US3572441A

US3572441A - Liquid discharge tank adapted to be hung and transported

Info

Publication number: US3572441A
Application number: US824037A
Authority: US
Inventors: Masuzoh Nodegi
Original assignee: Takashima and Co Ltd
Current assignee: Takashima Co Ltd; Takashima and Co Ltd
Priority date: 1968-05-15
Filing date: 1969-05-13
Publication date: 1971-03-30
Anticipated expiration: 1988-03-30
Also published as: JPS4927400B1

Abstract

A liquid discharge tank adapted to be hung from a helicopter can be filled with a fire extinguisher liquid when a tubular extension having a discharge part is withdrawn into the tank body and secured to the upper portion of the tank body. The fire extinguisher liquid is discharged from the tank by releasing the extension from the upper portion of the tank body so that it projects downwardly from the tank body.

Description

United States Patent Inventor Masuzoh Nodegi Tokyo, Japan Appl. No. 824,037 Filed May 13, 1969 Patented Mar. 30, I971 Assignee Takashima Kahashiki Kaisha Tokyo, Japan Priority May 15, 1968 Japan 43-32675 LIQUID DISCHARGE TANK ADAPTED TO BE HUNG AND TRANSPORTED 3 Claims, 2 Drawing Figs.

US. Cl 169/2, 169/30, 222/530, 239/171, 244/136 Int. Cl A62c 5/00 Field of Search 169/1, 2, 30, 34; 244/136; 239/171; 222/494, 495, 528, 530, 535

References Cited UNITED STATES PATENTS I/1957 Rust 169/1 3/1957 Wainess 169/26 7/1961 Borah 222/530 2/1969 Hubbard 239/ l 7 1X Primary Examiner- M. Henson Wood, Jr. Assistant ExaminerMichael Y. Mar Attorney-Kelman and Berman ABSTRACT: A liquid discharge tank adapted to be hung from a helicopter can be filled with a fire extinguisher liquid when a tubular extension having a discharge part is withdrawn into the tank body and secured to the upper portion of the tank body. The fire extinguisher-liquid is discharged from the tank by releasing the extension from the upper portion of the tank body so that it projects downwardly from the tank body.

Patented "March 30, 1971 3,5i2,441

2 Sheets-Sheet 1' INVENTOR.

BY Mqmzoh M00423! GE TANK ADAP'IED TO BE HUNG AND TRANSPORTED The present invention relates 'to a liquid discharge tank adapted to be filled with a fire extinguisher liquid and suspended from and transported by a helicopter so that the fire extinguisher liquid can be discharged from the sky.

in recent years, attempts have been to make use a helicopter or airplane in extinguishing fires in densely populated residential areas where houses stand close together and the free movement of fire engines is obstructed, fires in chemical plants, or fires in a forest which cannot be brought under control on the ground. Known fire'extinguishing activities from the sky have many disadvantages. For example, the amount of fire extinguisher liquid or agent that can be contained in a helicopter or plane is restricted by the space in the helicopter or plane. Discharging the liquid from the helicopter or plane requires a pump and the space for carrying the fire extinguisher liquid is further reduced by the pump that has also to be carried. Moreover, discharging the fire extinguisher liquid from the sky not only makes the fireextinguishing operation very complicated, but also has the disadvantage that the liquid discharged tends to be scattered in the air, making it impossible to concentrate the liquid on the burning object. In any event, it was impossible heretofore to extinguish,a fire from the sky by using a single helicopter or airplane.

It is a principal object of the present invention to provide a liquid discharge tank which permits to transport a large quantity of fire extinguisher liquid in one flight and discharge the same in such a manner that the liquid can be concentrated on the burning object. The tank is adapted to be hung from a helicopter or like aircraft has a larger capacity than tanks of the conventional type which are carried in .the helicopter, so that the tank can be filled with a large quantity of fire-extim guishing liquid. The tank consists of a tank body and an extension formed at the bottom of the tank body and having a discharge port at the free end. When the tank is to be filled with a fire extinguisher liquid the extension can be withdrawn into the tank body so that the discharge port is directed upwardly and the extension is supported on the upper portion of the tank body. The fire extinguisher liquid contained in the tank can be discharged and concentrated on the burning object upon release of the free end of the extension from the upper portion of the tank body. The extension released from engagement is forced by the weight of the fire extinguisher liquid in the tank body to move downwardly and out of the tank body. Thus it is possible to discharge the fire extinguisher liquid through the discharge port in an instant after release of the extension from the upper end of the tank body. The weight of the fire extinguisher liquid is utilized to discharge and concentrate the same on the burning object without using pumps or the like.

Additional objects as well as other features and advantages of this invention will become apparent from the description of a preferred embodiment set forth hereunder when considered in conjunction with the accompanying drawings, in which:

FIG. l is a front elevational view of a liquid discharge tank of the present invention; and

FIG. 2 is an elevational sectional view, on an enlarged scale, of the support mechanism and the hanging bar of the tank of HO. 1.

The tank body 1 is a bag formed integrally with a tubular extension 2. ln the illustrated position, the extension depends from the bottom of the tank body and has a discharge port 3 at the free end thereof. The extension 2 can be withdrawn into the tank body 1 as shown in phantom view in F IG. 1. When the extension 2 is withdrawn into the tank body 1, fire extinguisher liquid may be retained in the tank body; when the extension hangs downwardly as shown in solid lines, the fire extinguisher liquid is discharged through the extension and the discharge port. The tank is made of bias-cut layers of nylon fabric coated with rubber and sewn together spirally or bonded to one another so that the tank may withstand the pressure of liquid contained therein. Although not shown, the tank body 1 may be enclosed by a metal frame so as to keep UQUTD DTSC s.

the fabric taut. This facilitates pouring a fire extinguisher liquid into the tank and transporting the tank.

FIG. 2 shows in detail the supporting mechanism for the extension 2 in the tank body 1 and the cylinder mechanism for releasing said supporting mechanism. In FIG. 2, a cylinder 4 having a cover 13 at its lower end is mounted on the top of the tank body 1. From an opening 5 formed in the head of said cylinder 4 projects an upper end portion 7 of a piston 6 mounted in the cylinder 4.

A hanging bar 8 is fixedly attached to the portion 7 of the piston 6. The hanging bar 8 is adapted to be hitched to a hook (not shown) on the underside of a helicopter. When the tank is transported this way, the weight of the fire extinguisher liquid contained in the tank is applied to the hanging bar8, whereby hydraulic fluid in the cylinder 4 is compressed by the piston 6. An electromagnetic valve 9 is mounted on a hydraulic fluid passage 10 which connects the cylinder 4 with an annular groove 15 formed in the cylinder cover 13 above the upper end of an inner annular recess 14. The passage 10 is opened and closed by a valve body 11 of the electromagnetic valve 9. A cable 12 is connected to an electric operation,

system (not shown),in the helicopter and to the electromagnetic valve 9. When the passage 10 is opened, hydraulic fluid from the cylinder 4 is; supplied to said annular groove l5. Loosely mounted in the annular groove 15 is the upper portion of a cylindrical cam 16 whose lower portion is disposed in the inner annular recess 14. The cylindrical cam 16 is adapted to be moved downwardly by the pressure of the hydraulic fluid. Pawls 17 are mounted below the cylindrical cam 16 about a sleeve 19. Each of the pawls 17 has an engaging portion at the outer center edge, a detent 17b at the lower end, and an offset portion 17c at the inner center edge. A coil spring 18 is mounted between an annular shoulder 16a of the cylindrical cam 16 and the engaging portions 17a of the pawls 17 so as to urge the cam 16 upwardly to thereby prevent the lower portion of the cam 16 from pressing against the pawls 17. The detents 17b are normally maintained in engagement with an annular projection 26 of a tubular member 21. When the cam I6 is moved downwardly by hydraulic pressure, the pawls 17 are pivoted about the inner offset portions 17c so that the detents 17b are moved outwardly and released from engagement with the annular projection 26.

The sleeve 19 having a wider portion 19a and a narrower portion 19b is threadedly connected to the center of the cylinder cover 13. The wider portion 19a of the sleeve 19 is formed with vertically elongated slots 20 equal in number to the pawls 17. The pawls 17 are normally supported by the sleeve 19, the detents 17b being received in said slots 20 and the offset portions 17c being fitted over the junction of the wider portion 19a and the narrower portion 19b of the sleeve. The member 21 is loosely fitted in the sleeve 19.

A rope 22 secured to the free end of the extension 2 is attached to the tubular member 21. When the fire extinguisher liquid fills the tank body 1, the .rope 22 is pulled downwardly by the weight of the liquid and tends to pull the member 21 out of the sleeve.

When the member 21 is released by the pawls 17, the extension 2 is released from its withdrawn position and caused by the hydraulic pressure to depend from the tank body as shown in FIG. 1, whereby the liquid can be discharged in an instant.

In operation, the electromagnetic valve 9 is actuated to close the hydraulic fluid passage 10, and the hanging bar 8 connected to the piston 6 is hitched to the lower portion of a helicopter. The weight of the fire extinguisher liquid contained in the tank body 1 is applied to the hanging bar 8, so that hydraulic pressure is produced in the cylinder 4. When the passage 10 is opened, hydraulic pressure is applied to the upper end of the cylindrical cam 16. This causes the cam 16 to move downwardly against the biasing force of the spring l8, whereby the pawls 17 are caused to pivot and to move their detents outwardly. This permits the member 21 and the rope 22 to move downwardly with the extension 2, and the fire extinguisher liquid is released through the discharge port 3.

The release of the fire extinguisher liquid from the tank body 1 removes the hydraulic pressure from the upper end of .the cylindrical cam 16 which is moved upwardly by the spring 18, thereby restoring the pawls 17 to their original positions.

A rope 23 is provided for returning the member 21 to is original position. Belts 24 attach the tank body 1 to the cylinder 4, and manual pawl disengaging means 25 are slidably mounted on the lower end of the member 21.

While the invention has been described with reference to a preferred embodiment thereof, it will be understood of course, that the invention is not limited to the specific details of the embodiment shown and described, since many changes and modifications may be made therein, and it is contemplated therefore, by the appended claims, to cover any such modifications and changes as fall within the spirit and scope of this invention.

lclaim:

l. A tank adapted to be suspended from an aircraft comprismg:

a. a tank body impervious to liquid;

b. suspending means for suspending one end of said body from an aircraft;

c. a tubular extension on the opposite end of said body, said extension having a free end formed with a discharge port and being capable of being withdrawn into said body toward said one end;

(1. supporting means on said one end of said body for supporting said free end in the withdrawn position;

e. releasing means for releasing said supporting means and for thereby permitting said port to be expelled by the weight of liquid in said body while said one end is suspended from said aircraft; and

f. a source of hydraulic fluid on said body, said releasing means being connected to said source and hydraulically operated.

2. A tank as set forth in claim 1, wherein said suspending means include a fastener member adapted to be attached to said aircraft, and said source includes a cylinder element and a piston element slidable in said cylinder element, said element being respectively secured to said fastener member and to said body for compressing a liquid in said cylinder under the weight of a liquid in said body when the fastener member is attached to said aircraft.

3. A tank adapted to be suspended from an aircraft comprismg:

a. a bag impervious to liquid and constituting the body of said tank; l

b. suspending means for suspending one end of said body from an aircraft;

d. supporting means on said body for supporting said free end in the withdrawn position; and

e. releasing means for releasing said supporting means and for thereby permitting said port to be expelled by the weight of liquid in said body while said one end is suspended from said aircraft,

1. said bag and said extension being integrally made of pliable material.

Claims

1. A tank adapted to be suspended from an aircraft comprising: a. a tank body impervious to liquid; b. suspending means for suspending one end of said body from an aircraft; c. a tubular extension on the opposite end of said body, said extension having a free end formed with a discharge port and being capable of being withdrawn into said body toward said one end; d. supporting means on said one end of said body for supporting said free end in the withdrawn position; e. releasing means for releasing said supporting means and for thereby permitting said port to be expelled by the weight of liquid in said body while said one end is suspended from said aircraft; and f. a source of hydraulic fluid on said body, said releasing means being connected to said source and hydraulically operated.

3. A tank adapted to be suspended from an aircraft comprising: a. a bag impervious to liquid and constituting the body of said tank; b. suspending means for suspending one end of said body from an aircraft; c. a tubular extension on the opposite end of said body, said extension having a free end formed with a discharge port and being capable of being withdrawn into said body toward said one end; d. supporting means on said body for supporting said free end in the withdrawn position; and e. releasing means for releasing said supporting means and for thereby permitting said port to be expelled by the weight of liquid in said body while said one end is suspended from said aircraft,