Hose type aerial refueling equipment

Abstract

The utility model discloses a hose type aerial refueling device which comprises a refueling hose, an oil supply taper sleeve and an umbrella cover, the refueling hose is connected with the rear end of the oil supply taper sleeve, an oil outlet is formed in the front end of the oil supply taper sleeve, and the umbrella cover is installed on the oil supply taper sleeve and arranged in the circumferential direction of the oil supply taper sleeve. The oil supply device is characterized by further comprising a pressurization module used for increasing the oil conveying speed, the pressurization module comprises a stator, a rotor and blades, the stator is fixed in the oil supply taper sleeve, the rotor is tubular and is rotationally matched in the stator, and the oil filling hose is communicated with an oil outlet in the front end of the oil supply taper sleeve through an inner cavity of the rotor. The blades are arranged in the rotor and rotate along with the rotor, and the stator is provided with an electric drive winding used for driving the rotor to rotate and a power supply assembly used for providing electric energy. The utility model provides hose type aerial refueling equipment which can increase the oil transportation speed in a refueling hose on the basis of not changing the body structure of a refueling machine.

Description

Technical Field

[0001] The utility model relates to the technical field of plug-cone-sleeve type refueling systems, in particular to a hose type aerial refueling device. Background Art

[0002] Existing aerial refueling technologies are primarily divided into rigid-hose and hose-type refueling (also known as plug-and-drum refueling). Hose-type refueling offers advantages over rigid-hose refueling: a single large tanker can be equipped with multiple refueling systems, allowing simultaneous refueling of multiple aircraft. The use of flexible hoses provides enhanced safety due to the relative motion between the tanker and receiving aircraft. However, its disadvantages include sensitivity to atmospheric turbulence, difficulty in docking, and high pilot skill requirements. Furthermore, the refueling rate is slow, at approximately 1,500 liters per minute, making refueling large aircraft time-consuming.

[0003] To address the difficulty of docking hose-type aerial refueling systems, industry experts have addressed this issue by adding various attitude adjustment devices to the drogue to facilitate the docking process. For example, patent applications with publication numbers CN115871941A, CN111216907A, and CN114590413A all propose various solutions to facilitate the docking process. However, due to limitations in the tanker's fuselage design, there is no effective solution in the prior art to increase the fuel delivery speed without modifying the tanker's fuselage structure. Utility Model Content

[0004] The present invention aims to solve one of the technical problems in the related art to a certain extent at least: to provide a hose-type aerial refueling device, which can increase the oil delivery speed in the refueling hose without changing the structure of the refueling machine body.

[0005] To this end, one object of the present invention is to provide a hose-type aerial refueling system comprising a refueling hose, a refueling drogue, and a parachute. The refueling hose is connected to the rear end of the refueling drogue, and the front end of the refueling drogue has an oil outlet. The parachute is mounted on the refueling drogue and arranged circumferentially around the refueling drogue. The system is characterized by further comprising a booster module for increasing the oil delivery rate. The booster module comprises a stator, a rotor, and blades. The stator is fixed within the refueling drogue, and the rotor is tubular and rotatably engaged within the stator. The refueling hose communicates with the oil outlet at the front end of the refueling drogue through the rotor's inner cavity. The blades are arranged within the rotor and rotate with the rotor. The stator is provided with an electric drive winding for driving the rotor and a power supply assembly for providing electrical energy. The booster module, which is built into the refueling drogue and driven by the rotor, increases the flow rate of oil passing through the rotor's inner cavity, thereby ultimately increasing the flow rate of oil output from the oil outlet. Moreover, the boost module is integrated in the oil cone sleeve, and can serve as a partial counterweight of the oil cone sleeve, while not occupying any additional installation space in the oil cone sleeve. In addition, since the oil passes directly through the rotor cavity, it has a better cooling and heat dissipation effect on the entire boost module.

[0006] According to one embodiment of the present invention, the blades are spiral blades extending axially and rotating circumferentially along a helical line. Using spiral blades instead of conventional blades allows the oil to remain in contact with the spiral blades for a longer time and over a larger contact area within the rotor cavity. Consequently, at the same rotational speed, the spiral blades can provide greater water flow driving force than conventional blades.

[0007] According to an example of the present invention, the number of spiral coils of the spiral blade is not less than one.

[0008] According to an example of the present invention, the outer edge of the spiral blade is fixedly connected to the inner side wall of the rotor.

[0009] According to an example of the present invention, the spiral blade has a central shaft extending along its own central axis, and the central shaft is fixedly connected to the rotor via a connecting rod.

[0010] According to an example of the present invention, a guide cone is provided at the end of the central axis.

[0011] According to an example of the present invention, the outer edge of the spiral blade is in contact with the inner wall of the rotor.

[0012] According to an example of the present invention, a plurality of rotors are rotatably coupled within the stator, the rotors are arranged in sequence along the axial direction, and electric drive windings are provided at positions corresponding to the rotors within the stator. At least two of the rotors rotate in opposite directions, and the spiral blades within the two rotors with opposite rotation directions have opposite rotation directions.

[0013] According to an example of the present invention, two rotors are provided in the stator, and a fixed block is provided between the two rotors. The fixed block has an intermediate flow channel axially passing through both ends of the fixed block. The intermediate flow channel is spiral near the two ends, and the rotation direction of the spiral channel at the end of the intermediate flow channel is the same as the rotation direction of the spiral blade in the corresponding rotor.

[0014] The above technical solution has the following advantages or beneficial effects: First, the boost module in the oil delivery cone sleeve directly applies driving force to the oil, thereby increasing the oil delivery speed; second, the boost module is built into the oil delivery cone sleeve, and its own weight can serve as a counterweight for the oil delivery cone sleeve, making the entire cone sleeve more stable in the air; second, the rotor is tubular, and the two ends of the rotor are directly connected to the refueling hose and the oil outlet, so the torque of the rotor to drive the spiral blade to rotate is large; second, the use of spiral blades instead of conventional blades makes the oil in the rotor cavity contact with the spiral blade for a longer time and a larger contact area, so that at the same speed, the spiral blade can provide a greater water flow driving force than the conventional blade; finally, the use of two rotors with opposite rotation directions allows the torsional forces generated by the two rotors to offset each other, thereby reducing the situation where the entire cone sleeve is twisted by the torsional force of the rotor rotation during the aerial refueling process.

[0015] Additional aspects and advantages of the present invention will be given in part in the following description and will become apparent from the following description or learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of the hose-type aerial refueling equipment of the present utility model.

[0017] Figure 2 It is a structural schematic diagram of the boost module of the present invention.

[0018] Figure 3 This is a schematic diagram of the internal structure of the rotor in the boost module.

[0019] Figure 4 for Figure 3 Axonometric diagram of .

[0020] Figure 5 This is a schematic diagram of the internal structure of the rotor with the central axis in the boost module.

[0021] Figure 6 for Figure 5 Axonometric diagram of .

[0022] Figure 7 It is a schematic diagram of the internal structure of the stator with two rotors in the utility model.

[0023] Figure 8 yes Figure 7 Schematic diagram of the structure with a fixed block between the two rotors.

[0024] Among them, 100, refueling hose; 200, oil cone sleeve; 201, oil outlet; 300, umbrella sleeve; 400, boost module; 1, stator; 2, rotor; 3, blades; 4, electric drive winding; 5, power supply component; 6, center axis; 7, connecting rod; 8, guide cone; 9, fixing block; 10, spiral channel. DETAILED DESCRIPTION

[0025] The following describes in detail embodiments of the present invention, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0026] The hose-type aerial refueling equipment according to an embodiment of the present invention will be described in detail below with reference to the accompanying drawings.

[0027] The utility model provides a hose-type aerial refueling equipment, as shown in the figure, which includes a refueling hose 100, a refueling drogue 200 and an umbrella cover 300. The refueling hose 100 is connected to the rear end of the refueling drogue 200, and the front end of the refueling drogue 200 has an oil outlet 201. The umbrella cover 300 is installed on the refueling drogue 200 and arranged along the circumference of the refueling drogue 200. It is characterized in that it also includes a booster module 400 for increasing the oil delivery speed. The booster module 400 includes a stator 1, a rotor 2 and blades 3. The stator 1 is fixed in the refueling drogue 200, and the rotor 2 is tubular and rotatably fitted in the stator 1. The refueling hose 100 is connected to the oil outlet 201 at the front end of the refueling drogue 200 through the inner cavity of the rotor 2. The blades 3 are arranged in the rotor 2 and rotate with the rotor 2. The stator 1 is provided with an electric drive winding 4 for driving the rotor 2 to rotate and a power supply component 5 for providing electric energy.

[0028] In this embodiment, the other end of the refueling hose 100 is connected to a refueling machine, and the refueling machine is provided with a hose reel for reeling in or unreeling the refueling hose 100. The refueling machine is provided with a plug that matches the refueling drogue 200, which is a conventional component of existing hose-type aerial refueling. The oil outlet 201 is provided with a valve component for opening and closing the oil outlet 201. It should be understood that the refueling drogue 200 is also provided with a servo. After the rudder blades on the servo are deployed, the movement posture of the refueling drogue 200 in the air can be adjusted by swinging the rudder blades. The servo is a control component in existing hose-type aerial refueling equipment that changes the posture of the drogue so that the drogue and the plug on the refueling machine are more accurately connected. The structure of this servo is conventional technology in this field, so the structure of the servo is not described in detail.

[0029] In this embodiment, the boost module 400 is integrated into the fuel drogue 200, thus occupying no additional installation space and not changing the outer contour of the existing fuel drogue 200, thus having no impact on the overall aerodynamic layout. Furthermore, since the weight of the boost module 400 can be used as a counterweight for the fuel drogue 200 itself, the required counterweight for the fuel drogue 200 itself is eliminated, with no impact on the overall weight.

[0030] Specifically, the rotor 2 and stator 1 are circumferentially rotatable and axially constrained. The refueling hose 100 is connected to a connection on one end of the rotor 2, or alternatively, to a connection on a taper sleeve 200. The taper sleeve 200 contains a pipeline connecting the connection and the rotor. In this embodiment, sealing rings are used at the connection points of the refueling hose 100 during the process of transferring oil from the refueling hose 100 to the oil outlet to minimize oil leakage.

[0031] The electric drive winding 4 in the above embodiment refers to a component that generates a driving magnetic field when energized, thereby driving the rotor to rotate. This is a conventional component in the field of electric motors. The electric drive winding 4 includes a stator electric drive winding 4 wound around the stator 1 and a rotor electric drive winding 4 wound around the rotor 2. Furthermore, the power supply assembly 5 includes, but is not limited to, a power cord, which is electrically connected to the electric drive winding 4 on the stator. The other end of the power cord extends through the installation space within the fueling cone 200, along the refueling hose 100, and is electrically connected to the power supply on the fuel dispenser.

[0032] Based on the preference of the above embodiment, the blade 3 is a spiral blade extending in the axial direction and extending along a spiral line rotating in the circumferential direction.

[0033] Specifically, the spiral blade has at least one spiral coil, which is defined as one coil from a starting point, rotating 360° in the circumferential direction and returning to the starting point. The lead is the distance of the spiral line in the axial direction during one coil, and multiple coils are formed as the spiral line continues to extend.

[0034] One of the preferred examples based on the spiral blade: Figure 2-4 As shown, the outer edge of the spiral blade is fixedly connected to the inner wall of the rotor 2. As a result, when the spiral blade rotates, the oil in the rotor 2 can move axially under the push of the spiral blade 3. Preferably, the projection of the spiral blade 3 in cross section is annular.

[0035] Based on the second preferred example of the spiral blade: the spiral blade has a central shaft 6 extending along its own central axis, and the central shaft 6 is fixedly connected to the rotor 2 via a connecting rod 7.

[0036] The end of the central shaft 6 is provided with a guide cone 8. The addition of the guide cone 8 improves the axial fluidity of the oil and improves the vortex condition.

[0037] The outer edge of the spiral blade is in contact with the inner wall of the rotor 2 .

[0038] The rotor 2 in the boost module in the above embodiment will inevitably cause the boost module and the entire oil cone sleeve 200 to have a circumferential rotational torsional force during the rotation process. This torsional force poses a risk of causing the refueling hose to twist, and the oil cone sleeve 200 will be subjected to additional torsional force in the air, which will cause difficulties for the servo to adjust the posture of the entire oil cone sleeve 200, and ultimately affect the docking of the cone sleeve and the plug on the oiler, making the docking process difficult. To address this problem, the present embodiment is further improved in that: a plurality of rotors 2 are rotatably matched in the stator 1, and each rotor 2 is arranged in sequence along the axial direction, and an electric drive winding 4 is provided at the position corresponding to each rotor 2 in the stator 1, and at least two rotors 2 in each rotor 2 rotate in opposite directions, and the spiral blades in the two rotors 2 with opposite rotation directions have opposite rotation directions. Specifically, as Figure 7 As shown, two rotors 2 are provided in the stator 1. The two rotors 2 are arranged in sequence along the axial direction, and a positioning bearing is provided between the two rotors 2. Electric drive windings 4 are respectively provided at positions corresponding to the two rotors 2 on the stator 1. The two electric drive windings 4 are used to drive the corresponding rotors 2 to rotate. The two electric drive windings 4 are arranged so that when one rotor 2 rotates forward, the other rotor 2 rotates reversely. Thus, the torsional forces generated by the rotation of the rotors 2 are offset by the opposite rotation directions of the two rotors 2. In this embodiment, it is only necessary to make the circuit directions of the two electric drive windings 4 opposite to each other to generate opposite magnetic fields, thereby achieving the purpose of opposite rotation directions of the rotors 2. This is a very common existing technology in the field of motors. Therefore, in this embodiment, the circuit connection relationship of the two electric drive windings 4 will not be elaborated one by one.

[0039] In the above embodiment, two rotors 2 of the same structure are simultaneously arranged in a stator 1, and the two rotors 2 rotate in opposite directions at the same time, so that the two rotors can offset each other's torsional forces generated by the rotation of the rotors while conveying oil. However, since the two rotors 2 rotate in opposite directions, although the spiral blades 3 in the two rotors 2 are designed with opposite rotation directions so that the axial flow directions of the oil in the two rotors 2 are consistent, the rotation directions of the oil in the two rotors are different. Therefore, eddy currents are easily generated at the junction of the two rotors 2, thereby reducing the axial conveying efficiency of the oil. For this reason, the present embodiment is further improved in that: Figure 8 As shown, two rotors 2 are provided in the stator 1, and a fixed block 9 is provided between the two rotors 2. The fixed block 9 has an intermediate flow channel axially passing through both ends of the fixed block 9. The intermediate flow channel is spiral near both ends, and the rotation direction of the spiral channel 10 at the end of the intermediate flow channel is the same as the rotation direction of the spiral blades in the corresponding rotor 2. That is, the intermediate flow channel is composed of a left half flow channel and a right half flow channel. The left half flow channel and the right half flow channel intersect in the fixed block 9 and are connected to each other. The spiral rotation direction of the spiral channel 10 at the left end of the left half flow channel is the same as the rotation direction of the spiral blades in the left rotor, and the spiral rotation direction of the spiral channel 10 at the right end of the right half flow channel is the same as the rotation direction of the spiral blades 3 in the right rotor 2. The junction of the left half flow channel and the right half flow channel is set to be a smooth transition, so that the oil flows from Figure 8 In the process of the left rotor 2 being driven by the left spiral blade 3 to flow to the right, since the rotation direction of the oil is the same as that of the left half of the flow channel, the fluid can smoothly enter the left half of the flow channel, and the junction of the left half of the flow channel and the right half of the flow channel has a smooth transition, thereby reducing the energy loss of the oil when entering the right half of the flow channel from the left half of the flow channel. Finally, the oil flows out from the right half of the flow channel and enters the right rotor 2. Since the rotation direction of the right spiral blade 3 is also the same as that of the right half of the flow channel, the oil can smoothly enter the right rotor 3 from the right half of the flow channel. Finally, the vortex generated by the change in the rotation direction of the oil is small during the whole process, thereby minimizing the kinetic energy loss of the oil flow.

[0040] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are illustrative and cannot be understood as limitations on the present invention. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present invention.

[0041] Various changes and modifications will undoubtedly become apparent to those skilled in the art after reading the above description. Therefore, the appended claims should be construed to encompass all changes and modifications within the true intent and scope of the present invention. Any and all equivalents within the scope of the claims should be considered to be within the intent and scope of the present invention.

Claims

1. A hose-type aerial refueling device, comprising a refueling hose (100), a refueling drogue (200) and an umbrella cover (300), wherein the refueling hose (100) is connected to the rear end of the refueling drogue (200), the front end of the refueling drogue (200) is provided with an oil outlet (201), and the umbrella cover (300) is mounted on the refueling drogue (200) and arranged along the circumference of the refueling drogue (200), characterized in that: The invention also includes a boosting module (400) for increasing the oil delivery speed. The boosting module (400) includes a stator (1), a rotor (2) and blades (3). The stator (1) is fixed in an oil delivery cone sleeve (200). The rotor (2) is tubular and rotatably fitted in the stator (1). The oiling hose (100) is connected to the oil outlet (201) at the front end of the oil delivery cone sleeve (200) through the inner cavity of the rotor (2). The blades (3) are arranged in the rotor (2) and rotate with the rotor (2). The stator (1) is provided with an electric drive winding (4) for driving the rotor (2) to rotate and a power supply component (5) for providing electric energy.

2. The hose-type aerial refueling equipment according to claim 1, characterized in that: The blade (3) is a spiral blade that extends in the axial direction and extends along a spiral line that rotates in the circumferential direction.

3. The hose-type aerial refueling equipment according to claim 2, characterized in that: The number of spiral coils of the spiral blade is not less than one.

4. The hose-type aerial refueling equipment according to claim 2, characterized in that: The outer edge of the spiral blade is fixedly connected to the inner side wall of the rotor (2).

5. The hose-type aerial refueling equipment according to claim 2, characterized in that: The spiral blade has a central shaft (6) extending along its central axis, and the central shaft (6) is fixedly connected to the rotor (2) via a connecting rod (7).

6. The hose-type aerial refueling equipment according to claim 5, characterized in that: A guide cone (8) is provided at the end of the central shaft (6).

7. The hose-type aerial refueling equipment according to claim 5, characterized in that: The outer edge of the spiral blade is in contact with the inner wall of the rotor (2).

8. The hose-type aerial refueling equipment according to any one of claims 2 to 7, characterized in that: A plurality of rotors (2) are rotatably coupled within the stator (1), the rotors (2) being arranged in sequence along the axial direction, and electric drive windings (4) are provided at positions corresponding to the rotors (2) within the stator (1), at least two of the rotors (2) rotate in opposite directions, and the spiral blades within the two rotors (2) rotating in opposite directions rotate in opposite directions.

9. The hose-type aerial refueling equipment according to claim 8, characterized in that: Two rotors (2) are provided in the stator (1), a fixed block (9) is provided between the two rotors (2), and an intermediate flow channel is provided in the fixed block (9) and axially penetrates the two ends of the fixed block (9). The intermediate flow channel is spiral near the two ends, and the rotation direction of the spiral channel (10) at the end of the intermediate flow channel is the same as the rotation direction of the spiral blade in the corresponding rotor (2).

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