JP2561761Y2 - Replacement device for seals for shock absorbers - Google Patents

Description

[Detailed description of the invention]

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a device for replacing a seal of a shock absorbing device of a heavy vehicle, particularly an aircraft.

[0002]

2. Description of the Related Art In general, an airplane is provided with a shock absorbing device called a shock strut between a wheel and a fuselage or a wing portion in order to reduce an impact received when landing and moving by a wheel. The shock strut has an elongated columnar shape having a cylinder and a piston therein, and has a built-in gas and oil to absorb shock by cooperative operation. Therefore, the shock strut has an O to seal the oil.
A ring-type seal is provided; This seal must be replaced if an oil leak occurs.

Referring to FIG. 4, a conventional method of exchanging a shock strut seal will be briefly described.
FIG. 4 is a view illustrating an operation of replacing a seal of a shock strut according to the related art. In FIG. 4, a shock strut 3 is connected between the wing 1a and the fuselage 1 of the airplane and the wheel 2. As will be described later, since the seal of the shock strut 3 is provided between the cylinder and the piston of the shock strut 3, the seal is exposed to the outside by extending the shock strut. Also, since the seal is an O-ring type, the wheel
After the shock strut 3 and the shock strut 3 are cut off from each other, a seal must be inserted through the gap. Therefore,
As shown in FIG. 4, a plurality of large jacks 40 are provided below the fuselage 1 and the wings 1a of the airplane, and the seal inside the shock strut 3 is exposed by lifting the entire airplane with the large jack 40.

[0004]

However, according to such a conventional method, it takes a long time to install the large jack 40, and lifting the airplane with the large jack 40 while keeping it horizontal requires a high level of skill. Failure to select a reliable support location would cause the jack to come off, which would require excessive time and effort, and also had a problem in terms of safety. Further, in order to mount the O-ring type seal on the shock strut 3, it is necessary to raise the shock strut and insert the seal from below. For this reason, conventionally, when replacing the seal, the shock strut must be hung from above by a rope or the like, and the seal must be attached to a predetermined position from below the shock strut beyond the hung rope, which requires a great deal of labor. Further, the leg of the shock strut has a slope facing downward, and is unstable to be supported by a jack or the like, which is not preferable from the viewpoint of work safety. SUMMARY OF THE INVENTION An object of the present invention is to provide a device that can easily and safely change a seal quickly.

[0005]

In order to achieve the above-mentioned object, the seal replacement device for a shock absorbing device according to the present invention has an inverted slope facing downward, and a mounting hole is provided on a surface intersecting the inverted slope. An apparatus for replacing an O-ring type seal for a shock absorbing device having a substantially trapezoidal main body having a slope,
A cylindrical portion provided below the slope so as to extend in parallel with the slope, a plate connecting the main body and one end of the cylindrical portion, and a pin portion protruding from a lower surface of the main body; The outer diameter of the cylindrical portion is substantially equal to the inner diameter of the mounting hole of the shock absorbing device, the slope of the slope is equal to the slope of the reverse slope, the cylindrical portion is inserted into the mounting hole, and the slope is The shock absorber is attached to the shock absorbing device by abutting on the reverse slope, and the pin portion is lifted while holding the shock absorbing device by raising the pin portion.

[0006]

According to the seal replacement device for the shock absorbing device of the present invention, the outer diameter of the cylindrical portion is substantially equal to the inner diameter of the mounting hole of the shock absorbing device, and the slope of the slope is equal to the slope of the reverse slope. So that the cylindrical part is inserted into the mounting hole,
In addition, the slope comes into contact with the reverse slope so that the slope is securely attached to the shock absorbing device, and the pin portion is raised so that the shock absorbing device is raised while being held.

[0007]

Embodiments of the present invention will be described below with reference to the drawings. In the description of the present embodiment, a gas means air or an inert gas (for example, N ² gas). FIG. 1 is a perspective view of the vicinity of one leg of a certain type of airplane.
Only two of the normally four wheels are shown. The wheels 2 mounted on the axle 4 are linked back and forth by a track beam 5. Although not shown, the vertically extending shock strut 3 has an upper part attached to the fuselage. Further, the lower portion of the shock strut 3 is attached to the rod 5a by the track beam 5 and the pin 5b at the pin portion 3a.

Next, the structure of the shock strut 3 will be briefly described. FIG. 2 is a view showing a state in which the shock strut 3 is lifted up and cut off from the track beam 5, and a part of the shock strut is a sectional view. In FIG. 2, shock struts 3
Consists of a cylinder portion 3b and a piston portion 3c. In a normal use state, the piston portion 3c is inserted into the cylinder portion 3b, and gas and oil are injected into a space 3d defined by the piston portion 3c. . The gas in the space 3d acts as a spring, and the oil in the space 3d acts as a damper, so that the cooperative action of the two reduces the impact received by the wheels at the time of landing, etc., so that the oil is not transmitted directly to the aircraft. ing. The oleo seal 3e is an O-ring type seal,
The inner circumference of the cylinder 3b and the outer circumference of the piston 3c are sealed to prevent oil in the space 3d from leaking to the outside. A gas port 3f is attached to the top of the cylinder portion 3b, and gas can freely enter and exit the cylinder portion 3b via the gas port 3f. The configuration of the shock strut is well known and will not be described in detail below.

Further, a device for filling the shock strut 3 with gas will be described. FIG. 3 is a view showing a distribution device for filling the shock strut 3 with gas.
In some aircraft models, five legs are provided, one of which replaces the seal of the shock strut, so that four legs can be used for the purposes described below at the time of replacement. Therefore, the distribution device 6 shown in FIG.
Has one gas inlet 6g and four gas outlets 6h. Actually, four gas outlets are to be connected to four shock struts, respectively. However, in FIG. 4, one gas outlet is used for simplicity of explanation and because all the structures are common. Only 6h is shown connected to the shock strut 3.

The gas inlet 6g of the distributor 6 is connected to a pressurizing means (not shown), that is, a compressor. The gas inlet 6g is connected to the gas outlet 6h via a main valve 6e and a sub-valve 6c. The gas outlet 6h
It is connected to a gas port 3f of the shock strut 3 via a hose 7.

A branch is provided from the gas inlet 6g to the main valve 6e, and a main drain valve 6f is provided at the end of the branch. The main valve 6e is freely openable and closable. When in its open position, gas from the compressor can pass to the sub-valve 6c side, and when in its closed position, gas from the compressor is blocked from passing to the sub-valve 6c side. It has become. A main pressure gauge 6d is provided between the main valve 6e and the sub-valve 6c, and the pressure of the gas supplied from the compressor is measured by the main pressure gauge 6d.

A branch is provided from the sub-valve 6c to the gas outlet 6h, and a sub-drain valve 6b is provided at the end of the branch. When the sub-valve 6c is openable and closable, the gas passing through the main valve 6e can pass to the gas outlet 6h when in the open position, and the gas passing through the main valve 6e can pass to the gas outlet 6h when in the closed position. Are individually blocked. When the sub-valve 6c is in the closed position and the sub-drain valve 6b is in the open position, the gas in the shock strut 3 is individually released to the atmosphere via the gas outlet 6h. A sub-pressure gauge 6a is provided between the sub-valve 6c and the gas outlet 6h, and the pressure of the gas in the shock strut 3 is individually measured by the sub-pressure gauge 6a.

The shock strut 3 originally acts to reduce the impact by the gas filled therein. However, the gas pushes the piston portion 3c by pumping the gas at a higher pressure than normally used. Thus, the shock strut itself can be extended beyond its normal length.

Further, with reference to FIGS. 5 and 6, the seal changing device of the present invention will be described. FIG. 5 is a perspective view of the seal replacement device of the present invention. FIG. 6 is a perspective view of an extension adapter which is a connecting member attached to the seal changing device.

In FIG. 5, the seal replacing device 50 includes a substantially trapezoidal main body 50a, a cylindrical portion 50c extending parallel to the slope below the side slope 50b of the main body 50a, and a main body 50a.
a plate 50d for connecting the a with the slope 50b;
And a pin portion 50e protruding from the lower surface of Oa. Body 50a
A horizontally extending groove 5 is provided at the center of the front and
0f is provided. The outer diameter of the cylindrical portion 50c is substantially equal to the inner diameter of the rod mounting hole of the piston portion 3c of the shock strut 3.

In FIG. 6, an extension adapter 51 is formed so as to coaxially connect a circular tube portion 51a and a cylindrical portion 51b. The inner diameter of the circular tube portion 51a is substantially the same as the outer diameter of the pin portion 50e of the seal changing device 50, and the pin portion 50e can be fitted into the circular tube portion 51a. The outer diameter of the cylindrical portions 51b and 50e is substantially equal to the inner diameter of a hole (not shown) provided on the support surface 52a of the alligator jack shown in FIG.

Further, a procedure for replacing the seal of the shock strut 3 will be described below with reference to FIGS. First, referring to FIG. 3, the distribution device 6 is connected via a hose 7 to a shock strut 3 other than the shock strut whose seal is to be replaced. As described above, in FIG. 3, for the sake of simplicity, the dispensing device 6 is shown as being connected to only one shock strut. It is assumed that gas is pressure-fed in the direction of arrow A from a compressor (not shown). Each sub valve 6c
Is in the open position, but the main valve 6e is in the closed position.

By the way, in a certain type of airplane,
One leg is provided in front of the fuselage, two legs are arranged in parallel at the rear of the fuselage, and one leg is provided on each of the left and right wings, for a total of five legs. I have. In this case, for example, when replacing the seal of the shock strut of the wing leg, only the two legs provided behind the fuselage need to be extended, and the leg in front of the fuselage needs to be extended. There is no. The reason for this is that if the shock struts of the two legs provided at the rear of the fuselage are extended, the aircraft lifts the rear of the fuselage in a posture that bows forward, thereby causing the wing to be replaced. This is because the shock struts on the legs also extend to expose the seal. Therefore, in such a case, it is sufficient to connect the hose 7 to the two shock struts. In this case, in order to secure the stability of the fuselage, the leg of the wing opposite to the leg to be replaced must not be extended. On the other hand, when the subject of the replacement work is any of the legs at the rear of the fuselage, it is necessary to extend a total of three of the legs at the left and right wings and the remaining legs at the rear of the fuselage. Therefore, in such a case, the hose 7 is connected to the three shock struts.

When the main valve 6e is opened in such a state, the gas pressure-fed from the compressor is evenly transmitted to two or three shock struts 3. The transmitted gas is transmitted to the piston 3c of the shock strut 3.
Press to extend two or three shock struts 3 simultaneously. As the shock strut 3 elongates, the aircraft body rises. When the main valve 6e is closed when the body has risen to the predetermined position, the gas pumping stops, and the rise of the body also stops. If the degree of extension of the shock strut 3 is different due to the weight distribution of the aircraft and the aircraft is not horizontal in the left-right direction, the sub-drain valve 6
By setting b to the open position, the gas in the shock struts 3 is released to the atmosphere, and the shock struts are individually contracted so that the aircraft becomes horizontal. In addition, strong wind (about 1
As long as two or three shock struts are appropriately extended as described above, the fuselage can be stably held as long as no blows (5 knots or more) are blown, but an auxiliary jack can be used if necessary. In that case, it is not necessary to extend all of the shock struts, and only the shock strut at a position opposing the auxiliary jack may be extended.

FIG. 2 shows a state of the shock strut in which the seal is to be replaced in a state where the shock strut is extended and the fuselage is raised. Cylinder part 3
b and the piston portion 3c are relatively moved in the direction in which they are separated from each other, but are not completely separated from each other, and the two seals 3e are exposed. From this state, the track beam 5 and the rod 5a are cut off from the piston 3c, and the piston 3c is raised as described below.

FIG. 7 is a view showing a state in which the piston portion 3c of the shock strut is raised by using the seal replacement device 50 in order to replace the seal. To achieve such a state, first, the seal exchanging device 50 is connected to the extension adapter 51, and the alligator jack 52 is further connected.
The cylindrical portion 50c of the seal exchanging device 50 supported by the piston is inserted into the rod mounting hole of the piston portion 3c, and the slope 5
0b is brought into contact with the leg side of the piston 3c. The new seal 3e is set under the support surface 52a of the alligator jack 52 in advance as shown in the figure. In this state, the extension adapter 5
1 is placed on the support surface 52a of the alligator jack 52, the jack is operated to move the piston 3c to the track beam 5
And lift it upwards. The groove 50f of the seal changing device 50 is used when the seal changing device 50 is tied to the piston portion 3c with a wire 53 or the like as shown in FIG. It is to prevent. As is clear from FIG. 7, the thickness of the seal replacing device 50 is substantially the same as the thickness of the leg of the piston portion 3c, and does not interfere with the track beam 5 when the piston portion 3c rises.

The used seal may be cut in advance by a cutter or the like, or may be removed from below the piston portion 3c at this stage. After removing the used seal, the new seal 3e is moved from the alligator jack 52 through the seal changing device 50 and the leg of the piston 3c to a predetermined position. Since the seal 3e is made of rubber, it can be extended to some extent. After that, the alligator jack 52 is operated to move the piston portion 3
c is lowered, and the track beam 5 and the rod 5a are connected by the pins 3a and 5b.

Referring again to FIG. 3, when the main drain valve 6f of the distribution device 6 is opened with the above operations completed, all the gas in the shock strut 3 connected to the hose 7 is released to the atmosphere, and the airframe is released. Descends. While monitoring the sub-pressure gauge 6a, when the gas in the shock strut 3 reaches an appropriate pressure, the main drain valve 6f is closed. Fine adjustment of the pressure in each shock strut 3 may be performed by opening and closing the sub-valve 6c and the sub-drain valve 6b, respectively. When the fine adjustment is completed, the gas port 3f is closed, and the dispensing device 6 is cut off from the shock strut 3, whereby the seal replacement operation is completed.

[0024]

According to the seal replacement device for the shock absorbing device of the present invention described in detail above, the outer diameter of the cylindrical portion is substantially equal to the inner diameter of the mounting hole of the shock absorbing device, and the slope of the slope is inclined. Is equal to the slope of the inverted slope, the cylindrical portion is inserted into the mounting hole, and the slope is brought into contact with the inverted slope, whereby the cylinder is securely attached to the shock absorbing device, and the pin Is raised, the shock absorbing device is raised while being held.

[Brief description of the drawings]

FIG. 1 is a perspective view around one leg of a certain type of airplane.

FIG. 2 is a view showing a state in which a shock strut 3 is lifted upward and a track beam 5 is cut off.

FIG. 3 shows a distributor for filling shock struts 3 with gas.

FIG. 4 is a view illustrating an operation of replacing a seal of a shock strut according to the related art.

FIG. 5 is a perspective view of the seal replacement device of the present invention.

FIG. 6 is a perspective view of an extension adapter attached to the seal replacing device.

FIG. 7 is a view showing a state in which a piston portion 3c of a shock strut is raised by using a seal replacement device 50 in order to replace a seal.

[Explanation of symbols]

 2 Wheel 3 Shock strut 6 Distributor 50 Seal exchange device 51 Extension adapter

Continued on the front page (72) Inventor Tatsuo Yanagisawa 5-2-3-303, Sakuranocho, Toyonaka-shi, Osaka (72) Inventor Shinji Ikegami 5-6 Tennodai, Abiko-shi, Chiba Prefecture Cosmo Tennodai 605 (72) Inventor Omagari Yasuyuki Park Hills K507, 553-1 Shinanomachi, Totsuka-ku, Yokohama-shi, Kanagawa Prefecture (72) Koji Kihara 89, Honmoku Midorigaoka, Naka-ku, Yokohama-shi, Kanagawa Prefecture, Japan A-406, Midorigaoka Company House A-406 (72) Creator Shiki Sugawara Higashi-Oi, Shinagawa-ku, Tokyo 1-13-12-1109 (72) Inventor Kenzo Shimizu 4-15 Shimizu-cho, Chitose-shi, Hokkaido Tsutsumi Mansion 502

Claims (3)

(57) [Scope of request for utility model registration] 1. An apparatus for replacing an O-ring type seal for a shock absorbing device having an inverted slope facing downward and having a mounting hole in a plane intersecting the inverted slope, comprising: a base having a slope; A main body having a shape, a cylindrical portion provided below the slope to extend parallel to the slope, a plate connecting the main body to one end of the cylindrical portion, and a pin protruding from a lower surface of the main body. The outer diameter of the cylindrical portion is substantially equal to the inner diameter of the mounting hole of the shock absorbing device, the slope of the slope is equal to the slope of the reverse slope, and the cylindrical portion is inserted into the mounting hole. And a seal replacement device which is attached to the shock absorbing device when the slope comes into contact with the reverse slope, and is raised while holding the shock absorbing device by raising the pin portion. 2. The seal exchanging device further includes a groove in the main body, and when attached to the shock absorbing device, a string-shaped fastening means for fastening the shock absorbing device and the seal exchanging device. The seal replacement device of claim 1 adapted to receive. 3. The seal exchanging device according to claim 1, wherein said seal exchanging device further comprises a connecting member connected to said pin portion.