A telescopic three-section electric helicopter air refueling device

Abstract

The application provides a telescopic three-section electric helicopter air refueling device, which comprises a first pipe 12, a second pipe 11, a third pipe 18, a sealing ring 8, a first control box 9, a second control box 17, an initial cable 10 and a relay cable 1, wherein the first pipe 12, the second pipe 11 and the third pipe 18 realize telescopic function through the sleeving mode, fuel flows in the first pipe 12, the second pipe 11 and the third pipe 18, the first pipe 12, the second pipe 11 and the third pipe 18 are coaxial, the first pipe 12 sleeves the second pipe 11, and the second pipe 11 sleeves the third pipe 18; the first pipe 12 is fixedly connected with a helicopter end, and the second pipe 11 is connected with a tanker end; the first control box 9 and the second control box 17 each comprise a motor 33, a control box 6, a winch 4, a worm 22, a turbine 5 and a bearing 19; the first pipe 12 is provided with an inner limiting ring 20 at a tail end, the second pipe 11 is provided with an inner limiting ring 7 at a tail end and an outer limiting ring 16 at a front end, and the third pipe 18 is provided with an outer limiting ring 13 at a front end.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aviation technology, and particularly relates to a telescopic three-section electric helicopter air refueling device. BACKGROUND

[0002] It is very common for fixed-wing aircraft to perform air refueling, but only a few countries have mastered the technology of helicopter air refueling. The range of a helicopter is usually no more than 1000 km, and air refueling can extend the range, increase flight time, increase transport load, and greatly improve long-range deployment and mobility, thereby enhancing the combat capability and flexibility, especially for long-distance rescue, search, stealth reconnaissance and attack, and sea support, which has very important practical significance. Due to the limitations of the structure and flight mode of the helicopter, the difficulty of helicopter air refueling is much higher than that of fixed-wing aircraft,

[0003] At present, the air refueling of helicopters in the above countries adopts a telescopic boom air refueling device with a two-section structure arranged on the right side of the front fuselage. The head of the boom is provided with an air refueling connector, and the refueling pipe extends about 1 m beyond the rotor. The air refueling connector is connected to the floating anchor type air refueling connector of the tanker, and the technology is highly confidential, but it can be basically judged to be homologous technology. The telescopic boom has a large diameter, and it can be judged that the internal structure is complex and the weight is large. The two-section structure causes the telescopic boom refueling device to still occupy a large length after retraction. The telescopic boom air refueling device is mostly retrofitted after the helicopter is designed, which has a great impact on the aerodynamic layout and weight center of gravity of the helicopter, and a great retrofit cost will be paid. SUMMARY

[0004] The present application aims at the problem that the existing helicopter air refueling device cannot guarantee the coaxiality and straightness between the pipes and is difficult to meet the requirements of helicopter air refueling, and provides a telescopic three-section electric helicopter air refueling device, which can meet the requirements of helicopter air refueling.

[0005] Technical scheme: The present application provides a telescopic three-section electric helicopter air refueling device, which comprises a first pipe 12, a second pipe 11, a third pipe 18, a sealing ring 8, a first control box 9, a second control box 17, an initial cable 10, and a relay cable 1.

[0006] The first pipe 12, the second pipe 11, and the third pipe 18 realize telescopic function through the way of fitting, and fuel flows in the first pipe 12, the second pipe 11, and the third pipe 18; the first pipe 12, the second pipe 11, and the third pipe 18 are coaxial, the first pipe 12 covers the second pipe 11, and the second pipe 11 covers the third pipe 18; the first pipe 12 is fixedly connected to the helicopter end, and the second pipe 11 is connected to the tanker end;

[0007] The first operating box 9 and the second operating box 17 each comprise the motor 3, the control box 6, the winch 4, the worm 2, the turbine 5 and the bearing 19; the first pipe 12 is provided with the first pipe tail end inner limiting ring 20, the second pipe 11 is provided with the second pipe tail end inner limiting ring 7 and the second pipe front end outer limiting ring 16, and the third pipe 18 is provided with the third pipe front end outer limiting ring 13; the second pipe 11 and the third pipe 18 are each provided with the groove-shaped track 14 and the rack 15.

[0008] Further, the first pipe 12 is internally provided with the limiting ring at the tail end, the inner diameter of the first pipe tail end inner limiting ring 20 is matched with the outer diameter of the second pipe 11, and the first pipe tail end inner limiting ring 20 is provided with the sealing ring to ensure the sealing effect; the second pipe 11 is internally provided with the limiting ring at the tail end, the inner diameter of the second pipe tail end inner limiting ring 7 is matched with the outer diameter of the third pipe 18, and the second pipe tail end inner limiting ring 7 is provided with the sealing ring to ensure the sealing effect.

[0009] Further, the second pipe 11 is externally provided with the limiting ring at the front end, the outer diameter of the second pipe front end outer limiting ring 16 is matched with the inner diameter of the first pipe 12, the second pipe front end outer limiting ring 16 is provided with the sealing ring, and the sealing effect is strengthened twice; the third pipe 18 is externally provided with the limiting ring at the front end, the outer diameter of the third pipe front end outer limiting ring 13 is matched with the inner diameter of the second pipe 11, and the third pipe front end outer limiting ring 13 is provided with the sealing ring, and the sealing effect is strengthened twice.

[0010] Further, the contact points of the first pipe tail end inner limiting ring 20 and the outer wall of the second pipe 11, and the contact points of the second pipe front end outer limiting ring 16 and the inner wall of the first pipe 12; the contact points of the second pipe tail end inner limiting ring 7 and the outer wall of the third pipe 18, and the contact points of the third pipe front end outer limiting ring 13 and the inner wall of the second pipe 11.

[0011] Further, the first operating box 9 is fixedly connected at the tail end of the first pipe 12, and the second pipe 11 is telescoped by the turbine 5; the second operating box 17 is fixedly connected at the tail end of the second pipe 11, and the third pipe 18 is telescoped by the turbine 5.

[0012] Further, the second pipe 11 and the third pipe 18 are each provided with the groove-shaped track 14 on the outer pipe wall, and the rack 15 is arranged on the groove-shaped track 14.

[0013] Further, the initial cable 10 is fixedly connected on the pipe wall of the first pipe 12, one end of the initial cable 10 is connected with the helicopter, the other end of the initial cable 10 is connected into the control box 6 of the first operating box 9, and then connected into the control box 6 of the second operating box 17 through the winch 4 of the first operating box 9, the relay cable 1 and the winch 4 of the second operating box 17; the control box 6 of the first operating box 9 drives the motor 3 of the first operating box 9, and the control box 6 of the second operating box 17 drives the motor 3 of the second operating box 17.

[0014] Further, the winch 4 is fixed on the top of the control box 6 in the operating box, arranged behind the motor 3, and the top outlet of the winch 4 is higher than the motor 3, so as to ensure that the relay cable 1 channel is not hindered; the operating box is provided with a relay cable 1 channel, and the winch 4 always maintains the retracting tendency of the relay cable 1 through the internal spring.

[0015] In summary, the application provides a telescopic three-section electric helicopter aerial oil receiving device, which can achieve the following technical effects:

[0016] 1. The application adopts a three-section telescopic pipe structure, has large extension amount and small retraction length.

[0017] 2. The application uses the most easily obtained electric energy on the helicopter as the working energy source, and is easy to realize.

[0018] 3. The application adopts cable communication, and the motor 3 is used for controlling the extension and retraction of the pipe, and the cable does not affect the extension and retraction of the pipe through the ingenious structure; the pipe can be stopped at any length through the structural characteristics of the worm gear 2; the overall communication effect of the application is good, and the controllability is strong.

[0019] 4. The extension and retraction logic is ingenious, the structure is simple, the fastening between parts is good, the coaxiality, linearity and positioning of the pipes are guaranteed, and the whole device is easy to manufacture and has high reliability, and can meet the helicopter aerial oil receiving requirements. BRIEF DESCRIPTION OF DRAWINGS

[0020] Fig. 1 A structure diagram of a telescopic three-section electric helicopter aerial oil receiving device provided by the application is provided;

[0021] Fig. 2 A partial structure diagram of a telescopic three-section electric helicopter aerial oil receiving device provided by the application is provided;

[0022] Among them, 1 is a relay cable, 2 is a worm gear 2, 3 is a motor 3, 4 is a winch, 5 is a turbine, 6 is a control box, 7 is a second pipe tail end inner limiting ring, 8 is a sealing ring, 9 is a first operating box, 10 is an initial cable, 11 is a second pipe, 12 is a first pipe, 13 is a third pipe front end outer limiting ring, 14 is a groove-shaped track, 15 is a rack, 16 is a second pipe front end outer limiting ring, 17 is a second operating box, 18 is a third pipe, 19 is a bearing, and 20 is a first pipe tail end inner limiting ring. DETAILED DESCRIPTION

[0023] The application aims to design a suitable aerial oil receiving device for the active service type domestic helicopter, provide extension and retraction power for the most commonly used power supply system on the helicopter, adopt a three-section layout, and design a telescopic three-section motor 3 driven helicopter aerial oil receiving device.

[0024] As Figs. 1-2 The application provides a telescopic three-section electric helicopter air refueling device, which comprises a first pipe 12, a second pipe 11, a third pipe 18, a sealing ring 8, a first operating box 9, a second operating box 17, an initial cable 10 and a relay cable 1.

[0025] The first pipe 12, the second pipe 11 and the third pipe 18 are coaxial, the first pipe 12 surrounds the second pipe 11, and the second pipe 11 surrounds the third pipe 18.

[0026] The first operating box 9 and the second operating box 17 each comprise a motor 3, a control box 6, a winch 4, a worm 2, a turbine 5 and a bearing 19.

[0027] Specifically, the first pipe 12 is internally provided with a limiting ring at the tail end, the inner diameter of the limiting ring at the tail end of the first pipe 12 is matched with the outer diameter of the second pipe 11, and the limiting ring at the tail end of the first pipe 12 is provided with the sealing ring 8 thereon to ensure the sealing effect.

[0028] It should be noted that each limiting ring is provided with the sealing ring 8, which is equivalent to two layers of sealing rings 8 between each two pipes, thereby double strengthening the sealing effect.

[0029] Specifically, the second pipe 11 is externally provided with a limiting ring at the front end, the outer diameter of the limiting ring at the front end of the second pipe 11 is matched with the inner diameter of the first pipe 12, and the limiting ring at the front end of the second pipe 11 is provided with the sealing ring 8 thereon to strengthen the sealing effect twice.

[0030] It should be noted that the limiting ring at the front end of the second pipe 11 is matched with the limiting ring at the rear end of the first pipe 12 to prevent the second pipe 11 from being pulled out of the first pipe 12.

[0031] Specifically, the contact points between the inner limit ring at the rear end of the No. 1 tube 12 and the outer wall of the No. 2 tube 11, and the contact points between the outer limit ring at the front end of the No. 2 tube 11 and the inner wall of the No. 1 tube 12; the contact points between the inner limit ring at the rear end of the No. 2 tube 11 and the outer wall of the No. 3 tube 18, and the contact points between the outer limit ring 13 at the front end of the No. 3 tube 18 and the inner wall of the No. 2 tube 11.

[0032] It should be noted that, according to the two-point-one-line principle, the contact points between the inner stop ring at the rear end of tube 12 and the outer wall of tube 2 11, as well as the contact points between the outer stop ring at the front end of tube 2 11 and the inner wall of tube 12, ensure the coaxiality and linearity of tubes 12 and 11. Also, according to the two-point-one-line principle, the contact points between the inner stop ring at the rear end of tube 2 11 and the outer wall of tube 3 18, as well as the contact points between the outer stop ring 13 at the front end of tube 3 18 and the inner wall of tube 2 11, ensure the coaxiality and linearity of tubes 2 11 and 18.

[0033] Specifically, the No. 1 control box 9 is fixedly connected to the tail end of the No. 1 pipe 12, and controls the extension and retraction of the No. 2 pipe 11 through the turbine 5; the No. 2 control box 17 is fixedly connected to the tail end of the No. 2 pipe 11, and controls the extension and retraction of the No. 3 pipe 18 through the turbine 5.

[0034] Specifically, the outer walls of the No. 2 pipe 11 and the No. 3 pipe 18 are both provided with grooved tracks, and racks 15 are provided on the grooved tracks.

[0035] It should be noted that the width of the rack 15 is comparable to but slightly larger than the width of the turbine 5 to ensure smooth operation.

[0036] It should be noted that the height of the rack 15 is equivalent to but slightly smaller than the height of the grooved track to ensure that the rack 15 of the third pipe 18 does not interfere with the second pipe 11, and the rack 15 of the second pipe 11 does not interfere with the first pipe 12.

[0037] Among them, the rack 15 and the turbine 5 have the same key parameters such as tooth pitch, tooth top height, tooth groove width, etc., to ensure that the turbine 5 and the rack 15 are accurately matched and the turbine 5 drives the rack 15 smoothly.

[0038] It is understood that a grooved track is provided on the outer tube wall, and a rack 15 is mounted on the grooved track. The width of rack 15 is comparable to, but slightly larger than, the width of turbine 5 to ensure smooth operation. The height of rack 15 is comparable to, but slightly smaller than, the height of the grooved track to ensure that rack 15 does not interfere with the tube. Key parameters related to rack 15 and turbine 5, such as tooth pitch, tooth top height, and tooth groove width, are essentially identical. This ensures that turbine 5 and rack 15 precisely match and that turbine 5 smoothly drives rack 15. The two sides of the grooved track effectively constrain turbine 5 to travel on rack 15, which is equivalent to positioning tube 3 18 circumferentially relative to tube 2 11, and tube 2 11 circumferentially relative to tube 12.

[0039] It should be noted that the slot-shaped track can effectively constrain the turbine 5 to walk on the rack 15, which is equivalent to the positioning of the No. 3 pipe 18 in the circumferential direction of the No. 2 pipe 11, and the positioning of the No. 2 pipe 11 in the circumferential direction of the No. 1 pipe 12.

[0040] Specifically, the initial cable 10 is fixed to the wall of the No. 1 pipe 12, one end of the initial cable 10 is connected to the helicopter, and the other end of the initial cable 10 is connected to the control box 6 of the No. 1 control box 9, and then through the No. 1 winch 4, the relay cable 1 and the No. 2 winch 4, the control box 6 of the No. 2 control box 17; the No. 1 control box 6 drives the No. 1 motor 3, and the No. 2 control box drives the No. 2 motor 3.

[0041] Specifically, the winch 4 is fixed on the top of the control box 6 in the control box and is arranged behind the motor 3, and the top of the winch 4 is higher than the motor 3 to ensure that the channel of the relay cable 1 is not hindered; the control box is provided with a channel for the relay cable 1, and the winch 4 is always kept in the tendency of retracting the relay cable 1 through the internal spring.

[0042] It should be noted that the winch 4 always keeps the tendency of retracting the relay cable 1 through the internal spring. When the oil receiving pipe is elongated, the winch 4 is unwound, and the spring is energized; when the oil receiving pipe is retracted, the spring is released, and the winch 4 is wound, so as to keep the relay cable 1 tight at any time, so as to ensure that the relay cable 1 does not affect the extension and retraction of the oil receiving pipe.

[0043] When the oil receiving pipe is elongated, the winch 4 is unwound, and the spring is energized; when the oil receiving pipe is retracted, the spring is released, and the winch 4 is wound, so as to keep the relay cable 1 tight at any time, so as to ensure that the relay cable 1 does not affect the extension and retraction of the oil receiving pipe.

[0044] Specifically, the motor 3 is screwed and fixed on the top of the control box 6 in the control box and is arranged behind the winch 4, and the motor 3 drives the turbine 5 through the worm 2, and the turbine 5 drives the rack 15.

[0045] It should be added that the motor 3 drives the turbine 5 through the worm 2, and the turbine 5 drives the rack 15. The present application utilizes the characteristics that the worm gear 2 transmission can only drive the turbine 5 by the worm 2, and cannot drive the worm 2 by the turbine 5, so that the oil receiving pipe can only be elongated and retracted under the drive of the motor 3, and will not be elongated and retracted by external force, so the present application does not need to set a limiting device to prevent the oil receiving pipe from retracting when refueling, and the oil receiving pipe can be stopped at any length.

[0046] As described above, the present application utilizes the characteristics that the worm gear 2 transmission can only drive the turbine 5 by the worm 2, and cannot drive the worm 2 by the turbine 5, so that the oil receiving pipe can only be elongated and retracted under the drive of the motor 3, and will not be elongated and retracted by external force, so the present application does not need to set a limiting device to prevent the oil receiving pipe from retracting when refueling.

[0047] The application provides a telescopic three-section electric helicopter air refueling device, and the following technical effects can be achieved:

[0048] 1. The application adopts a three-section telescopic pipe structure, has large telescopic amount, and small length after retraction.

[0049] 2. The application uses the most easily obtained electric energy on the helicopter as the working energy source, and is easy to realize.

[0050] 3. The application adopts cable communication, and the motor 3 is controlled to achieve the purpose of controlling the telescopic refueling device, and the cable does not affect the telescopic pipe through the ingenious structure, and the refueling device can be stopped at any length through the structural characteristics of the worm gear 2, the overall communication effect of the application is good, and the controllability is strong.

[0051] 4. The telescopic and retraction logic is ingenious, the structure is simple, the fastening between parts is good, the coaxiality, linearity and positioning of the pipes of the refueling device are guaranteed, and the refueling device is easy to manufacture, the whole device has high reliability, and can meet the requirements of the helicopter air refueling.

Claims

1. A telescopic three-section electrically powered helicopter in-flight refueling device, characterized in that, It comprises a first pipe (12), a second pipe (11), a third pipe (18), a sealing ring (8), a first operating box (9), a second operating box (17), an initial cable (10) and a relay cable (1). The first pipe (12), the second pipe (11) and the third pipe (18) are coaxial, the first pipe (12) surrounds the second pipe (11), and the second pipe (11) surrounds the third pipe (18). The first operating box (9) and the second operating box (17) each comprise a motor (3), a control box (6), a winch (4), a worm (2), a worm wheel (5) and a bearing (19). The initial cable (10) is fixed to the wall of the first pipe (12), one end of the initial cable (10) is connected to a helicopter, the other end of the initial cable (10) is connected to the control box (6) of the first operating box (9) and then passes through the winch (4) of the first operating box (9), the relay cable (1) and the winch (4) of the second operating box (17) in sequence and is connected to the control box (6) of the second operating box (17).

2. The telescopic three-section electrically powered helicopter in-flight refueling device according to claim 1, characterized in that, The first pipe (12) is provided with an inner limiting ring at the tail end, the inner diameter of the inner limiting ring at the tail end of the first pipe (20) matches the outer diameter of the second pipe (11), and a sealing ring is arranged on the inner limiting ring at the tail end of the first pipe (20) to ensure the sealing effect. The second pipe (11) is provided with an inner limiting ring at the tail end, the inner diameter of the inner limiting ring at the tail end of the second pipe (7) matches the outer diameter of the third pipe (18), and a sealing ring is arranged on the inner limiting ring at the tail end of the second pipe (7) to ensure the sealing effect.

3. The telescopic three-section electrically powered helicopter in-flight refueling device according to claim 1, characterized in that, The outer end of the second pipe (11) is externally provided with a limiting ring, the outer diameter of the limiting ring (16) at the outer end of the second pipe is matched with the inner diameter of the first pipe (12), a sealing ring is arranged on the limiting ring (16) at the outer end of the second pipe, and the sealing effect is twice strengthened; the outer end of the third pipe (18) is externally provided with a limiting ring, the outer diameter of the limiting ring (13) at the outer end of the third pipe is matched with the inner diameter of the second pipe (11), and a sealing ring is arranged on the limiting ring (13) at the outer end of the third pipe, so that the sealing effect is twice strengthened.

4. The telescopic three-section electrically powered helicopter in-flight refueling device according to claim 1, characterized in that, The inner limiting ring (20) at the tail end of the first pipe is in contact with the outer wall of the second pipe (11), and the outer limiting ring (16) at the front end of the second pipe is in contact with the inner wall of the first pipe (12); the inner limiting ring (7) at the tail end of the second pipe is in contact with the outer wall of the third pipe (18), and the outer limiting ring (13) at the front end of the third pipe is in contact with the inner wall of the second pipe (11).

5. The telescopic three-section electrically powered helicopter in-flight refueling device according to claim 1, characterized in that, The first operating box (9) is fixedly connected to the tail end of the first pipe (12) and operates the second pipe (11) to stretch and retract through the worm gear (5); the second operating box (17) is fixedly connected to the tail end of the second pipe (11) and operates the third pipe (18) to stretch and retract through the worm gear (5).

6. The telescopic three-section electrically powered helicopter in-flight refueling device according to claim 1, characterized in that, The second pipe (11) and the third pipe (18) are both provided with a groove-shaped track (14) on the outer pipe wall, and the groove-shaped track (14) is provided with a rack (15).

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