JPH0357572Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to an aircraft engine cargo handling device for carrying heavy cargo, particularly an aircraft engine, into and out of the aircraft.

[Conventional technology]

Conventionally, when an aircraft engine breaks down in a remote location, if there is no local repair shop or if the failure is catastrophic and cannot be repaired, it is necessary to transport a repaired engine to the location. At that time, cargo handling equipment is required to carry the engine into and out of the aircraft, but if this equipment is not available on site, this equipment is transported along with the engine by aircraft. For this reason, it is necessary to make the cargo handling device as compact as possible so that it can be housed inside the machine, and various devices have been proposed in the past.

[The problem that the idea attempts to solve]

However, conventional cargo handling devices have a problem in that disassembly and assembly operations are extremely troublesome and require a large number of man-hours. Furthermore, when the cargo handling device is placed on the floor inside the aircraft, there is a problem in that the load is concentrated on a local part of the floor.

This invention solves these problems by making each member that supports the elevating table on which the engine is mounted expandable and retractable, and also prevents the load of the cargo handling equipment from being concentrated on a part of the aircraft floor. The purpose is to provide cargo handling equipment for aircraft engines.

[Means to solve the problem]

To achieve this objective, the aircraft engine cargo handling device of the present invention includes a horizontal boom that is extendable and retractable in the horizontal direction, a front pillar and a rear pillar that are foldably attached to both ends of the horizontal boom, and that are supported by the horizontal boom. A device body including a lifting table on which an aircraft engine is mounted, and a plurality of rolling members that are placed on a floor surface inside the aircraft body and support the device body at a predetermined height above the aircraft floor surface. The storage base is movably supported.

[Effect]

According to the above configuration, the cargo handling device for an aircraft engine can be easily installed inside the aircraft by reducing the horizontal boom, front pillar, and rear pillar.
Moreover, the load of the apparatus main body is distributed and applied to the machine floor surface by rolling members located at a predetermined height above the floor surface, thereby preventing stress concentration on the floor surface.

〔Example〕

Hereinafter, the present invention will be explained based on embodiments shown in the drawings.

Fig. 1 is a front view showing a state in which the cargo handling equipment for an aircraft engine is stored and attached to a storage base inside the aircraft, Fig. 2 is a plan view taken in the direction of - arrow in Fig. Fig. 4 is a front view showing the assembled state of the cargo handling device for an aircraft engine; Fig. 5 is a plan view taken from - arrow in Fig. 4;
The drawings are a side view taken in the direction of the - arrow in FIG. 4, and FIG. 19 is a perspective view of the cargo handling device for an aircraft engine at the time of assembly, in which the aircraft engine is mounted.

A cargo handling device for an aircraft engine 1, which is an example of heavy cargo according to the present invention, is a so-called engine loader 2, which includes two horizontal booms 3 arranged in parallel, and two booms fixed perpendicularly to both ends of the horizontal booms 3. telescopic booms 4A, 4B, and two front pillars 5 foldably attached to both ends of the telescopic boom 4A.
, two rear pillars 6 foldably installed at both ends of the telescopic boom 4B, a lifting mechanism 8 installed on the horizontal boom 3, an lifting table 10 that is raised and lowered by the lifting mechanism 8, and a storage base 11. There is.

The horizontal boom 3 includes a fixed part 3a and a movable part, for example, a two-stage movable boom 3b, which is slidably built into one end of the fixed part 3a.
is expanded and contracted by the operation of a hydraulic cylinder 12 (hereinafter, unless otherwise specified, the actuator will be referred to as a hydraulic cylinder), which is an example of an actuator built into the fixed part 3a. The two telescoping booms 4A, 4B are formed into an L-shape, with fixed parts 4a, 4b fixed to both ends of the fixed part 3a of the two horizontal booms 3, and slidably built into both ends of the fixed parts 4a, 4b. 2 each
It consists of movable parts 4d, 4e and 4f, 4g, and these movable parts expand and contract by the operation of hydraulic cylinders 13A, 13B built in fixed parts 4a, 4b.

The front pillar 5 includes a first joint 5A hinged to the lower ends of the movable parts 4d and 4e of the telescopic boom 4A by a hinge mechanism 15A, and a second joint 5A hinged to the first joint 5A by a hinge mechanism 15B. It consists of part 5B. The hinge mechanism 15A is connected to a hydraulic cylinder 16A attached to the movable parts 4d and 4e of the telescopic boom 4A, and the hinge mechanism 15B is connected to a hydraulic cylinder 16B attached to the first joint 5A. Further, a jack 20 for the front pillar 5 operated by a hydraulic cylinder 18 is attached to the lower part of the second joint portion 5B, and a wheel (hereinafter referred to as a ground contact member) is attached to a wheel, which is an example of a ground contact member. ) 21 is rotatably supported.

In FIG. 6, the right rear pillar 6 has a hinge mechanism 22A at the lower end of the movable part 4f of the telescopic boom 4B.
A first joint 6A is hinged to the lower end of the first joint 6A, a second joint 6B is hinged to the lower end of the second joint 6A by a hinge mechanism 22D, and a second joint 6B is hinged to the lower end of the second joint 6B by a hinge mechanism 22D. The attached third joint 6
It consists of D. The hinge mechanism 22A is attached to a hydraulic cylinder 23A attached to the movable portion 4f, the hinge mechanism 22B is attached to a hydraulic cylinder 23B attached to the first joint portion 6A, and the hinge mechanism 22D is attached to a hydraulic cylinder attached to the second joint portion 6B. 23D, respectively. Further, a jack 26A for the rear pillar 6 that is operated by a hydraulic cylinder 25A is attached to the lower part of the third joint 6D, and a wheel 28 is rotatably supported at the tip of the jack 26A.

In FIG. 6, the left rear pillar 6 has a hinge mechanism 22 at the lower end of the movable part 4g of the telescopic boom 4B.
It consists of a first joint 6E hinged by E, and a second joint 6F hinged to the lower end of the first joint 6E by a hinge mechanism 22F. The hinge mechanism 22E is connected to a hydraulic cylinder 23E attached to the movable part 4g, and the hinge mechanism 22F is connected to a hydraulic cylinder 23F attached to the first joint part 6E. Further, a jack 26B operated by a hydraulic cylinder 25B is attached to the lower part of the second joint 6F, and the tip of the jack 26B has a
A wheel 28 is rotatably supported. FIG. 7 shows the folded state of the rear pillar 6 when the engine loader 2 is stored.

The lifting mechanism 8 includes a winding drum 32, an electric winch 33 for rotating the winding drum 32, a plurality of pulleys 34, for example four, and four hydraulic cylinders 35. The winding drum 32 is a mounting base 3 fixed perpendicularly to the center of the fixed part 3a of the two horizontal booms 3.
6 and is rotatably supported on the flange portion 32.
Four divided portions 32b are formed by a.

The electric winch 33 is integrally connected to the winding drum 32, and the winding drum 32 is rotated by operating the electric winch 33.
The four pulleys 34 are connected to two telescopic booms 4A and 4B.
The pulleys are connected to the winding drum 32 via guide pulleys 38, which are fixed to the insides of the two telescopic booms 4A and 4B. Each division part 32 of
Two wires 40, each of which is an example of a winding member, are wound around b. 40 wires each
One of the cylinders is connected to each of the four hydraulic cylinders 35 (see FIG. 8).

As shown in FIG. 9, the elevating table 10 has a rectangular shape, and cutouts 10a are formed at its four corners to avoid contact with the front pillar 5 and rear pillar 6 during storage. A wire connecting beam 43 is lightly press-fitted into the notch 10a. The wire 40 is connected to the wire connecting beam 43.
It is designed so that two can be hung. On the upper surface of the lifting table 10, a plurality of rollers 45 and a drive wheel 46 driven by an electric motor protrude from the upper surface and are rotatably supported, and on the lower surface,
A plurality of wheels 48 for ground running protrude from the lower surface and are rotatably supported, respectively.

Also, on the front and rear end surfaces of the lifting table 10, there are stoppers 50 for preventing the engine 1 from falling (see Fig. 4).
A plurality of side guide rollers 51, for example, three side guide rollers 51, for guiding the movement of the engine 1 are rotatably supported on both longitudinal end faces.

The storage base 11 is placed inside the fuselage 55 via a plate-shaped pallet 54, and as shown in FIG. and a mounting section 11b arranged in parallel with the mounting section 1.
On the upper surface of 1b, rollers 56, which are examples of a plurality of rolling members, protrude from the upper surface and are rotatably supported. Further, a pair of support jacks 58 are attached to the arm portion 11d formed perpendicularly to the front portion of the base portion 11a. The support jack 58 includes a horizontal boom cradle 61 that slides vertically inside the arm 11d by a hydraulic cylinder 60, and the upper part of the horizontal boom cradle 61 is
It can be connected to the tip of the movable part 3b of the horizontal boom 3 by a pin 62.

Next, the operation of the embodiment of the present invention will be explained.

FIG. 11 to FIG. 18 are schematic diagrams showing the operating procedure of the engine loader 2 of the present invention, and the procedure will be explained one by one below.

First, the engine loader 2 mounted on the fuselage 55 is inserted into the opening 65a of the side cargo door 65 of the fuselage 55.
We will explain the case of transporting it outside and assembling it.

() Move the engine loader 2 to the side cargo door 6
5 (see FIG. 11), and remove the connecting rope between the pallet 54 and the engine loader 2.

() Operate the hydraulic cylinder 12 of the horizontal boom 3 to extend the movable part 3b until the rear pillar 6 comes out to a predetermined position outside the fuselage 55. At this time, the lifting table 10 is moved by the rollers 56 of the storage base 11.
slide on top.

() Operate the hydraulic cylinder 13B of the telescopic boom 4B to extend the movable parts 4f and 4g to the maximum extent (see Fig. 6), and then operate the hydraulic cylinder 23 of the hinge mechanism 22 to extend each joint of the rear pillar 6. The wheel 28 is extended to ground the wheel 28 on the ground surface 66. (See Figure 12).

() Hydraulic cylinder 6 of the support jack 58 inserted into the storage base 11 inside the fuselage 55
0 and the hydraulic cylinder 25 of the jack 26 of the rear pillar 6 are operated to operate the support jack 58 of the storage base 11 and the jack 26 of the rear pillar 6.
is extended, and the elevating table 10 is raised and separated from the rollers 56 of the storage base 11.

() The movable part 3b of the horizontal boom 3 is further extended, and the engine loader 2 is transferred to a predetermined position outside the fuselage 55. (See Figure 13).

() Operate the hydraulic cylinder 13A of the telescopic boom 4A to extend the movable parts 4d and 4e to the maximum extent (see Fig. 5), and then operate the hydraulic cylinder 16 of the hinge mechanism 15 to extend the front pillar 5.
by extending each joint of the wheel 21 to the contact surface 66.
ground to. (See Figure 14).

() After removing the pin 62 and separating the movable part 3b of the horizontal boom 3 and the horizontal boom cradle 61 of the support jack 58, the hydraulic cylinder 12 is operated to reduce the movable part 3b to the minimum.

() Attach the opening prevention bar 68 between the front pillar 5 and rear pillar 6 by input.

() Operate the hydraulic cylinders 18 and 25 of the front pillar 5 and rear pillar 6 to
After raising 0,26, electric winch 3
3 to move the lifting table 10 to the ground surface 66.
Place it on.

() Elevate the wire connecting beam 43 to the table 1
Pull it all the way from 0 and clamp it.

() The elevating table 10 is raised by the electric winch 33, and the upper surface of the elevating table 10 is aligned with the machine floor 55a of the machine body 55.

Next, as shown in FIG. 15, a procedure for transferring the engine 1 placed on the pallet 54 in the fuselage 55 to the engine loader 2 that has been assembled will be described.

() Remove the storage base 11 forward and transport the engine 1 together with the pallet 54 to the vicinity of the side cargo door 65.

() The engine 1 and the pallet 54 are transferred onto the lifting table 10 using the drive wheels 46.

() Elevating table 1 by electric winch 33
0 is lowered, and the wheels 48 are brought into contact with the ground plane 66. (See Figure 16).

() Wire connection beam 4 of lifting table 10
Remove the wire 40 from 3 by input, and remove the pallet 64.
Instead, only the engine 1 is lifted up by the electric winch 33. (See Figure 17).

() After manually storing the wire and the connecting beam 43 in the lifting table 10, the lifting table 10 is pulled out by a towing vehicle, and the engine trailer 70 is inserted in its place.

() Lower the engine 1 using the electric winch 33 and mount it on the engine trailer 70.
(See Figure 18).

() The engine 1 mounted on the engine trailer 70 is transported to the site.

Next, a procedure for loading the engine 1 mounted on the engine trailer 70 into the fuselage 55 will be explained.

() The engine trailer 70 with the engine 1 installed enters the engine loader 2, the wire 40 is hung around the engine 1, and the lifting mechanism 8
Lift only engine 1.

() Pull out the empty engine trailer 70 and insert the elevating table 10 on which the empty shipping stand 72 is mounted in its place.

() Operate the electric winch 33 to lower the engine 1 and mount it on the shipping stand.

() Remove the wire 40 of the lifting mechanism 8 from the engine 1 and replace it with the wire connecting beam 43 of the lifting table 10.

() Operate the electric winch 33 to raise the elevating table 10 until the top surface matches the floor 55a of the aircraft body 55.

() The engine 1 is transported into the fuselage 55 using the lifting table 10 and the driving wheels of the aircraft floor 55a.

() The engine 1 is transported to a predetermined position within the fuselage 55 using the drive wheels.

Next, a procedure for storing the engine loader 2, which has been carried out of the fuselage 55 and assembled, into the fuselage 55 will be described.

() Storage base 11 stored in the fuselage 55
is transported to a predetermined position near the side cargo door 65 using drive wheels.

() The lifting table 10 is once lowered to the ground plane, and the wire connecting beam 43 is stored.

() Operate the electric winch 33 to raise the lifting table 10 until it reaches the top dead center position.

() Operate the jacks 20 and 26 of the front pillar 5 and rear pillar 6 to lower the horizontal boom 3 to a predetermined height position where it can be inserted into the fuselage 55.

() Remove the opening prevention bar 68 between the front pillar 5 and rear pillar 6 by inputting the input.

() Operate the hydraulic cylinder 12 to extend the movable part 3b of the horizontal boom 3 to the maximum extent, and fix its tip to the horizontal boom cradle 61 of the support jack 58 with the pin 62.

() The hydraulic cylinder 16 is operated to fold each joint of the front pillar 5, and then the hydraulic cylinder 13A is operated to retract the movable parts 4d and 4e of the telescopic boom 4A.

() Retract the movable part 3b of the horizontal boom 3 to a predetermined position where a part of the engine loader 2 enters the fuselage 55.

() Lower the support jack 58 and the jack 26 of the rear pillar 6, and lower the lifting table 10.
is placed on the roller 56 of the storage base 11.

() The hydraulic cylinder 23 is operated to fold each joint of the rear pillar 6, and then the hydraulic cylinder 13B is operated to fold the movable part 4 of the telescopic boom 4B.
Reduce f, 4g.

() The movable part 3b of the horizontal boom 3 is reduced to the minimum, and the engine loader 2 is placed on the storage base 11.
While sliding on the rollers 56 of the camera, the camera is placed in the storage position.

() Connect the engine loader 2 and the pallet 54 using a connecting rope.

In the above operating procedure, when the engine loader is stored, the device main body is supported by a plurality of rollers 56 located at a predetermined height above the surface of the machine body 55a, and therefore, the load of the device main body is generated on the plurality of rollers 56. The compressive stress applied to the machine floor 55a is distributed and applied to the machine floor 55a surface, and stress concentration on the machine floor 55a surface can be prevented. Furthermore, the plurality of rollers 56, which are the supporting surfaces of the apparatus main body, are located above the surface of the machine floor 55a, making it easy to carry in and take out the apparatus main body.

Sequence control is performed according to the operating procedures when assembling and storing the engine loader 2, and each step is completed by detecting the position, length, etc.
Proceed to the next step. engine loader 2
Taking assembly as an example, part of the sequence control is
Shown in Figure 0.

In addition, after the engine loader 2 is carried out from the fuselage 55 and assembled, the distance to the horizontal boom 3 is measured with a sensor (ultrasonic sensor or optical sensor) on the side cargo door 65, and the distance to the horizontal boom 3 is measured and the predetermined value is extended to the predetermined height. Front pillar 5, rear pillar 6 until
Activate the jacks 20 and 26. Subsequent adjustments (tilt, etc.) may be made manually.

Aircraft 55 during removal or loading of engine 1
In order to prevent contact between the side cargo door 65 and the horizontal boom 3 due to fluctuations in the height of the horizontal boom 3, the height is measured using the sensor mentioned above, and when the height reaches a certain critical value, the jack is automatically activated to follow the fluctuation. It has become a system to do this.

To control the posture of the lifting table 10, the lengths of the four wires 40 can be adjusted individually. This can be done by operating the hydraulic cylinder 35. Also, front pillar 5 and rear pillar 6
Although the opposing front pillars 5 and 6 move in opposite directions, only one of the front pillars 5 and 6 may move. It is also possible to apply the present invention to the handling of heavy cargo other than the engine 1.

〔effect〕

As mentioned above, according to the present invention, a horizontal boom,
Since the front pillar and the rear pillar can be expanded and contracted, the engine loader can be stored compactly within the fuselage, and there is no need for assembly or disassembly, making cargo handling work easier. Furthermore, since the device main body is supported by a plurality of rollers at a predetermined height above the machine floor surface, stress concentration on the machine floor surface can be prevented.

[Brief explanation of drawings]

Figure 1 is a front view of the engine loader (aircraft engine cargo handling device) when stored inside the aircraft;
The figure is a plan view taken in the direction indicated by the - arrow in FIG. 1, FIG. 3 is a plan view taken in the direction indicated by the - arrow shown in FIG.
Fig. 6 is a side view taken from the - arrow direction in Fig. 4, Fig. 7 is a schematic side view of the rear pillar when folded, and Fig. 8 shows a hydraulic cylinder for adjusting the wire length in the lifting mechanism. FIG. 9 is a perspective view showing the relationship with the wire; FIG. 9 is a plan view of the elevating table;
Figure 0 is a front view of the storage base with the support jack attached, Figures 11 to 18 are schematic diagrams showing the operating procedure of the engine loader, and Figure 19 is a diagram of the engine loader when assembled with an aircraft engine installed. The perspective view and FIG. 20 are sequence control diagrams of the engine loader during assembly. 1...Aircraft engine, 2...Engine loader (aircraft engine cargo handling device), 3...Horizontal boom (H/B), 5...Front pillar (F/
P), 6... Rear pillar (R/P), 10... Elevating table, 11... Storage base, 55... Airframe,
55a... Machine floor, 56... Roller which is an example of a rolling member.

Claims (1)

[Scope of utility model registration request] A device main body comprising a horizontal boom that is extendable in the horizontal direction, a front pillar and a rear pillar that are foldably attached to both ends of the horizontal boom, and a lift table that is supported by the horizontal boom and that mounts an aircraft engine; 1. A cargo handling device for an aircraft engine, comprising a storage base that is placed on a floor surface within an aircraft body and rotatably supports a plurality of rolling members that support the device body at a predetermined height above the floor surface.