Airplane traction test platform based on hydraulic power

Abstract

An aircraft traction test platform based on hydraulic power comprises a track system, a hydraulic power system, a mobile platform and a lifting frame. The track system is positioned below the whole device; the hydraulic cylinder power system comprises two parts, one part is a traction hydraulic system arranged in front of the moving platform, and the other part is a lifting hydraulic system arranged on the two sides of the lifting frame; a wheel holding mechanism formed by the moving platform and the lifting frame is located above the rail system. The detachable integrated frame of the lifting frame is taken down by unscrewing the nuts, the airplane wheel is jacked to the front supporting table, then the detachable integrated frame is installed back, the nuts are screwed, and the airplane wheel can be held tightly; the lifting frame is jacked up through the lifting hydraulic systems on the two sides, and airplane wheels can be lifted up. The traction hydraulic system pulls the mobile platform to walk, so that the airplane can be dragged to walk. The method can be used for start-stop dynamics analysis and vibration characteristic research of the airplane in a traction state.

Description

Technical Field

[0001] The invention discloses an aircraft towing test platform based on hydraulic power, belonging to the technical field of special vehicles for airports, and specifically is an aircraft towing test platform with the function of lifting and hoisting aircraft wheels. Background Art

[0002] An aircraft tractor is a support device used to tow aircraft on the airport ground. It is divided into a tow tractor with a rod and a tow tractor without a rod according to its structure. One of the key points to judge the quality of an aircraft tractor is the towing process of the aircraft tractor and the aircraft. Therefore, it is urgent to design a convenient, efficient and fast device for towing aircraft.

[0003] Existing tractors can only push and tow aircraft over short distances. After the relevant work is completed, the aircraft will start its own engine to move. This not only causes noise pollution at the airport, but also shortens the effective service life of the aircraft engine and increases fuel consumption to a certain extent, thus increasing the cost of aircraft operation. If existing tractors are used for towing, the slow towing speed will affect the normal take-off and landing of flights, and the fast towing technology is not mature. One of the difficulties is the dynamic problem at the coupling between the aircraft and the tractor. Summary of the invention

[0004] The present invention provides an aircraft towing test platform based on hydraulic power to solve the problems raised in the above background technology.

[0005] To achieve the above purpose, the present invention provides the following solutions:

[0006] An aircraft traction test platform based on hydraulic power includes a track system, a hydraulic power system, a mobile platform and a lifting frame. The track system is located below the entire device; the hydraulic cylinder power system includes two parts, one is a traction hydraulic system placed in front of the mobile platform, and the other is a lifting hydraulic system placed on both sides of the lifting frame; the wheel holding mechanism composed of the mobile platform and the lifting frame is located above the track system.

[0007] The track system solution of the present invention patent: the track system includes: pad, TG-60 rail clamp, track, TG-60 fish plate, traction cylinder support. Figure 1 As shown, the rails are connected through the TG-60 fishplate, and the connected rails are fixed on the pad by the TG-60 rail clamp.

[0008] The hydraulic power system solution of the present invention: the traction hydraulic cylinder and the lifting hydraulic cylinder both include: a hydraulic cylinder and a hydraulic rod. Figure 1 , Figure 2 and Figure 3As shown, the top of the traction hydraulic rod is connected to the mobile platform and the spoke-type sensor between the two, and the traction hydraulic cylinder is connected to the front hydraulic circuit through the traction rod support located on the track. The top of the lifting hydraulic rod is connected to the lifting frame on the mobile platform through the trunnion, and the lifting hydraulic cylinder is connected to the mobile platform base through the I-beam fixed on the base and the trunnion fixed on the I-beam.

[0009] The mobile platform solution of the present invention patent: the mobile platform includes: a "C"-shaped frame and track wheels. Figure 2 and Figure 3 As shown, the "C"-shaped frame is composed of several I-beams, and both sides are composed of two I-beams plus two I-beams to form reinforcement ribs. Two track wheels are connected between the two I-beams, and the other single side is composed of two I-beams and a trunnion fixed by bolts under one of the I-beams. The trunnion under the I-beam is connected to the I-beam hole under the lifting mechanism through a pin.

[0010] The lifting frame solution of the present invention patent: the lifting frame is composed of a frame composed of a plurality of I-beams and square steels, two rollers and two support platforms with rollers. Figure 4 As shown, the front upper rollers and the front support platform with rollers are connected to the I-beam frame by bolts to form a fixed frame, and the door frame composed of I-beams and square steels and the rear upper rollers and the rear support platform with rollers together form a detachable integrated frame, which is connected to the front fixed frame by bolts.

[0011] Compared with the prior art, the beneficial effects of the present invention are: by designing a lifting frame, the front wheel of the aircraft can be quickly clamped and fixed, that is, the front wheel of the aircraft is clamped between the roller and the support platform with the roller; by designing a hydraulic cylinder power system, the lifting hydraulic cylinder can be lifted a certain distance after the lifting device clamps the front wheel of the aircraft, and after the aircraft wheel is lifted, the traction hydraulic cylinder can also drive the mobile platform to move forward. The present invention can be used for the start-stop dynamics analysis and vibration characteristics research of the aircraft in the traction state. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is an overall schematic diagram of the present invention.

[0013] Figure 2 It is a schematic diagram of the wheel holding mechanism of the present invention.

[0014] Figure 3 It is a schematic diagram of the mobile platform and lifting hydraulic system of the present invention.

[0015] Figure 4 It is a schematic diagram of the lifting frame of the present invention.

[0016] Among them: 1-traction hydraulic cylinder, 2-traction cylinder support, 3-traction hydraulic rod, 4-track, 5-pad, 6-TG-60 fishtail plate, 7-TG-60 rail clamp, 8-"C" type frame, 9-lifting frame, 10, 11, 12, 13-track wheel, 14-spoke sensor, 15-long pin, 16, 18-lifting hydraulic cylinder, 17, 19-lifting hydraulic rod, 20, 21-lifting cylinder upper ear shaft, 22, 23-ear shaft, 24, 26-roller, 25, 27-support platform with roller, 28, 29-ear shaft, 30, 31, 32, 33, 34-I-beam, 35-lifting cylinder lower ear shaft. DETAILED DESCRIPTION

[0017] The technical solution of the present invention is further described in detail below in conjunction with the accompanying drawings.

[0018] The patent of this invention is an aircraft traction test platform based on hydraulic power, the structure is as follows Figure 1-Figure 4 As shown, it includes: track system, hydraulic power system, mobile platform and lifting frame.

[0019] refer to Figure 1 A hydraulically powered aircraft towing test platform is used to realize the walking of a towing mobile platform and the lifting and lowering of a lifting frame. The track system comprises a track (4), a pad (5), a TG-60 fishtail plate (6), and a TG-60 track clamp (7). The track (4) composed of a plurality of I-beams and a TG-60 fishtail plate (6) is fixed to the pad (5) through the TG-60 track clamp (7) and bolts, and the walking of the mobile platform is realized through the track system formed by the I-beams and the TG-60 fishtail plate (6).

[0020] refer to Figure 1 and Figure 3 The hydraulic power system comprises a traction hydraulic cylinder (1), a traction hydraulic rod (2), a lifting hydraulic cylinder (16, 18), and a lifting hydraulic rod (17, 19). The traction hydraulic cylinder (1) is placed on a traction cylinder support (2) fixed on a pad (5). The top ear shaft of the traction hydraulic rod (3) is connected to the ear shaft connected to a spoke-type sensor (14) fixed on a "C"-shaped frame (8) through a long pin (15), so that the traction mobile platform can be moved. The lifting hydraulic system is placed on both sides of the lifting frame (9), one side of which is an I-beam (34) bolted to the bottom of the "C"-shaped frame (8), and the lower ear shaft of the lifting hydraulic cylinder (16) is connected to the lower ear shaft (35) of the lifting hydraulic cylinder fixed on the I-beam (34) through a pin. The top ear shaft (20) of the lifting hydraulic rod (17) is connected to the ear shaft (22) of the lifting frame (9), and the connection method of the other side is the same. Under the joint action of the lifting hydraulic cylinders on both sides, the lifting frame (9) can be lifted and lowered, thereby realizing the lifting and lowering of the aircraft wheels.

[0021] refer to Figure 1 and Figure 2 The mobile platform comprises a "C"-shaped frame (8) and track wheels (10, 11, 12, 13).

[0022] The "C"-shaped frame (8) is composed of a plurality of I-beams, and both sides are composed of two I-beams plus two I-beams (30, 31) or I-beams (32, 33) to form reinforcing ribs, and two track wheels (10, 12) or track wheels (11, 13) are connected between the two I-beams, and the other single side is composed of two I-beams and a trunnion (28, 29) fixed by bolts under one of the I-beams. The trunnion (28, 29) is connected to the lower I-beam of the lifting frame (9) by a pin.

[0023] refer to Figure 4 The lifting frame (9) is composed of a frame composed of a plurality of I-beams and square steels, two rollers (24, 26) and two supporting platforms with rollers (25, 27), wherein the front roller (24) and the supporting platform with rollers (25) are connected to the I-beam frame by bolts to form a fixed frame, and a detachable integrated frame composed of a door frame composed of I-beams and square steels and the rear rollers (26) and the supporting platform with rollers (27) is connected to the front fixed frame by bolts.

[0024] The specific implementation mode of the present invention is as follows: the detachable integrated frame of the lifting frame (9) is removed by unscrewing the nut, the aircraft wheel is pushed to the front support platform, and then the detachable integrated frame is reinstalled and the nut is tightened, so that the aircraft wheel can be held tightly; the lifting frame (9) is lifted by the lifting hydraulic system, so that the aircraft wheel can be lifted; finally, the moving platform is towed by the traction hydraulic system to move, so that the aircraft can be towed to move.

Claims

1. An aircraft traction test platform based on hydraulic power, characterized in that It includes a track system, a hydraulic power system and a mobile platform. The track system is located below the entire device; the hydraulic cylinder power system includes two parts, one is a traction hydraulic system located in front of the mobile platform, and the other is a lifting hydraulic system located on both sides of the lifting frame; the wheel holding mechanism composed of the mobile platform and the lifting frame is located above the track system.

2. The hydraulic powered aircraft towing test platform according to claim 1, characterized in that: The lifting hydraulic system is placed on both sides of the lifting frame (9).

3. The hydraulic powered aircraft towing test platform according to claim 1, characterized in that: The "C"-shaped frame (8) is composed of a plurality of I-beams, and both sides are composed of two I-beams plus two I-beams (30, 31) or I-beams (32, 33) to form reinforcing ribs, and two track wheels (10, 12) or track wheels (11, 13) are connected between the two I-beams, and the other single side is composed of two I-beams and a trunnion (28, 29) bolted to the bottom of one of the I-beams. The trunnion (28, 29) is connected to the lower I-beam of the lifting frame (9) by a pin.

4. The hydraulic powered aircraft towing test platform according to claim 1, characterized in that: The lifting frame (9) is composed of a frame composed of a plurality of I-beams and square steels, two rollers (24, 26) and two support platforms with rollers (25, 27), wherein the front roller (24) and the support platform with rollers (25) are fixedly connected to the I-beam frame by bolts to form a fixed frame, and a detachable integrated frame composed of a door frame composed of I-beams and square steels and the rear rollers (26) and the support platform with rollers (27) is connected to the front fixed frame by bolts.

5. The hydraulic powered aircraft towing test platform according to claim 1, characterized in that: The detachable integrated frame of the lifting frame (9) is removed by unscrewing the nut, the aircraft wheel is pushed to the front support platform, and then the detachable integrated frame is reinstalled and the nut is tightened, so that the aircraft wheel can be held tightly.

6. The hydraulic powered aircraft towing test platform according to claim 1, characterized in that: The lifting frame (9) is lifted by the lifting hydraulic system to lift the wheels of the aircraft.

7. The hydraulic powered aircraft towing test platform according to claim 1, characterized in that: The aircraft can be towed by using a traction hydraulic system to tow the mobile platform.

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