lifting mechanism 14, a supporting device and a power device. The traction mechanism 1 is connected to the base 2. The lifting and slewing mechanism 6 is connected to the lifting mechanism 14 through a mounting seat 7. The pitching mechanism 5 is arranged on the lifting and slewing mechanism 6. The lifting mechanism 14 and the power device are arranged on the base 2. The lifting mechanism 14 is connected to the power device. The supporting device is arranged on the pitching mechanism 5.

[0031] The traction mechanism 1 includes a connecting rod 101, a handle 102 and a hinge part 103. One end of the connecting rod 101 is connected to the handle 102, and the other end of the connecting rod 101 is connected to the hinge part 103. The base 2 includes a connecting part 201, a supporting part 202 and a wheel 203. One end of the connecting part 201 is hinged to the hinge part 103, the other end of the connecting part 201 is connected to the supporting part 202, and the wheel 203 is rotatably connected to the connecting part 201. The traction mechanism 1 enables the loading vehicle to be manually towed.

[0032] The pitching mechanism 5 includes a pitching support disc 501, a pitching knob 502, a pitching scale 503, a worm gear 504 and a worm 505. The pitching support disc 501 is connected to the pitching scale 503. One end of the pitching knob 502 is connected to the worm 505. The worm gear 504 is arranged on the pitching scale 503. The worm 505 is arranged on the support disc 501, and the worm 505 meshes with the worm gear 504.

[0033] The support device includes a bracket fixing mechanism 3 and a support frame 4, which are used for supporting and fixing aircraft with multiple different diameters. The bracket fixing mechanism 3 is arranged on the support frame 4, and the support frame 4 is connected to the pitching mechanism 5.

[0034] The bracket fixing mechanism 3 includes a dovetail-shaped aircraft clamp 301, a dovetail chute 302, a limit bolt 303, and multi-diameter fixing bolts 304. The aircraft clamp 301 is arranged in the chute 302, and the aircraft clamp 301 is fixedly connected to the chute 302 through the fixing bolts 304. The chute 302 is connected to the support frame 4, and the limit bolt 303 is arranged on one side of the opening 306 of the chute 302. The dovetail-shaped aircraft clamp 301 is realized to overturn when the aircraft clamp moves and supports, and the support and fixation of aircraft with different diameters are realized through the multi-diameter fixing bolts 304 at different positions.

[0035] The top of the aircraft clamp 301 is rotatably connected with a roller 305. The roller 305 is made of rubber, which can provide soft support for the aircraft, protect the aircraft, and can roll to facilitate the loading of the aircraft. Limit posts 307 are arranged on both sides of the chute 302, and the height of the top of the roller 305 is greater than the height of the top of the limit posts 307 to avoid affecting the takeoff of the aircraft.

[0036] The lifting and slewing mechanism 6 can rotate. The lifting and slewing mechanism 6 includes a slewing mounting disc 601, a disc bearing 602, and a slewing support disc 604. The slewing mounting disc 601 is connected to the mounting seat 7, the disc bearing 602 is arranged on the slewing mounting disc 601, the slewing support disc 604 is arranged on the slewing mounting disc 601, and the slewing support disc 604 is connected to the support frame 4 of the support device.

[0037] A slewing limit pin 603 is arranged on the slewing mounting disc 601, an outer ring 605 is arranged on the disc bearing 602, a limit groove 606 is arranged on the outer ring 605, and the slewing limit pin 603 passes through the outer ring 605 through the limit groove 606. The slewing limit pin 603 limits the slewing angle of the lifting and slewing mechanism 6.

[0038] The power device includes a fuel tank 8, a manual pump 10, and an oil cylinder 15. The fuel tank 8 is connected to the manual pump 10 through a pipeline, the manual pump 10 is connected to the oil cylinder 15 through an oil circuit 12, and a manual pump handle 9 is arranged on the manual pump 10. A one-way throttle valve 11 and a manual stop valve 13 are arranged on the oil circuit 12. The power device is used to provide the lifting function of the lifting mechanism 14 of the loading vehicle.

[0039] A usage method of an aircraft loading vehicle includes the following steps:

[0040] S1: This vehicle is a loading truck that transports the aircraft from the storage warehouse to the designated location. According to the diameter of the transported aircraft, adjust the multi-diameter aircraft bracket fixing mechanism 3, remove the multi-diameter fixing bolts 304 on the multi-diameter aircraft bracket fixing mechanism 3, move the aircraft clamp 301 to the appropriate position, insert the multi-diameter fixing bolts 304 and tighten them, and load the aircraft onto the vehicle by hoisting, ensuring that the rollers 305 are at their support points upwards;

[0041] S2: Move the vehicle to below the designated position, adjust the lifting height through the hydraulic system and the lifting mechanism 14, and rotate the handle of the stop valve 13 counterclockwise to open the stop valve; rotate the handle of the unloading valve of the hydraulic pump 10 clockwise to close the unloading valve; repeatedly press down the handle 9 of the hydraulic pump to lift the aircraft to the required height; rotate the manual stop valve 13 clockwise to close the stop valve 13 and keep the vehicle at the required height; adjust the attitude of the vehicle as needed, manually adjust the rotation and pitch knob 502, and observe the pitch scale 503 to keep the vertical axis of the aircraft parallel to the installation device; through the rotary mounting plate 601 in the rotary mechanism 6, the disc bearing 602, the rotary limit pin 603 limits the rotation angle, and the rotary support plate 604 supports the pitching mechanism to achieve the rotary function and keep the horizontal axis of the vehicle parallel to the installation device; move the vehicle body forward and backward as needed to basically align the suspension of the aircraft with the corresponding position of the loading device at the same time for loading;

[0042] S3: After loading is completed, rotate the handle of the stop valve 13 to open the stop valve, rotate the handle of the unloading valve of the hydraulic pump 10 to open the unloading valve, adjust the support frame 4 of the multi-diameter aircraft bracket fixing mechanism of the vehicle to the original height, and finally tow the vehicle away from the loading position.

Claims

1. A mechanical loading vehicle for an aircraft, characterized in that: It includes a traction mechanism (1), a base (2), a pitching mechanism (5), a lifting and slewing mechanism (6), a lifting mechanism (14), a supporting device and a power device. The traction mechanism (1) is connected to the base (2). The lifting and slewing mechanism (6) is connected to the lifting mechanism (14) through a mounting seat (7). The pitching mechanism (5) is arranged on the lifting and slewing mechanism (6). The lifting mechanism (14) and the power device are arranged on the base (2). The lifting mechanism (14) is connected to the power device. The supporting device is arranged on the pitching mechanism (5).

2. The mechanical loading vehicle for an aircraft according to claim 1, wherein: The traction mechanism (1) includes a connecting rod (101), a handle (102) and a hinge part (103). One end of the connecting rod (101) is connected to the handle (102), and the other end of the connecting rod (101) is connected to the hinge part (103). The base (2) includes a connecting part (201), a supporting part (202) and wheels (203). One end of the connecting part (201) is hinged to the hinge part (103), and the other end of the connecting part (201) is connected to the supporting part (202). The wheels (203) are rotatably connected to the connecting part (201).

3. The mechanical loading vehicle for an aircraft according to claim 1, wherein: The pitching mechanism (5) includes a pitching support disk (501), a pitching knob (502), a pitching scale disk (503), a worm gear (504) and a worm (505). The pitching support disk (501) is connected to the pitching scale disk (503). One end of the pitching knob (502) is connected to the worm (505). The worm gear (504) is arranged on the pitching scale disk (503). The worm (505) is arranged on the support disk (501), and the worm (505) meshes with the worm gear (504).

4. The mechanical loading vehicle for an aircraft according to claim 1, characterized in that: The supporting device includes a bracket fixing mechanism (3) and a support frame (4). The bracket fixing mechanism (3) is arranged on the support frame (4), and the support frame (4) is connected to the pitching mechanism (5).

5. The mechanical loading vehicle for an aircraft as claimed in claim 4, wherein: The bracket fixing mechanism (3) includes an aircraft clamp (301), a chute (302), a limit bolt (303) and a fixing bolt (304). The aircraft clamp (301) is arranged in the chute (302), and the aircraft clamp (301) is fixedly connected to the chute (302) through the fixing bolt (304). The chute (302) is connected to the support frame (4). The limit bolt (303) is arranged on one side of the opening (306) of the chute (302).

6. The mechanical loading vehicle for an aircraft according to claim 5, wherein: The top of the aircraft clamp (301) is rotatably connected to a roller (305). Limit posts (307) are arranged on both sides of the chute (302), and the height of the top of the roller (305) is greater than the height of the top of the limit posts (307).

7. The mechanical loading vehicle for an aircraft as claimed in claim 1, wherein: The lifting and slewing mechanism (6) includes a slewing mounting disk (601), a disk bearing (602) and a slewing support disk (604). The slewing mounting disk (601) is connected to the mounting seat (7). The disk bearing (602) is arranged on the slewing mounting disk (601). The slewing support disk (604) is arranged on the slewing mounting disk (601), and the slewing support disk (604) is connected to the supporting device.

8. The mechanical loading vehicle for an aircraft according to claim 7, characterized in that: A rotary limit pin (603) is provided on the rotary mounting disc (601), an outer ring (605) is provided on the disc bearing (602), a limit groove (606) is provided on the outer ring (605), and the rotary limit pin (603) penetrates through the outer ring (605) through the limit groove (606).

9. The mechanical loading vehicle for an aircraft according to claim 1, wherein: The power device includes an oil tank (8), a manual pump (10) and an oil cylinder (15). The oil tank (8) is connected to the manual pump (10) through a pipeline. The manual pump (10) is connected to the oil cylinder (15) through an oil circuit (12), and a manual pump handle (9) is provided on the manual pump (10).

10. A mechanical loading vehicle for an aircraft as described in claim 9, characterized in that: A one-way throttle valve (11) and a stop valve (13) are provided on the oil circuit (12).

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