JPH0656235B2 - Fluid pouring / discharging connection device - Google Patents

Description

Description: TECHNICAL FIELD The present invention relates to a fluid supply / discharge connection device, and more particularly, a fluid supply / discharge connection device suitable for injecting and discharging a cryogenic fluid in the atmosphere. Regarding

[Conventional technology]

INDUSTRIAL APPLICABILITY The present invention is suitable for use in a fluid supply / discharge connection device, particularly in a connection portion between a rocket and a ground facility when supplying a large flow rate, a large amount of liquefied oxygen, liquefied hydrogen, etc. to a satellite launch rocket. Regarding the connection device, in addition to the function of supplying these fluids securely and safely without leakage, the connection device on the ground equipment side can be separated from the rocket without trouble when the rocket is launched, and the connection device on the rocket side is light in weight Nothing has hitherto been found that can fully satisfy the functions required for a rocket.

[Problems to be solved by the invention]

 The technical problems solved by the present invention are as follows.

1. A fluid supply / discharge connection device that can prevent leakage of fluid and can reliably supply and discharge a large amount of fluid.

2. (EN) Provided is a fluid supply / drainage connection device that can be easily connected and disconnected.

3. Prevent icing, especially in connection devices suitable for cryogenic fluids.

4. The weight of the fluid supply / discharge connecting device has been reduced, and in particular, the weight of one of the connecting devices provided on the rocket side, which is required in the rocket, has been reduced.

[Means for solving problems]

In order to solve the above-mentioned problems, in the invention according to claim 1 (hereinafter referred to as the first invention), one connection device is extended in the axial direction of the fluid injection / exhaust passage to surround the passage. A connecting piece having a sealing surface is attached to the tip of the arranged double bellows, and a device for supplying and discharging a pressurized fluid is provided in this chamber with the space between the double bellows being a closed chamber, and the other connecting device is the connecting piece. Has a cylindrical seal facing the.

Next, in addition to the above, in the invention described in claim 2 (hereinafter referred to as the second invention), a box for forming a closed chamber around both connecting portions and a device for supplying a purging fluid to the closed chamber Is provided.

[Action]

In the first aspect of the invention, when the pressurized fluid is supplied into the closed chamber formed by the double bellows, the bellows expands in the direction of the cylindrical seal due to the fluid pressure, and the sealing surface of the joining piece comes into contact with and pressurizes the cylindrical seal. The required seat surface pressure can be obtained.

Therefore, the operation of connecting the connecting devices is simple, and it is possible to provide the connecting device without leakage.

Further, when the connecting device is separated, the joining piece is separated from the tubular sheet by the restoring force of the bellows by only discharging the pressurized fluid, and the separation can be surely performed.

In the second invention, in addition to the first invention, since the box for forming the closed chamber and the supply device for the purging fluid are provided in the closed chamber as described above, when the both connecting devices are connected,
By first supplying the purging fluid into the closed chamber,
Air is purged around the both connecting devices to become an atmosphere of the purging fluid, and freezing of the connecting devices is prevented by using the purging fluid that does not change or solidify depending on the temperature of the supplied or discharged fluid. You can

〔Example〕

An embodiment of the present invention will be described with reference to FIG. 1 and FIG.

The present embodiment is a connecting device between a rocket and a ground facility for pouring and discharging liquefied oxygen or liquefied hydrogen (hereinafter referred to as liquid oxygen or the like) to and from the rocket.

Reference numeral 1 denotes a ground-side connecting member, which has a pouring / discharging hole 1a formed at its central portion and is provided at the tip of the ground-side pouring / discharging pipe.
The inner nipple 3 and the outer nipple 4 extending in the axial direction of the shoulder portion 2 and the pouring / discharging hole 1a connected thereto are provided. The pouring / discharging hole 1a and the inner side of the inner nipple 3 communicate with each other to form a pouring / discharging path A for liquid oxygen or the like. Reference numeral 9 is an annular joint piece inserted between the two nips 3, 4 in the vicinity of the end portions of the both nips 3, 4, the outer surface of the tip part of which is a smooth spherical sealing surface 9a and a liquid in the inner hole part. It has a hole 9b which is a passage for oxygen and the like. Cylindrical members 7 and 8 are provided with their both ends attached to the connecting member 1 and the joining piece 9 as shown in FIG. 1, extending in the axial direction of the pouring / discharging passage A and surrounding the pouring / discharging passage A. The inner bellows and the outer bellows, and the annular space surrounded by the double bellows 7, 8 and the connecting member 1 and the joint piece 9 forms a closed chamber B. The connection member 1 is provided with a pressurization port 5, one end of the pressurization port 5 is opened to the closed chamber B, and the other end is the third port.
As shown in the drawing, the solenoid valve 16 is connected to a helium supply / discharge pipe 17 which is connected to a helium gas source (not shown). Each of the above members constitutes the ground-side connecting device C.

On the other hand, a socket 10 including a cylindrical seal 10a and a seat portion 10b which is attached to the tip end side of the seal 10a and forms a seal by contacting with the sealing surface 9a is attached to a rocket via an attaching member 11 and will be described later. The sealing surface 9a of the joint piece 9 is pressed against the seat portion 10b when the fluid is supplied and discharged. The socket 10 is connected to a pipe in the rocket. Reference numeral 13 denotes a box, one side of which is attached to the connecting member 12 of the ground-side pouring / discharging pipe, and the other side of the box 13 is removably attached to the rocket outer plate, and has the ground-side connecting device C and socket inside thereof. A closed chamber D that closes the periphery of 10 is formed. An opening 15 is provided in the box 13, and a page helium gas injection / exhaust pipe 14 is connected to the opening 15.

In this embodiment, when the box 13 is attached to the rocket outer plate as described above, as shown in the upper half of FIG. 1, the sealing surface 9a of the joint piece 9 and the seat portion 10b of the socket 10 are connected to each other. Are not in contact with each other and face each other with a gap. In this state, a small amount of helium gas is caused to flow into the sealed chamber D of the box 13 through the page helium gas injection / exhaust pipe 14,
The surroundings of the connection device C and the socket 10 on the ground side are set as helium zero atmosphere. Next, the solenoid valve 16 is operated to supply the helium gas for pressurization to the closed chamber B between the double bellows 7, 7 through the helium gas supply / discharge pipe 17 and the pressurization port 5. Due to the internal pressure of the helium gum in the closed chamber B, the bellows 7 and 8 extend to the left in FIG. 1, and the joint piece 9 attached to the tip of the bellows 7 and 8 moves to the left to the lower half of FIG. As shown, the sealing surface 9a is in close contact with the seat portion 10b,
Further, the seat surface 9a is pressed against the seat portion 10b by the pressure of the helium gas to secure a necessary seat surface pressure. Further, the force that the connecting member 1 receives from the helium gas in the closed chamber B can be received by the box 13 attached to the rocket outer plate. Therefore, in this state, the pouring / discharging path A
Since a passage formed by the inside of the hole 9b of the joining piece 9 and the cylindrical seal 10a is formed, the pouring / discharging passage A, the joining piece 9, the cylindrical seal are formed.
Liquid oxygen or the like can be supplied into the rocket through 10a, or conversely, can be discharged from the rocket.

FIG. 4 shows the relationship between the pressure of the helium gas supplied between the double bellows 7 and 8, the seat surface pressure between the sealing surface 9a and the seat portion 10b, and the leakage amount of liquid oxygen and the like. When the helium gas pressure reaches Po, the required seat surface pressure is obtained and leakage does not occur. Therefore, if the pressure of the helium gas supplied to the closed chamber A is set to be equal to or higher than Po and the value is held,
Liquid oxygen etc. can be supplied and discharged without leakage.

Further, when the ground side connection device C is separated, the solenoid valve 16 is operated to exhaust the helium gas in the closed chamber B, and the sealing surface 9a of the joint piece 9 is operated by the restoring force of the bellows 7, 8. Move it away from the seat part 10b, and then on the box 1
This can be done by removing 3 from the rocket skin.

Since this embodiment has the above-described configuration and operation, the following effects can be obtained.

1. By supplying helium gas for pressurization into the closed chamber B formed between the double bellows 7 and 8, a necessary seat surface pressure is secured between the seal surface 9a and the seat portion 10b,
A large flow rate and a large amount of liquid oxygen can be supplied and discharged without leakage without fail.

2. By supplying helium gas into the closed chamber D of the box 5, the surroundings of the ground-side connecting device C and the socket 10 become zero helium atmosphere, and icing can be prevented when supplying and discharging low temperature liquid oxygen and the like.

3. The ground-side connecting device C can be attached to the rocket by a simple operation of attaching the box 13 to the rocket outer plate.

4. When the ground-side connecting device C is separated, as described above, the pressurizing helium gas in the closed chamber B is discharged, and the restoring force of the bellows 7, 8 separates the sealing surface 9a from the seat portion 10b. This can be surely done by a simple operation of removing the box 13 from the rocket skin.

5. The socket 10 provided on the rocket side is only composed of the cylindrical seal 10a and the seat portion 10b, and can be reduced in weight.

Although helium gas is shown as the pressurizing gas to be supplied into the closed chamber B and the box 13 in the present embodiment, it does not liquefy or solidify at the fluid temperature handled before and after flowing liquid oxygen or the like to be supplied and discharged. Appropriate gas or fluid can be used.

Needless to say, the fluid to be supplied and discharged may be liquid oxygen, liquid hydrogen, ultra-low temperature fluid such as liquid nitrogen and LNG, or other fluids.

Further, in the present embodiment, the socket 10 is provided with the seat portion 10b, but omitting this, the shape of the material tip of the cylindrical seal 10a is appropriately selected so that the sealing surface 9a of the joining piece is directly attached to the tip of the cylindrical seal 10a. It is also possible to make contact to form a sealing surface.

〔The invention's effect〕

As described above, the first aspect of the invention secures the seat surface pressure required in the connecting device by supplying the pressurized fluid having a desired pressure to the closed chamber formed between the double bellows. Therefore, the fluid can be supplied and discharged under the condition that there is no leakage.

Moreover, the connection device can be attached and detached quickly by a simple operation for supplying and discharging the pressurized fluid. Particularly, at the time of disconnection, the connecting device is reliably separated by the restoring force of the double bellows. Further, one of the connecting devices is a simple one having a cylindrical seal and can be reduced in weight, and is particularly effective when used for a device such as a rocket that requires reduction in weight.

In addition to the effects of the above-mentioned first invention, the second invention can form a zero atmosphere with a purging fluid around both the connection devices, and in particular, when supplying and discharging an ultra-low temperature fluid, the connection device is frozen. It can be prevented, and there will be no damage due to freezing during the separation. Therefore, the second invention is effective in supplying and discharging a large amount of ultra-low temperature fluid such as liquid oxygen, liquid hydrogen, liquid nitrogen, or LNG, and particularly provides a fluid supply / discharge connection device suitable for rockets. can do.

[Brief description of drawings]

FIG. 1 is a longitudinal sectional view showing an essential part of an embodiment of the present invention, FIG. 2 is a side view of the same, FIG. 3 is a schematic view of the above embodiment, and FIG. 4 is a helium gas pressure in the above embodiment, It is explanatory drawing which shows the relationship between seat surface pressure and the amount of leaks. In the drawing, 1 is a connecting member, 3 is an inner nipple, 4 is an outer nipple, 5 is a pressurizing port, 7 is an inner bellows, 8 is an outer bellows, 9 is a connecting piece, 10 is a socket 10a is a cylindrical seal, and 15 is a box A. Road, B is a closed room, C is a ground connection device, and D is a closed room.

 ─────────────────────────────────────────────────── ─── Continuation of front page (72) Hirotaka Okura 10 Oe-cho, Minato-ku, Nagoya-shi, Aichi Prefecture, Nagoya Aircraft Manufacturing Co., Ltd. (72) Toru Nakamura 10 Oe-cho, Minato-ku, Nagoya-shi, Aichi Address Mitsubishi Heavy Industries, Ltd.Nagoya Aircraft Works

Claims (2)

[Claims] 1. A connecting member to a pipe having a fluid pouring / discharging passage in a central portion, a joint piece having a sealing surface at a tip and a through hole in the central portion, a shaft surrounding the fluid pouring / discharging passage of the connecting member. One connecting device having double bellows arranged so as to extend in the direction and having both ends attached to the connecting member and the joining piece to form a sealed chamber therebetween, and a device for supplying and discharging a pressurized fluid to and from the sealed chamber. And the other connecting device that is provided so as to face the connecting piece and has a cylindrical seal. 2. A connecting member to a pipe having a fluid injection / exhaust passage in the central portion, a joint piece having a sealing surface at the tip and a through hole in the central portion, surrounding the fluid passage of the connecting member and extending in the axial direction of the passage. One connection device having double bellows arranged so as to extend and both ends of which are attached to the connection member and the joining piece to form a sealed chamber therebetween, and a device for supplying and discharging pressurized fluid to and from the sealed chamber; The other connecting device facing the joining piece and having a cylindrical seal; a box forming a closed chamber around the both connecting devices; and a device for supplying a purging fluid to the closed chamber of the box. A fluid pouring / discharging connection device.