Telescopic three-section type electric helicopter air oil receiving device

Abstract

The invention provides a telescopic three-section type electric helicopter aerial oil receiving device which comprises a first pipe 12, a second pipe 11, a third pipe 18, a sealing ring 8, a first operation box 9, a second operation box 17, an initial cable 10 and a relay cable 1, the first pipe 12, the second pipe 11 and the third pipe 18 achieve the telescopic function in a sleeving mode, and fuel oil 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 second pipe 11 is sleeved with the first pipe 12, and the third pipe 18 is sleeved with the second pipe 11; the first pipe 12 is fixedly connected with the helicopter end, and the second pipe 11 is in butt joint with the oiling machine end. Each of the first operation box 9 and the second operation box 17 comprises a motor 33, a control box 6, a winch 4, a worm 22, a turbine 5 and a bearing 19; a first pipe tail end inner limiting ring 20 is arranged on the first pipe 12, a second pipe tail end inner limiting ring 7 and a second pipe front end outer limiting ring 16 are arranged on the second pipe 11, and a third pipe front end outer limiting ring 13 is arranged on the third pipe 18.

Description

Technical Field

[0001] The patent of this invention belongs to aviation technology, and specifically relates to a retractable three-stage electric helicopter aerial refueling device. Background Art

[0002] It is very common for fixed-wing aircraft to perform aerial refueling, but only a few countries have mastered the technology of aerial refueling for helicopters. The range of helicopters usually does not exceed 1,000 km. Aerial refueling can extend the range, increase flight time, increase transport load, and greatly improve long-range deployment and mobility, thereby enhancing its combat capability and flexibility, especially for long-distance rescue, search, covert reconnaissance, maritime support and other subjects, which has great practical significance. Due to the limitations of the structure and flight mode of helicopters, the difficulty of aerial refueling of helicopters is much higher than that of fixed-wing aircraft. Currently, only five countries, including the United States, France, Japan, Brazil, and Israel, can use KC130J and A400M propeller low-speed cruise tankers to perform aerial refueling on helicopters such as UH-60, CH53, HH-3E, MH-47E, H-225M, and H-36.

[0003] At present, the helicopter aerial refueling in the above countries all adopts the retractable truss aerial refueling device, which is a two-stage structure and is set on the right side of the front fuselage. The aerial refueling joint is set at the head of the truss. The refueling pipe exceeds the rotor by about 1m. The aerial refueling joint is connected with the hose floating anchor aerial refueling joint of the tanker. The technology is highly confidential, but it can be basically judged to be a homologous technology. The diameter of the retractable truss is huge, and it can be judged that the internal structure is complex and the weight is large. The setting of the two-stage structure causes the truss refueling device to still occupy a large length after retraction. The retractable truss aerial refueling device is mostly modified after the helicopter is finalized, which has a great impact on the aerodynamic layout and weight center of gravity of the helicopter, and will pay a large modification cost. Summary of the invention

[0004] In view of the problem that the existing helicopter aerial refueling device cannot ensure the coaxiality and linearity between the pipes and is difficult to meet the requirements of helicopter aerial refueling, the present application provides a retractable three-stage electric helicopter aerial refueling device that can meet the requirements of helicopter aerial refueling.

[0005] Technical solution: The present application provides a retractable three-stage electric helicopter aerial refueling device, including a No. 1 pipe 12, a No. 2 pipe 11, a No. 3 pipe 18, a sealing ring 8, a No. 1 control box 9, a No. 2 control box 17, an initial cable 10, and a relay cable 1, wherein:

[0006] The No. 1 pipe 12, the No. 2 pipe 11, and the No. 3 pipe 18 are telescopically connected, and the fuel flows inside the No. 1 pipe 12, the No. 2 pipe 11, and the No. 3 pipe 18; the No. 1 pipe 12, the No. 2 pipe 11, and the No. 3 pipe 18 are coaxial, the No. 1 pipe 12 covers the No. 2 pipe 11, and the No. 2 pipe 11 covers the No. 3 pipe 18; the No. 1 pipe 12 is fixedly connected to the helicopter end, and the No. 2 pipe 11 is connected to the tanker end;

[0007] The No. 1 operating box 9 and the No. 2 operating box 17 both include a motor 3, a control box 6, a winch 4, a worm 2, a turbine 5, and a bearing 19; the No. 1 pipe 12 is provided with an inner limit ring 20 at the tail end of the No. 1 pipe, the No. 2 pipe 11 is provided with an inner limit ring 7 at the tail end of the No. 2 pipe, and an outer limit ring 16 at the front end of the No. 2 pipe, and the No. 3 pipe 18 is provided with an outer limit ring 13 at the front end of the No. 3 pipe; the No. 2 pipe 11 and the No. 3 pipe 18 are both provided with grooved tracks 14 and racks 15.

[0008] Furthermore, a limited ring is arranged inside the tail end of the No. 1 tube 12, the inner diameter of the internal limit ring 20 at the tail end of the No. 1 tube matches the outer diameter of the No. 2 tube 11, and a sealing ring is arranged on the internal limit ring 20 at the tail end of the No. 1 tube to ensure the sealing effect; a limited ring is arranged inside the tail end of the No. 2 tube 11, the inner diameter of the internal limit ring 7 at the tail end of the No. 2 tube matches the outer diameter of the No. 3 tube 18, and a sealing ring is arranged on the internal limit ring 7 at the tail end of the No. 2 tube to ensure the sealing effect.

[0009] Furthermore, a limiting ring is provided on the outside of the front end of the No. 2 tube 11, the outer diameter of the outer limiting ring 16 on the front end of the No. 2 tube matches the inner diameter of the No. 1 tube 12, and a sealing ring is provided on the outer limiting ring 16 on the front end of the No. 2 tube to secondary enhance the sealing effect; a limiting ring is provided on the outside of the front end of the No. 3 tube 18, the outer diameter of the outer limiting ring 13 on the front end of the No. 3 tube matches the inner diameter of the No. 2 tube 11, and a sealing ring is provided on the outer limiting ring 13 on the front end of the No. 3 tube to secondary enhance the sealing effect.

[0010] Furthermore, the contact points of the inner limit ring 20 at the tail end of the No. 1 tube and the outer wall of the No. 2 tube 11, as well as the contact points of the outer limit ring 16 at the front end of the No. 2 tube and the inner wall of the No. 1 tube 12; the contact points of the inner limit ring 7 at the tail end of the No. 2 tube and the outer wall of the No. 3 tube 18, as well as the contact points of the outer limit ring 13 at the front end of the No. 3 tube and the inner wall of the No. 2 tube 11.

[0011] Furthermore, 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.

[0012] Furthermore, the second pipe 11 and the third pipe 18 are both provided with grooved tracks 14 on the outer pipe walls, and racks 15 are provided on the grooved tracks 14 .

[0013] Furthermore, the initial cable 10 is fixedly connected 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 is connected to the control box 6 of the No. 2 control box 17 through the winch 4 of the No. 1 control box 9, the relay cable 1 and the winch 4 of the No. 2 control box 17 in sequence; the control box 6 of the No. 1 control box 9 controls and drives the motor 3 of the No. 1 control box 9, and the control box 6 of the No. 2 control box 17 controls and drives the motor 3 of the No. 2 control box 17.

[0014] Furthermore, the winch 4 is fixedly connected to the top of the control box 6 in the operating box and is arranged behind the motor 3. The top outlet of the winch 4 is higher than the motor 3 to ensure that the channel of the relay cable 1 is unobstructed; a channel for the relay cable 1 is left on the operating box, and the winch 4 always maintains the tendency of the relay cable 1 to retract through its internal spring.

[0015] In summary, the present application provides a retractable three-stage electric helicopter aerial refueling device, which can achieve the following technical effects:

[0016] 1. The present invention adopts a three-section telescopic tube structure, which has a large extension amount and a short length after retraction.

[0017] 2. The present invention uses the most easily available electrical energy on a helicopter as the working energy source, and is easy to implement.

[0018] 3. The present invention adopts cable communication and operates the motor 3 to achieve the purpose of controlling the extension and retraction of the tube. The cable will not affect the extension and retraction of the tube through an ingenious structure. The tube can be stopped at any length through the structural characteristics of the worm gear 2. The present invention has good overall communication effect and strong maneuverability.

[0019] 4. The extension and retraction logic is ingeniously designed, but the structure is simple, the parts are well fastened, the coaxiality, linearity and positioning between the pipes are guaranteed, and it is easy to manufacture. The whole device has high reliability and can meet the requirements of helicopter aerial refueling. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A schematic diagram of the structure of a retractable three-stage electric helicopter aerial refueling device provided in this application;

[0021] Figure 2 A schematic diagram of the partial structure of a retractable three-stage electric helicopter aerial refueling device provided in this application;

[0022] Among them, 1-relay cable, 2-worm gear 2, 3-motor 3, 4-winch, 5-turbine, 6-control box, 7-inner limit ring at the tail end of No. 2 pipe, 8-sealing ring, 9-No. 1 operating box, 10-initial cable, 11-No. 2 pipe, 12-No. 1 pipe, 13-outer limit ring at the front end of No. 3 pipe, 14-grooved track, 15-rack, 16-outer limit ring at the front end of No. 2 pipe, 17-No. 2 operating box, 18-No. 3 pipe, 19-bearing, 20-inner limit ring at the tail end of No. 1 pipe. DETAILED DESCRIPTION

[0023] The present invention aims to design a suitable aerial refueling device for the currently established domestic helicopters, using the most commonly used power supply system on the helicopter to provide retractable power, adopting a three-stage layout, and designing a retractable three-stage motor 3 to drive the helicopter aerial refueling device.

[0024] like Figure 1-2 As shown, the present application provides a retractable three-stage electric helicopter aerial refueling device, including a No. 1 pipe 12, a No. 2 pipe 11, a No. 3 pipe 18, a sealing ring 8, a No. 1 control box 9, a No. 2 control box 17, an initial cable 10, and a relay cable 1, wherein:

[0025] The No. 1 pipe 12, the No. 2 pipe 11, and the No. 3 pipe 18 are telescopically connected, and the fuel flows inside the No. 1 pipe 12, the No. 2 pipe 11, and the No. 3 pipe 18; the No. 1 pipe 12, the No. 2 pipe 11, and the No. 3 pipe 18 are coaxial, the No. 1 pipe 12 covers the No. 2 pipe 11, and the No. 2 pipe 11 covers the No. 3 pipe 18; the No. 1 pipe 12 is fixedly connected to the helicopter end, and the No. 2 pipe 11 is connected to the tanker end;

[0026] The No. 1 operating box 9 and the No. 2 operating box 17 both include a motor 3, a control box 6, a winch 4, a worm 2, a turbine 5, and a bearing 19; the No. 1 pipe 12 is provided with an inner limit ring 20 at the tail end of the No. 1 pipe 12, the No. 2 pipe 11 is provided with an inner limit ring 7 at the tail end of the No. 2 pipe 11 and an outer limit ring 16 at the front end of the No. 2 pipe 11, and the No. 3 pipe 18 is provided with an outer limit ring 13 at the front end of the No. 3 pipe 18; the No. 2 pipe 1111 and the No. 3 pipe 18 are both provided with grooved tracks 14 and racks 15.

[0027] Specifically, a limited ring is arranged inside the tail end of the No. 1 tube 12, and the inner diameter of the internal limit ring at the tail end of the No. 1 tube 12 matches the outer diameter of the No. 2 tube 11, and a sealing ring 8 is arranged on the internal limit ring at the tail end of the No. 1 tube 12 to ensure the sealing effect; a limited ring is arranged inside the tail end of the No. 2 tube 11, and the inner diameter of the internal limit ring 7 at the tail end of the No. 2 tube 11 matches the outer diameter of the No. 3 tube 18, and a sealing ring 8 is arranged on the internal limit ring 7 at the tail end of the No. 2 tube 11 to ensure the sealing effect.

[0028] It should be noted that a sealing ring 8 is provided on each retaining ring, which is equivalent to having two layers of sealing rings 8 between each two tubes, thereby doubly strengthening the sealing effect.

[0029] Specifically, a limiting ring is arranged on the outside of the front end of the No. 2 pipe 11, and the outer diameter of the limiting ring on the front end of the No. 2 pipe 11 matches the inner diameter of the No. 1 pipe 12. A sealing ring 8 is arranged on the outer limiting ring on the front end of the No. 2 pipe 11 to enhance the sealing effect for the second time; a limiting ring is arranged on the outside of the front end of the No. 3 pipe 18, and the outer diameter of the limiting ring on the front end of the No. 3 pipe 18 matches the inner diameter of the No. 2 pipe 11. A sealing ring 8 is arranged on the outer limiting ring on the front end of the No. 3 pipe 18 to enhance the sealing effect for the second time.

[0030] It should be noted that the outer stop ring at the front end of the No. 2 pipe 11 cooperates with the inner stop ring at the rear end of the No. 1 pipe 12 to prevent the No. 2 pipe 11 from slipping out of the No. 1 pipe 12. The outer stop ring at the front end of the No. 3 pipe 18 cooperates with the inner stop ring at the rear end of the No. 2 pipe 11 to prevent the No. 3 pipe 18 from slipping out of the No. 2 pipe 11.

[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 point between the inner stop ring at the rear end of the No. 1 tube 12 and the outer wall of the No. 2 tube 11, and the contact point between the outer stop ring at the front end of the No. 2 tube 11 and the inner wall of the No. 1 tube 12 ensure the coaxiality and linearity of the No. 1 tube 12 and the No. 2 tube 11. According to the two-point-one-line principle, the contact point between the inner stop ring at the rear end of the No. 2 tube 11 and the outer wall of the No. 3 tube 18, and the contact point between the outer stop ring 13 at the front end of the No. 3 tube 18 and the inner wall of the No. 2 tube 11 ensure the coaxiality and linearity of the No. 2 tube 11 and the No. 3 tube 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 tube 18 does not interfere with the second tube 11 , and the rack 15 of the second tube 11 does not interfere with the first tube 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 stably.

[0038] It is understandable that a groove track is provided on the outer tube wall, and a rack 15 is provided on the groove track. The width of the rack 15 is equivalent to the width of the turbine 5 but slightly larger to ensure smooth operation. The height of the rack 15 is equivalent to the height of the groove track but slightly smaller to ensure that the rack 15 does not interfere with the tube. The key parameters of the rack 15 and the turbine 5, such as the pitch, top height, and tooth groove width, are basically the same to ensure that the turbine 5 and the rack 15 are accurately matched, and the turbine 5 drives the rack 15 smoothly. The two sides of the groove track can effectively constrain the turbine 5 to move on the rack 15, which is equivalent to the third tube 18 being positioned in the circumferential direction of the second tube 11, and the second tube 11 being positioned in the circumferential direction of the first tube 12.

[0039] It should be noted that the two sides of the grooved track can effectively constrain the turbine 5 to move on the rack 15, which is equivalent to the No. 3 pipe 18 being positioned in the circumferential direction of the No. 2 pipe 11, and the No. 2 pipe 11 being positioned in the circumferential direction of the No. 1 pipe 12.

[0040] Specifically, the initial cable 10 is fixedly connected 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 is connected to the control box 6 of the No. 2 control box 17 through the No. 1 winch 4, the relay cable 1 and the No. 2 winch 4 in sequence; the No. 1 control box 6 controls and drives the No. 1 motor 3, and the No. 2 control box controls and drives the No. 2 motor 3.

[0041] Specifically, the winch 4 is fixedly connected to the top of the control box 6 in the control box and is arranged behind the motor 3. The top outlet of the winch 4 is higher than the motor 3 to ensure that the channel of the relay cable 1 is unobstructed. A channel for the relay cable 1 is left on the control box, and the winch 4 always maintains the tendency of the relay cable 1 to retract through its internal spring.

[0042] It should be noted that the winch 4 always keeps the retraction trend of the relay cable 1 through its internal spring. When the receiving pipe is extended, the winch 4 is unloaded and the spring is charged. When the receiving pipe is retracted, the spring is released and the winch 4 is reeled in, so as to keep the relay cable 1 tight at all times to ensure that the relay cable 1 does not affect the extension and retraction of the receiving pipe.

[0043] When the receiving pipe is extended, the winch 4 is unloaded and the spring stores energy. When the receiving pipe is retracted, the spring releases energy and the winch 4 is reeled in, keeping the relay cable 1 taut at all times to ensure that the relay cable 1 does not affect the extension and retraction of the 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. 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 invention utilizes the characteristic that the worm gear 2 can only drive the turbine 5 by the worm 2, and the worm 2 cannot be driven by the turbine 5, so the oil receiving pipe can only be extended and retracted under the drive of the motor 3, and will not be extended and retracted by external forces. Therefore, the present invention does not need to set a limit device to prevent the oil receiving pipe from retracting during refueling, and the oil receiving pipe can be stopped at any length.

[0046] In summary, the present invention utilizes the characteristic that the worm gear 2 can only drive the turbine 5 by the worm 2, but cannot drive the worm 2 by the turbine 5. Therefore, the oil receiving pipe can only be extended and retracted under the drive of the motor 3 and will not be extended and retracted by external forces. Therefore, the present invention does not need to set a limiting device to prevent the oil receiving pipe from retracting when refueling.

[0047] The present application provides a retractable three-stage electric helicopter aerial refueling device, which can achieve the following technical effects:

[0048] 1. The present invention adopts a three-section telescopic tube structure, which has a large extension amount and a short length after retraction.

[0049] 2. The present invention uses the most easily available electrical energy on a helicopter as the working energy source, and is easy to implement.

[0050] 3. The present invention adopts cable communication and operates the motor 3 to achieve the purpose of controlling the extension and retraction of the oil receiving device. The cable will not affect the extension and retraction of the pipe through the ingenious structure. The oil receiving device can be stopped at any length through the structural characteristics of the worm gear 2. The present invention has good overall communication effect and strong controllability.

[0051] 4. The extension and retraction logic is ingeniously designed, but the structure is simple, the parts are well fastened, the coaxiality, linearity and positioning of the pipes in the refueling device are guaranteed, and it is easy to manufacture. The entire device has high reliability and can meet the requirements of helicopter aerial refueling.

Claims

1. A retractable three-stage electric helicopter aerial refueling device, characterized in that: It includes a No. 1 pipe (12), a No. 2 pipe (11), a No. 3 pipe (18), a sealing ring (8), a No. 1 control box (9), a No. 2 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) are sleeved to achieve a telescopic function, and the fuel flows inside 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 to the helicopter end, and the second pipe (11) is connected to the tanker end; The first control box (9) and the second control box (17) both comprise a motor (3), a control box (6), a capstan (4), a worm (2), a turbine (5), and a bearing (19); the first pipe (12) is provided with an inner stop ring (20) at the tail end of the first pipe, the second pipe (11) is provided with an inner stop ring (7) at the tail end of the second pipe and an outer stop ring (16) at the front end of the second pipe, and the third pipe (18) is provided with an outer stop ring (13) at the front end of the third pipe; the second pipe (11) and the third pipe (18) are both provided with a grooved track (14) and a rack (15).

2. The retractable three-stage electric helicopter aerial refueling device according to claim 1 is characterized in that: A limiting ring is arranged inside the tail end of the first tube (12), the inner diameter of the limiting ring (20) inside the tail end of the first tube matches the outer diameter of the second tube (11), and a sealing ring is arranged on the limiting ring (20) inside the tail end of the first tube to ensure a sealing effect; a limiting ring is arranged inside the tail end of the second tube (11), the inner diameter of the limiting ring (7) inside the tail end of the second tube matches the outer diameter of the third tube (18), and a sealing ring is arranged on the limiting ring (7) inside the tail end of the second tube to ensure a sealing effect.

3. The retractable three-stage electric helicopter aerial refueling device according to claim 1 is characterized in that: A limiting ring is arranged outside the front end of the second pipe (11), the outer diameter of the outer limiting ring (16) at the front end of the second pipe matches the inner diameter of the first pipe (12), and a sealing ring is arranged on the outer limiting ring (16) at the front end of the second pipe, so as to enhance the sealing effect for a second time; a limiting ring is arranged outside the front end of the third pipe (18), the outer diameter of the outer limiting ring (13) at the front end of the third pipe matches the inner diameter of the second pipe (11), and a sealing ring is arranged on the outer limiting ring (13) at the front end of the third pipe, so as to enhance the sealing effect for a second time.

4. The retractable three-stage electric helicopter aerial refueling device according to claim 1 is characterized in that: The inner stop ring (20) at the tail end of the first tube contacts the outer wall of the second tube (11), and the outer stop ring (16) at the front end of the second tube contacts the inner wall of the first tube (12); the inner stop ring (7) at the tail end of the second tube contacts the outer wall of the third tube (18), and the outer stop ring (13) at the front end of the third tube contacts the inner wall of the second tube (11).

5. The retractable three-stage electric helicopter aerial refueling device according to claim 1 is characterized in that: The first control box (9) is fixedly connected to the tail end of the first pipe (12) and controls the extension and retraction of the second pipe (11) through the turbine (5); the second control box (17) is fixedly connected to the tail end of the second pipe (11) and controls the extension and retraction of the third pipe (18) through the turbine (5).

6. The retractable three-stage electric helicopter aerial refueling device according to claim 1 is characterized in that: The second pipe (11) and the third pipe (18) are both provided with grooved tracks (14) on the outer pipe walls, and racks (15) are provided on the grooved tracks (14).

7. The retractable three-stage electric helicopter aerial refueling device according to claim 1 is characterized in that: The initial cable (10) is fixedly connected 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 is connected to the control box (6) of the No. 2 control box (17) through the winch (4) of the No. 1 control box (9), the relay cable (1) and the winch (4) of the No. 2 control box (17) in sequence; the control box (6) of the No. 1 control box (9) controls the motor (3) of the No. 1 control box (9), and the control box (6) of the No. 2 control box (17) controls the motor (3) of the No. 2 control box (17).

8. The retractable three-stage electric helicopter aerial refueling device according to claim 1 is characterized in that: The winch (4) is fixedly connected to the top of the control box (6) in the control box and is arranged behind the motor (3). The top outlet of the winch (4) is higher than the motor (3) to ensure that the passage of the relay cable (1) is unobstructed. A passage for the relay cable (1) is left on the control box. The winch (4) always maintains the tendency of the relay cable (1) to retract through its internal spring.

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