KR100274500B1 - Air refueling system for aircraft with telescopic refueling probe - Google Patents

Abstract

The refueling tank has a telescopic refueling probe formed of a plurality of telescoping tubes capable of extending and retracting from a pylon mounted on a dropable external fuel tank of the aircraft wing. Telescopic drive is achieved by a drive mechanism comprising a motor and a screw jack mechanism operable to extend and retract a telescoping tube in which another tube is slidably mounted on one tube. When fully retracted, the probe is fully introduced into the combined fuel tank assembly so that no additional drag or lift is generated on the aircraft and the probe remains hidden.

Description

Air refueling system for aircraft with telescopic refueling probe

The present invention relates to an aerial refueling tank having a telescoping refueling system, and more particularly to an apparatus installed in a wing pylon mounted to a fuel tank for use in aerial refueling of an aircraft.

Air refueling systems for aircrafts have been in use for many years. Such systems are generally known as "hose reel and drogue systems". The system is disclosed in U.S. Patent Application No. 3,100,614, filed on 1963.8.13 by Murrow, U.S. Patent Application No. 3,061,246, filed on October 30, 1962 by Kirby, U.S. Application No. 4,633,376, filed December 30, 1986 by Newman. U.S. Patent Application No. 4,095,761, filed on June 22, 1978 by Anderson, U.S. Patent Application No. 4,540,144, filed on 1985.9.10 by Perella, and U.S. Patent Application No. 740,344, filed at 1954.4.27 by Boeing. Known in

In all of the above systems except Perella's patent application, the aerial refueling probe of the refueling aircraft is in a state where the fixed unit protrudes from the fuel tank of the aircraft. In the case of a perella, telescoping fuel probes are known which are driven by fuel pressure. This unit is relatively short and retracts into a housing mounted on the aircraft fuselage. The oil supply nozzle protrudes from the housing in the position where the probe is fully retracted.

In prior art systems, all or major portions of the refueling probe or probe housing are always extended to airflow, not just at refueling. This adds unexpected drag or lift to the aircraft. In addition, the visible unit can be immediately exposed to unfriendly aviation patrol officers whose aircraft's extensive capabilities may be a disadvantage in military strategy.

In addition, in many conventional air refueling systems, it is difficult for the pilot to observe the refueling probe conveniently during refueling operations. Of course, this makes the coupling of the probe and drogue difficult and may require the assistance of other crew members. In a fighter with only one pilot, it is important for the pilot to watch the probe carefully to facilitate the coupling of the drog to the probe.

The system of the present invention can extend sufficiently at an appropriate angle to be easily observed by the pilot when refueling, and can be fully retracted into the fuel tank pylon to prevent lift or drag from occurring on the aircraft, and It provides a telescoping probe that cannot be observed at the time, which is a clear improvement over conventional air refueling systems.

The system of the present invention uses a plurality of telescoping tube members, the innermost tube of which has a fuel nozzle on its distal end. The telescoping member is driven between the extended and retracted positions by an electric or air motor. The telescoping member in the retracted position is fully contained within the refueling pylon or other external fuel tank of the aircraft. A “dry” compartment is provided for the motor in the tank to isolate the motor from the fuel.

The probe nozzle of the innermost tube in the extended position extends sufficiently outward at an appropriate angle to the aircraft so that it can be easily observed by the pilot from the cockpit.

The rotational drive of the motor is converted to linear drive by an elongated screw jack that engages the nut member fixedly attached to the innermost tube so that the rotational movement of the motor linearly moves the innermost tube. Another extensible telescoping tube, which may be one, two or more, is driven linearly in accordance with the rotational drive of the motor by means of a second screw jack or sliding drive.

The telescoping tube is retracted into the fuel tank by reversing the linear motion of the tube by reversing the rotation of the motor.

It is therefore an object of the present invention to provide an improved air refueling system that utilizes probe and dlog type refueling coupling.

Another object of the present invention is to provide an air refueling system using telescoping tubes that can be fully retracted into an aircraft fuel tank.

Another object of the present invention is to provide an air refueling system in which the refueling probe can be easily observed by the pilot in the cockpit.

Other objects of the present invention will become apparent from the following description taken in conjunction with the accompanying drawings.

1 is a side view of a probe in an extended position.

2 is a partial cutaway side view showing a probe retracted into a fuel tank.

3 is a side view of the motor device.

4 is a cross-sectional view taken along the plane indicated by line 4-4 of FIG.

5 is a cross-sectional view taken along the plane indicated by line 5-5 of FIG.

FIG. 6 is a cross-sectional view taken along the plane indicated by lines 6-6 of FIG. 1 showing the operating states of the second screw jack and barrel nut.

FIG. 7 is a sectional view taken along the plane indicated by line 7-7 of FIG.

FIG. 8 is a sectional view taken along the plane indicated by line 8-8 of FIG.

9 is a partial cross-sectional front view showing the operation of the second screw jack.

Figure 9 (a) is a perspective view showing a T-shaped lug (1ug) used for the linear operation of the second screw jack.

FIG. 10 is a schematic diagram showing a shutoff valve used to shut off the supply of fuel when the wing's fuel tank is full and to transfer additional fuel to another tank.

11 is a partial cross-sectional side view showing details of the shutoff valve and the transfer valve.

12 (a) to 12 (c) are schematic diagrams showing the arrangement of probes for pilot observation.

FIG. 13 is a schematic diagram showing that the tube is adjacent to a retracted position in a mechanism for extending and retracting a telescoping tube. FIG.

FIG. 14 is a schematic diagram showing the mechanism of FIG. 13 showing that the tube is in an extended position. FIG.

* Explanation of symbols for main parts of the drawings

12: motor 14: house motor compartment

16: fuel tank 17: aircraft wing

18: middle tube 27: inner tube

28: probe nozzle 30: fixed tube

Referring to Figures 1 and 2, it is shown that the system of the present invention is extended and retracted, respectively. The fixed tube 30 is mounted and fixed on the outer wall of the compartment 14 in which the motor 12 is mounted. Compartment 14 mounted on the bottom wall of fuel tank 16 is waterproof to allow the motor to be isolated from the fuel in the tank and remain dry. The fuel tank 16 may be a pylon mounted on the bottom surface of the aircraft wing 17. In the retracted position as shown in FIG. 2, the intermediate tube 18 can be retracted into the outer stationary tube 30, and the inner tube 27 is retracted into the intermediate tube 18. The inner tube has a probe nozzle 28 on its distal end for engaging with a drog that supplies fuel into the tank 16.

Referring to FIG. 1, in order to be easily observed by the pilot when refueling, the probe 28 is external from the pylon at the proper horizontal distance “H”, the appropriate vertical distance “V” and the appropriate angle “A” for the particular aircraft. Must be extended to Optimal parameters must be determined experimentally for each installation. Parameters for the F-16 aircraft are “H” = 213.36 cm (84 in); “A” = 10 °; “V” = 86.36 cm (34 inches).

3 through 9 (a), a drive mechanism for driving the device between the retracted and extended positions of the tube is shown.

As shown in FIG. 3, a drive motor 12, which may be an electric or hydraulic motor, is installed in a waterproof or “dry” compartment 14 mounted to the bottom of the fuel tank 16. The drive shaft of the motor is fixedly attached to the threaded shaft or the screw jack 11a with the bolt 10. The screw jack 11a is substantially threaded along its entire length and, as shown in FIGS. 4 and 5, to the barrel nut member 15 fixedly attached to the first extension tube 18. Screwed together. The barrel nut assembly is prevented from rotating by frictional resistance to the rotation of the first extension tube 18, and the extension tube 18 is linearly driven in accordance with the rotation of the screw jack 11a.

As shown in Fig. 6, the tubular shaft 11b forming the second screw jack is concentric with the screw jack 11a. Like the first screw jack, the outer wall of the second screw jack is substantially threaded along its entire length. The second screw jack is screwed to the barrel nut 25 fixedly attached to the inner extension tube 27. As shown in Figs. 9 and 9 (a), the T-type driving lug 29 has an upper portion of the “T” shape which is fixedly attached to the inner wall of the second screw jack 11b. The first (inner) screw jack 11a has a groove 11c in which the bottom portion of the “T” type slides along the longitudinal extension. Thus, the rotary motion of the screw jack 11a is transmitted to the screw jack 11b, and the screw jack 11b slides along the screw jack 11a to provide linear and rotary motion of the screw jack 11b.

As described above, the second screw jack 11b is threadedly coupled to the barrel nut 25 which is fixedly attached to the inner extension tube 27. The tube 27 has a lubrication probe nozzle 28 on the distal end. Thus, the rotational movement of the screw jack 11b drives the tube 27 linearly. The stop member 32 (see FIGS. 6 and 8) extends from the inner wall of the tube 18 to limit the forward movement of the inner tube 27 relative to the intermediate tube.

Thus, the inner tube member 27 and the intermediate tube member 18 are driven linearly with respect to each other and with respect to the fixed tube member 30 to be in an extended position. The tube members are driven to a retracted position in the fuel tank by reversing the rotation of the motor.

Aircraft refueling system distribution, which is critical for stability at low refueling speeds, requires fuel distribution capability to internal and external fuel tanks. This is achieved pneumatically and is unaffected while using air refueling tanks. During refueling, fuel is transported to all internal tanks as in conventional vanes equipped with tanks. However, check valves 38 (see FIGS. 10 and 11) may be installed in the aircraft's fuel system to provide fuel flow to the external fuel tank (pylon) of the opposite wing. As shown in FIG. 11, the check valve 38 is a conventional three-way two-position solenoid operated valve. This replaces the one-way valve that was commonly used to allow external tanks to be refueled through conventional air refueling reservoirs. The three-way two-position valve allows refueling through the air refueling tank and the air refueling reservoir.

As shown in FIG. 10, a shutoff valve 19 is provided in the oil supply system. The valve opens during refueling to deliver fuel taken by the probe to both the inner and outer tanks. When the oil supply tank 16 is full, the tank level detector closes the valve 19 so that fuel is no longer supplied to the tank 16 but is transferred to other external and internal tanks. In addition, when all external and internal tanks are full and refueling is finished, the valve 19 opens to transfer the remaining fuel in the probe to the tank 16.

Referring to Figures 12 (a) through 12 (c), the position of the probe is shown for easy viewing by the pilot. As already explained with respect to Figure 1, the position of the probe determines the above contents. The position should be adjusted so that the pilot can observe the probe with the air tanker facing up. This is determined experimentally for several different aircraft types. These parameters are shown in Figures 12 (a) and 12 (b) for the F-16 aircraft, with the angles shown being the pilot's viewing angle from the cockpit.

An alternative embodiment of the probe of the invention is shown schematically in FIGS. 13 and 14.

The probe is driven from the retracted position to the extended position by the motor as in the first embodiment in accordance with the rotation of the motor which is converted to linear motion by a screw jack which engages a nut fixed to one or more tubes. This embodiment has different means than the first embodiment for the drive mechanism used for driving the intermediate tube and for driving between the first and second screw jacks. The same numerals are used to indicate the same parts of the second embodiment and the first embodiment. FIG. 13 shows the probe in a nearly fully retracted position, while FIG. 14 shows the probe in an extended position.

The screw jack 11a is fixedly attached to the drive shaft of the electric or air motor 12. The screw jack 11a is substantially threaded along its entire length. The circular ring 40 is fixedly attached to the distal end of the screw jack 11a and has an engagement portion or dog teeth 41 on its surface. The screw jack 11b is hollow and concentrically outward with respect to the screw jack 11a. The lid 44 located at one end of the screw jack 11b has a thread 43 on the inner surface of the screw jack 11b for engaging with the threaded outer surface of the screw jack 11a. The distal end of the screw jack 11b is supported on the inner wall of the inner tube 27 by the slide bearing 46. The lid 44 is supported on the circular ring 50 by the ball bearing 48. The circular end plate 58 of the screw jack 11b has an engagement portion or dog teeth 79. Fuel holes are provided in the ring 50 and slide bearing assembly to allow fuel to pass there through.

The inner tube 27 has a circular ring 52 fixedly attached thereto and has a threaded portion 53 that engages with a thread on the outer surface of the screw jack 11b. The probe nozzle 28 is located on the distal end of the tube 27. The intermediate tube 18 has a keyway 57 extending longitudinally along the inner wall of the intermediate tube in which the ring member 60 on the outer wall of the inner tube 27 is fitted while preventing rotation of the inner tube. . The fixed outer tube 30 has a key groove 62 similar to the key groove so that the ring member 64 of the intermediate tube 18 travels while preventing the rotation of the intermediate tube. The slide bearing 70 and the fuel seal 72 are provided between the outer tube 30 and the intermediate tube 18 and between the intermediate tube 18 and the inner tube 27, the bearing and the seal being of the outer tube. And on the inner surface of the circular ring 74 extending from the intermediate tube. The holes are provided in all ring and bearing assemblies in the inner tube 27 to allow fuel to pass through there.

The apparatus of the second embodiment of the present invention operates as follows. In the fully retracted position (moved in the extension direction as nearly as fully retracted as shown in FIG. 13), the dog teeth 59a on the screw jack 11a are opposite the dog teeth 59b on the screw jack 11b. And screw the two screw jacks together effectively. The screw portion 53 of the tube 27 engages with the thread on the outer wall of the screw jack 11b. The two screw jacks rotate with the tube 27 driven through the female threaded portion 53 which engages with the threaded outer wall of the screw jack 11b. As already explained, the inner tube 27 is prevented from rotating by the engagement of the ring member 60 in the keyway 57. Therefore, the inner tube 27 is driven linearly. When the inner tube 27 extends far enough, the ring member 60 engages the opposite ring 74a. The intermediate tube 18 is connected to the screw jack 11b by the ball bearing 48 which rotates the screw jack 11b in the state in which rotation by the key groove 57 is prevented. The intermediate tube 18 extends outward as shown in FIG. 14 until its ring member 64 abuts against the ring member 74b opposite the outer tube 30 at the point where the probe is fully extended.

The probe is retracted by reversing the direction of rotation of the motor. This causes the rotation of the inner screw jack 11a in the opposite direction. The frictional force prevents rotation of the external screw jack 11b, thereby linearly contracting the external screw jack. As with the retraction, the external screw jack drives the intermediate tube with keyway to the rear. When the outer screw jack 11b is fully retracted, the joining teeth on the outer and inner screw jacks are driven together in the form of the joining portion. This rotates the outer screw jack 11b which drives the threaded portion 53 of the inner tube. Since the inner tube has a ring 60 that fits into the keyway 57, the inner tube moves linearly inward until it is prevented from rotation and reaches a fully retracted position.

While the invention has been described and illustrated in detail, it should be clearly understood that the description and examples claimed in the invention are not to be taken in a limiting sense, the scope of the invention being limited by the following claims.

The system of the present invention can be fully extended at an appropriate angle to be easily observed by the pilot when refueling and can be fully retracted into the fuel tank pylon to avoid generating lift or drag on the aircraft and observed when not refueling. The provision of a telescoping probe which cannot be achieved is a clear improvement over the prior art of air refueling systems.

Claims (15)

A fuel tank mounted on an aircraft body having a first compartment for fuel transport and a second compartment isolated from the first compartment in a waterproof state, a motor mounted in the second compartment, and connected to a drive shaft of the motor by a motor; An elongate shaft that is rotationally driven, a fixed tube member, a plurality of movable tube members mounted concentrically in the fixed tube member for a predetermined limited sliding motion therebetween, and for connecting the movable tube member to each other. Means for connecting said elongate shaft to one of said tube members for driving one of said tube members, and means for preventing rotational movement of one of said tube members during linear movement by driving said shaft. One of said tube members having a probe nozzle formed on its distal end; Telescopic lubrication for driving the tube member between an extended position in which the tube member extends completely out of the fuel tank such that all the tube members are in a retracted position contained in the fuel tank and the probe nozzle receives fuel. Air refueling system for aircraft with probes. The aerial refueling system of claim 1, wherein the one of the tube members is a tube member located at the innermost of the tube members. The aerial refueling system of claim 1, wherein the fuel tank is a pylon mounted on the wing of the aircraft. 2. The apparatus of claim 1, wherein the elongate shaft is means threaded along its entire length to form a screw jack and fixedly attached to the one of the tube members screwed with the screw jack, wherein the one of the tube members. An air refueling system for an aircraft having a telescopic refueling probe that is means for preventing the rotation of the tube member to linearly move the one of the tube members. 5. The tube of claim 4, wherein the other one of the tube members has a means attached to the other of the tube members for screwing a screw jack formed by the elongate shaft and preventing rotation of the other of the tube members. And the screw jack has a means for linearly driving the other of the tube members. The aerial refueling system of claim 1 wherein the probe in an extended position has a telescopic refueling probe extending outward from the fuel tank at an angle and distance that allows the probe nozzle to be viewed from the aircraft cockpit. The aerial refueling system of claim 1, wherein the other one of the plurality of tube members is driven by the drive shaft and is a means for preventing and linearly rotating a rotational movement of the other of the tube members. The air refueling system of claim 1, wherein the other one of the plurality of tube members has a telescopic refueling probe that is linearly towed by the one of the tube members. A fuel tank mounted on an aircraft, a fixed outer tube, an inner movable tube having a probe nozzle at its distal end to receive fuel, a barrel nut fixedly attached to the inner tube, and located between the inner tube and the outer tube An intermediate movable tube concentric with the tubes, the inner shaft being threaded along a longitudinal extension to form a screw jack and threadably engaged with the barrel nut of the intermediate tube, wherein An outer hollow shaft threadedly coupled to the barrel nut located concentrically with the inner shaft and attached to the inner tube, a watertight compartment in the tank, a motor mounted in the compartment, to generate rotation The inner shaft during longitudinal movement of the drive shaft of the motor connected to the inner shaft and the outer shaft along the inner shaft; Means for connecting said inner and outer shafts so that rotational drive of said outer shaft is caused by a shaft, said inner shaft engaging a barrel nut of one of said movable tubes and said outer axis being a barrel of the other of said movable tubes. Engaging the nut, the outer wall of the outer shaft being threaded to form a screw jack, the motor driving the shaft, the shaft forming a retracted position where the tube and shaft are fully retracted into the tank and the tube forming a probe An air refueling system for an aircraft having a telescopic refueling probe for driving the tube between extended positions extending out of the tank. 10. The air refueling system of claim 9, wherein the outer shaft engages the barrel nut of the inner tube and the inner shaft engages the barrel nut of the intermediate tube. 10. The apparatus of claim 9, wherein the means for connecting the inner shaft and the outer shaft so that rotational drive of the outer shaft occurs comprises a drive lug fixedly attached to the outer shaft, the inner shaft extending longitudinally along the inner shaft. An aerial refueling system having a telescopic refueling probe having a groove, wherein the lug is slidably fitted in the groove to linearly move and rotate the outer tube along the inner tube. 10. The air refueling system of claim 9, wherein the probe in the extended position has a telescopic refueling probe extending outward from the fuel tank at an angle and distance that allows the probe nozzle to be viewed from the aircraft cockpit. A fuel tank mounted to the aircraft, a fixed outer tube, an inner movable tube concentric with the outer tube and having a probe nozzle at the distal end to receive fuel, and located between the inner and outer tubes and the inner and outer An intermediate movable tube concentric with the tube, an inner shaft threaded to form a screw jack, an outer hollow shaft fitted around the inner shaft and concentric with the inner shaft, the inner shaft and the outer shaft being threaded And a motor mounted in the compartment having a screw means of the outer hollow shaft for coupling to the inner shaft, a waterproof compartment in the tank, a drive shaft connected to the inner shaft to generate rotation, and the inner shaft of the outer shaft. Means for connecting said inner and outer shafts to produce a rotational drive, and a circuit between said inner and intermediate tubes Means for connecting the inner tube to the intermediate tube to prevent pre-movement and to linearly move the inner tube and the intermediate tube relative to each other, and to prevent rotational movement between the intermediate tube and the outer tube and to the outer tube Means for connecting said intermediate tube to said outer tube for linearly moving said intermediate tube, said inner tube engaging each other when said inner tube is linearly driven such that said inner tube pulls said intermediate tube linearly; and A stop and drive means for engagement on the intermediate tube and stop means on the intermediate tube and an outer tube that engage with each other to stop forward movement of the intermediate tube, the motor driving the shaft, the shaft into the tank. Opened to the outside of the tank to form a fully retracted retraction position and fuel probe Aerial refueling system of an aircraft having a telescopic refueling probe for driving the tube between the extended position. 14. The apparatus of claim 13, wherein said means for connecting said inner tube to said intermediate tube that drives to prevent and linearly rotate a rotational movement between said inner tube and said intermediate tube comprises: a ring member on said inner tube and said ring member; An air refueling system for an aircraft having a telescopic refueling probe comprising a slot on the intermediate tube that is fitted. 15. The device of claim 14, wherein said means for connecting said intermediate tube to said outer tube to prevent and linearly rotate a rotational movement between said intermediate tube and said outer tube is fitted to said keyway and said keyway on said outer tube member. An air refueling system for an aircraft having a telescopic refueling probe comprising a ring on the intermediate tube member.