US1728449A

US1728449A - Aerial-filling device

Info

Publication number: US1728449A
Application number: US477231A
Authority: US
Inventors: Procofieff-Seversky Alexander
Original assignee: Individual
Current assignee: Individual
Priority date: 1921-06-13
Filing date: 1921-06-13
Publication date: 1929-09-17
Anticipated expiration: 1946-09-17

Description

Sept. 1: 7, 1929. A. PROCOFlEFF-SEVERSKY 1 72 5 449 AERIAL FILLING DEMIYGE' Filed June 13, 19211 2' Sheets-Sheet l mmw Sept. 17, 1929. A. PROCOFIEFF-SEVERSKY 1,728,449

AERIAL FILLING DEVICE File J n 1 1921 2 Sheets-Sheet Patented Sept. 1.7, 1929 UNITED STATES PATENT OFFICE ALEXANDER PBOCOFIEFI-SEVEBSY, OF NEW YORK, N. Y.

AERIAL-FILLING DEVICE Application filed June is,

This invention relates in general to means for supplying fuel to aircraft while in flight and more particularly to a novel supply means, a novel receiving means, and means for automatically providing for the passage of fuel when the supply means and receiving means are operative in communication with each other, and means for preventing the escape of 'fuel when the supply,

means and receiving means are out of communication. i

The problem of providing aircraft with fuel while in flight is a very important .one. It is well known that dirigibles and large bombing iplanes are almost completely at the mercy o the small, easily maneuverable, pursuit planes, and that it is almost essential that in every bombing expedition the dirigible or large bombing planes must be accompanied by an escort of pursuit planes for purposes of defense. However, the small weight carrying capacity of these small fast planes permits them to carry only two or three hours fuel and thus limits their range of operation to such a considerable degree' that it is impossible to conduct a bombing expedition any great distance into the enemy territory.

Furthermore, extended flights for commercial purposes have hitherto been impractical in that if the flight is to last for any great number of hours practically the whole useful lifting capacity of the plane is exerted in carrying fuel, leaving but a small art thereof for carrying useful commercial oad. I propose to provide large fuel tankers, either dirigibles or large planes, to supply fuel to the pursuit ships while in flight.

It may be practlcal to have one such tanker in a squadrolrof planes, the tanker carrying no bombs, or each large craft may have supply means in addition to its bomb load.

It is the object of my invention to provide means whereby one aircraft can obtain fuel from another while in flight.

It is an object of my invention to provide a novel supply. means from the supply craft or tanker and a novel receiving means for the ship to. be provided with fuel. A further object. is to provide a novel valve ar- 1921. Serial No. 477,231.

Figure 4 is an enlarged detail showing of the valve mechanism with the valve open; Figure 5 is the, same with the valve closed;

Figure 6 is a detail of the receiving apparatus with the funnel in operative position;

Figure 7 is a detail of the same showing the funnel in inoperative collapsed position.

Referring to the drawings in detail 1 is the fuel supply tank which is mounted on the frame 4 of the dirigible, bombing plane, or whatever the mother ship or tanker is to be. An outlet pipe 2 bearing in frame 4, is provided for tank 1. This pipe communicates with a. pipe 8 which acts as the axle of drum 9, upon which the fuel supply hose 15 is adapted to be wound. A

valve 6 is provided between

pipes

2 and 8 to cut ofi'the supply fuel to pipe 8 when desired. The axle of pipe 8 bears rotatably in .the bearing 7 and has its hollow portion extended to a point just beyond the center of the drum. Here the axle is provided with an externally screw-threaded lug 8 which has an opening 12 bored therethrough into the interior of the hollow portion of the axle to provide a passage for the fuel from the interio'r. of the axle to the supply hose 15.

Supply hose 15 is provided with the usual nipple 8' for securing the hose 2 to the lug or tap 13. The end 14 of the axle 8 freely rotates in a conical bearing in frame 5. Fixedly mounted on the axle 8', adjacent to the drum 9is a side wheel 10 around which; extends a cable or any suitable means for hose when desired.

In Figure 3 the lower end of the hose 15 is shown when it is extended and just about to enter the receiver. A cable 30 is conducted-through guides 30, secured to the sides of the supply hose 15 for the purpose of operating valve 29 to permit the escape of the waste fuel in hose 15 after valve 6 has been closed and it is desired to wind up the. drum and draw the hose in. The valve 29 is normally closed.

Figures 4 and 5 show in detail the automatic valve which forms an important feature of my invention. The hose 15 is provided at its lower outlet with a metal collar or cylinder 16 which has an interior valve seat 17.

Anaxle 18 extends diametrically through the cylinder near its lower portion and has fixedly mounted thereon a spur gear 19 which is adapted to mesh with a second spur gear 20 mounted on a second axle 21, mounted centrally on the valve seat. A valve 2 is mounted on the axle'2l.

iMourted exteriorly of the cylinder 16 and on axle 18, are two

half cylinders

23 and 27.

The member 27 is fixedly secured to the side of the cylinder 16, but member 23 is fixedly mounted on axle 1 8 and is adapted to pivot with the rotating of this axle as will hereinafter be disclosed, to act as a lever for the operation of the valve 22,

Cylinder 16 has at its base a metal are 24 which is grooved to provide a seat in which lies a light metal leaf spring 25. This spring is fixedly attached at a point 26 to the member 27 which. as hereinbefore stated is immovably mounted on cylinder 16. The other end of this leaf spring has a sliding engagement with the member at 28. The normal tendency of the spring is to maintain the member 23 in the position shown in Fig. 5. This operates through the axle. the spur gear 19, the spur gear 20, and the axle 21 to maintain the valve 22 normally pressed. If when in its seat and closed, however, the member 23 is depressed by any force against the action of the leaf spring the valve will be opened as shown in Fig. 4. In the fuel tank 56 of the receiving aircraft there is an opening 31 connected with a pipe 32 which bends at right angles as shown in Fig. 7, and extends to a point without the body of the aircraft.

The receiving apparatus comprises an outer pipe 34 and an inner pipe 35. The inner pipe is flared at its mouth to provide a fluid joint between the mouths of the two pipes, and extends to a point near the base of the second pipe where it is supported by a web 37 in the outer pipe.

The two pipes are of such relative diameter as to provide an annular space, which,

from the drum and allowed to trail.

as will be readily seen, is in communication with pipe 32.-

Near the top edge of the outer pipe there are mounted lugs 38 which are adapted to act as pivot mountings for stays 39. Stays 39 co-act with a flexible or collapsible material 45 to form a collapsible funnel, Pivotally connected to these stays at a point 40 near their centers are ribs 41. The other ends of ribs 41 are pivotally connected to a ring 42. The outside pipe has a bearing portion 43 keyed to a sleeve 43 at 43 This sleeve is adapted to bear in a bearing 43 on which the whole receiver freely turns. The pipe 34 is adapted to communicate through this bearing with pipe 32. A handle 44 within the cockpit enables the pilot to turn the receiver from a position parallel to the aircraft body (its position in flight) to any desired position to engage the supply pipe of the tanker craft.

When it is desired to establish communication between the hose and the receiver, the

pilot turns the receiver at the desired angle, pushes outwardly on ring 42 to open his guiding funnel and maneuvers his craft so that the hose 15 enters the pipe 35. The pipe 35 is of such diameter that as the hose enters the pipe the member 23 will be pressed back against the action of the spring and the valve opened. The gasoline will then flow through the hose 15, pipe 35, pipe 34, bearing 43, pipe 32, and into the tank 6. Figure 1 is a disclosure of my device as will appear in operation, the two planes disclosed not being of the relative types to be used, but merely showing the means of fuel transfer. 47 is the supply craft and 49 the receiving craft. 50 is a showing of the entire receiver and 45 shows the funnel extended.

My device .having been described in detail, the operation will be seen to be as follows: When it is desired to effect a fuel transfer between the craft, the hose is first wou}nd '1 11's hose is of such heavy material that when filled with gasoline is quite rigid. Valve 3 is then opened permitting the fuel to drain from tank 2 and fill the hose, the valve 22, of course, being automatically held closed.

The pilot of the receiving craft then rotates the receiver into the approximate inclination of the hose, approaches the supply craft gradually from below until the end of the hose is just above the open mouth of the funnel driveway when he zooms slightly and the hose passes freely into the receiver, the automatic valve opening, and the fuel transfer taking place. The receiver pipe is of such considerable length to allow for some relative motion between the craft without any interruption to the flow of fuel. If, however, there is any excess relative motion between the craft such as would cause the .vent the escape of fuel;

hose to be withdrawn from the receiver, the valve will automatically close and thus pre- The receiver is mounted in bearin 43 at a point sufficiently near the center 0' its length to permit the pilot tofset it in the desired position in spite of the blast of air due to the motion of the craft therethrough.

When the recelvin the pilot will dive and the pilot of the supply craft will close valve 3, open relief valve 29,

' permitting the escape of the fuel in the hose and roll u the hose on the drum.

While t e.foregoing is given as one embodiment of my inventlon it should be understood that the same may be carried out in other ways within the scope of the appended claims: 1

What I claim is: 1. Means for providing for a fuel transfer of liquid from a supply aircraft to a re ceiving aircraft while 1n flight, comprising in combination, a hose depending from said connected withsaid hose.

supply aircraft, and a receiver on said receiving aircraft adapted to be operatively 2.4Means' for providing fbr a fuel transfer of liquid from a supply aircraft to a receiving aircraft while in flight, comprising in combination, a ose depending from said supply aircraft, a receiver on said receiving aircraft adapted to receive said hose, and means for guiding said hose into said receiver. I

3. Means for providing for a fuel transfer of liquid from a supply aircraft to a receiving aircraft while in flight, com rising in combination, a hose depending rom said supply aircraft, a receiver on said receiving aircraft adapted to receive said hose, and collapsible means forguiding said hose into said receiver. a

4. Means for providing for a fuel transfer of liquid from a supply aircraft to a receiving aircraft while in flight, comprising in combination, a hose depending from said supply aircraft, a receiver on said receiving aircraft adapted to receive said hose, and collapsible means for guiding said hose into said receiver, said receiver being rotatably mounted for the purpose described.

5. Means for providing for a fuel transfer of, liquid from a supply aircraft to a receiving aircraft while in flight, comprising in combination, a hose depending from said supply aircraft, a receiver on said receiving aircraft adapted to receive said hose, and.

collapsible means for guidingsaid hose into said receiver, said receiver being rotatably mounted for the purpose described, said receiver being adapted to permit aconsiderable degree of relative motion between the two aforesaid aircraft.

6. 'Means for providing for a fuel transfer of liquid from a supply aircraft to a. receiving aircraft while in flight, comprising in combination, a hose depending from said supply aircraft, and a receiver on said receiving aircraft adapted to receive said hose, means on the depending end of said hose for preventing the escape of liquid from the hose when the hose is out of engagement with said receiver. craft has been fueled,

7. Means for providing for a fuel transfer of liquid from a supply aircraft to a receiving aircraft while in flight, comprising in combination, a hose depending from said supply aircraft, and a receiver on said receiving aircraft adapted to receive said hose,

means on the depending end of said hose for preventing the escape of liquid from the hose when the hose is out of engagement with said receiver, said means automatically providing for the escape of liquid from the hose into the receiver when the hose and receiver are in engagement.

- 8. Means for providing for a fuel transfer of liquid from a supply aircraft to a receiving aircraft while in flight, comprising in combination, a hose depending from said supply aircraft, and a receiver on said receiving aircraft adapted to receive said hose, means on the depending end of said hose for preventing the escape of liquid from the hose when the hose is out of engagement with said receiver, said means automatically providing for the esca e of liquid from the hose into the receiver w en the hose and receiver are in engagement, and means for guiding said hose into said receiver.

- 9. Means for providing for a fuel transferon the depending end of said hose for pre ventin the escape of liquid from the hose when t e hose is out of engagement with said receiver, said means automatically providing for the escape of liquid from the hose into the receiver when the hose and receiver are in enga ement, means for guiding said hose into sald receiver, and a relief valve for permitting the escape of gasoline from the hose when desired.

10. Means for supplying "fuel from a supply aircraft to a second aircraft while in flight, comprising a hose depending from said supply aircraft, said hose being supplied with a valve at its depending end for automatically preventing the escape of fuel from said hose exce t when the. desired fuel transfer is taking p ace.

11. An apparatus for operatively connect- 'ing two aeroplanes when in flight for-the transfer ,of liquid fuel from one plane tothe other, said apparatus comprising a tubular member through which the liquid fuel is adaptedto pass.

12. Means for providing for the transfer of liquid fuel from a supply aircraft to a receiving aircraft while in flight comprising, in combination, a hose depending from the supply aircraft, and a receiver on said receiving aircraft adapted to be operatively connected with said hose. i

13. Means for providing for the transfer of liquid fuel from a supply aircraft to a receiving aircraft While in flight comprising, in combination, a hose depending from said supply aircraft, a receiver on said receiving aircraft adapted to be operatively connected with said hose, and guiding means to facilitate such connection.

14. Means for providing for the transfer of liquid fuel from a supply aircraft to a receiving aircraft while in flight comprising,

in combination, a hose depending from said.

supply aircraft, a receiver on said receiving aircraft adapted to be operatively connected With said hose, and means on the depending end of said hose for preventing the escape of liquid from the hose when it is out of engagement with said receiver, said means being automatically actuated to allow the liquid to flow from the hose into the receiver when they are operatively connected.

In testimony whereof I have afiixed my signature.

ALEXANDER PROCOFlEFF-SEVERSKY.