Rotorcraft tip light apparatus, method of use, and blade

Abstract

The present application belongs to the technical field of overall design of rotary-wing aircraft, and particularly relates to a rotor tip light device of a rotary-wing aircraft, a use method and a rotor blade. The rotor tip light device is arranged in a fairing at a tip of a rotor blade, and comprises a rotor tip cover, a right wing rib, a left wing rib, a mounting bolt and a rotor tip light emitting body. The rotor tip cover adopts a thin-walled structure of metal or composite material, and is filled with foam outside the right wing rib and the left wing rib. The right wing rib and the left wing rib are determined according to a rotor blade airfoil and a size of the rotor tip light emitting body.

Description

Technical Field

[0001] This invention belongs to the field of rotorcraft overall design technology, and particularly relates to a rotorcraft tip light device, its usage method, and rotor blades. Background Technology

[0002] Rotary-wing aircraft have one or more approved anti-collision lights installed on their airframe structure, which to some extent meet the requirements for helicopter use on the ground and in the air.

[0003] (1) Although existing rotorcraft have a lot of lighting equipment, such as navigation lights, collision avoidance lights, landing lights and formation lights, these lighting equipment are mainly arranged on the left and right sides of the rotorcraft fuselage or the vertical tail, providing the general outline of the rotorcraft. Since the rotor disk size and installation position are much larger than the external outline of the rotorcraft fuselage, the overall structure of the rotorcraft cannot be effectively covered when the rotorcraft is being maintained on the ground, especially the rotor blade size. Therefore, in scenarios where the lighting conditions in the airport hangar are insufficient or when the use of all aircraft lights is to keep the aircraft silent, accidents are likely to occur where the rotor tip collides with the hangar or other aircraft.

[0004] (2) When rotorcraft fly in close formation at night, compared with the large spacing of fixed-wing aircraft, the spacing between rotorcraft is generally 1.5 to 2.5 times the rotor disk diameter. Although rotorcraft have anti-collision lights and formation lights that can show the relative position of two aircraft, pilots cannot accurately judge the relative position of two aircraft in low light conditions at night, which poses a safety hazard. Summary of the Invention

[0005] This invention relates to a rotor tip light device, its usage method, and rotor blades for a rotorcraft. By arranging rotor tip lights at the tips of the rotor blades, and taking into account the ground and air operation scenarios and operational requirements of helicopters, the rotor collision avoidance design of the rotorcraft is rationally planned to solve the problem that pilots cannot accurately judge the relative positions of two aircraft in low-light conditions at night, which poses a safety hazard.

[0006] To achieve the above objectives, the present invention employs the following technical solution.

[0007] A rotor tip light device for a rotary-wing aircraft, the rotor tip light device being disposed within a fairing at the tip of a rotor blade, the rotor tip light device comprising:

[0008] Propeller tip cover 002, right wing rib 003, left wing rib 004, mounting bolt 005, propeller tip light emitting body 010;

[0009] The propeller tip cover 002 adopts a thin-walled structure of metal or composite material, and is filled with foam on the outside of the right wing rib 003 and the left wing rib 004. The right wing rib 003 and the left wing rib 004 are determined according to the airfoil of the propeller blade and the size of the propeller tip lamp light body 010.

[0010] Furthermore,

[0011] Along the rotor radial direction, select cross sections 60mm and 163mm away from the edge of the rotor tip cover 002, and construct the left wing rib 004 and the right wing rib 003 respectively.

[0012] Furthermore,

[0013] The paddle tip lamp light-emitting body 010 includes: a transparent cover 011, a first sealing gasket 012, a second sealing gasket 013, a light shield 014, a fixing bolt 015, a light emitter 016, a cable 017, a base 018, a counterweight block 019, a counterweight bolt 020, and a plug 021.

[0014] The transparent cover 011 is made of transparent material, and its shape is consistent with the airfoil of the propeller blade.

[0015] The first sealing gasket 012 and the second sealing gasket 013 are placed between the transparent cover 011 and the paddle tip cover 002, and are conformal to the transparent cover 011.

[0016] The light shield 014 is made of an opaque plastic sheet, which is concave in shape and fits the bottom of the light emitter 016.

[0017] The LED 016 is an LED with visible light and infrared light, adjustable brightness, and a beam angle greater than 210°;

[0018] The base 018 is a metal alloy part with a concave inner cavity, used to install the light emitter 016. Both the base 018 and the light emitter 016 are fixed by fixing bolts 015.

[0019] A space is reserved for cable 017 in the concave part of the base, and an installation interface is reserved for counterweight 019 and counterweight bolt 020;

[0020] The counterweight 019 consists of a vulcanized rubber layer and a steel core, and is configured as multiple cylindrical pads. It is fixed to the groove inside the base 018 with counterweight bolts 020.

[0021] Furthermore,

[0022] The light emitter 016 is equipped with multiple rows of LEDs, each row of LEDs can emit light independently, and each row of LEDs emits light at a different angle through the light shield 014. By controlling the light emission of different rows of LEDs, a light-emitting device with a variable angle is formed.

[0023] The present invention also provides a rotor blade for a rotary-wing aircraft, the rotor blade comprising: a blade tip light device, a blade body 090, a leading edge cladding 091, and a cable plug 092;

[0024] The tip light device is located at the tip of the blade, and its shape is consistent with the theoretical aerodynamic shape of the blade design. It is connected to the blade body 090 through a connector.

[0025] Furthermore,

[0026] The connector includes: a propeller tip bracket 093 and a cable socket 094; used to realize the mechanical and electrical connection of the propeller tip lamp device;

[0027] A blade tip bracket 093 and a cable socket 094 are reserved at the tip of the blade body 090. The blade tip bracket 093 is a high-strength structural component with reserved connecting threads, which is manufactured integrally with the blade body 090. Two or more cable sockets 094 are arranged inside the tip of the blade body 090. The cables of the multiple cable sockets 094 are manufactured integrally with the blade body 090.

[0028] The present invention also provides a method for using a rotor tip light device in a rotorcraft, the method comprising:

[0029] In the absence of light at night:

[0030] Move the rotorcraft from outside the hangar to inside the hangar. At this time, the rotorcraft's collective pitch is at its lowest, and the light angle of the blade tip light device is adjusted to its maximum, so that the ground crew in the pilot position can always observe the distance between the blades and other obstacles.

[0031] When the rotorcraft is started on the ground with the collective pitch at 0 lift, the rotorcraft is taxiing on the ground. The illumination angle of the propeller tip light device is adjusted to the first illumination angle so that the pilot in the pilot's seat can observe the distance between the propeller blades and other obstacles; the first illumination angle is less than the maximum illumination angle.

[0032] The rotorcraft is started on the ground, with the rotor blades at the maximum lift position, ready for takeoff. The illumination angle of the rotor tip lights is adjusted to be less than the first illumination angle.

[0033] Furthermore, the method includes:

[0034] In the absence of light at night:

[0035] When rotorcraft fly in formation, the wingman adjusts the beam angle of the propeller tip light device to the minimum beam angle so that the wingman can observe the position of the lead aircraft and judge the formation distance based on the propeller disk outline.

[0036] In this invention, the rotor blade tip light is installed on the tip structure of the rotor blade. It is a light-emitting device that provides a schematic diagram of the rotor disk outline on the ground or in the air, eliminating the need to turn on all lights in the hangar at night and preventing collisions between the rotor blades and the hangar or other aircraft. During nighttime formation flying, it displays the range of motion of the large rotor blades, helping wingmen determine their relative position and distance to the lead aircraft and avoiding mid-air collisions. The rotor blade tip light is installed at the front of the rotor blade tip, and its luminous surface matches the airfoil of the blade tip, preventing aerodynamic damage caused by adding light to the rotor blade, which would affect the rotor's aerodynamic lift and noise. The rotor blade tip light uses a bolt-fixed and sealed gasket structure, reducing the cumbersome procedure of disassembly and assembly using a screwdriver under normal circumstances, improving disassembly and assembly efficiency, and greatly enhancing maintenance efficiency. The rotor blade tip light utilizes a multi-channel power supply and employs connectors at the blade tips, significantly improving reliability. The cables are pre-embedded within the blade beam, adapting well to the blade structure and featuring a universal design. A light shield is added to the rotor blade tip light's illumination range, allowing for adjustable illumination angles to meet the visibility requirements at the blade tips. The rotor blade tip light offers multiple illumination modes and brightness adjustments, operating in both conventional and infrared modes, facilitating the provision of a full aircraft silhouette during covert operations in law enforcement and law enforcement situations. The rotor blade tip light also features blade counterweight adjustment, eliminating weight errors introduced during component manufacturing and providing rapid adjustment for the dynamic and static balance of the blades. Attached Figure Description

[0037] Figure 1 A diagram of a rotor blade tip light device provided in an embodiment of the present invention;

[0038] Figure 2 A diagram showing the position of the propeller tip light on the propeller blade, provided in an embodiment of the present invention;

[0039] Figure 3 This is a diagram showing the connection between the propeller tip light and the propeller blade, provided in an embodiment of the present invention.

[0040] Figure 4 A diagram illustrating the composition of the paddle tip lamp provided in an embodiment of the present invention;

[0041] Figure 5 This is a diagram illustrating the composition of the paddle tip lamp light-emitting body provided in an embodiment of the present invention;

[0042] Figure 6 A scene analysis diagram of paddle tip lights in a formation scenario provided in an embodiment of the present invention;

[0043] Figure 7 This is a trapezoidal formation scene diagram provided in an embodiment of the present invention;

[0044] Figure 8A scene analysis diagram of a paddle lamp on the ground provided in an embodiment of the present invention;

[0045] Figure 9 The light emission angle requirements of the paddle tip lamp provided in the embodiments of the present invention;

[0046] Figure 10 The external field-of-view projection curve of the rotor tip lamp at the lowest position provided in the embodiment of the present invention;

[0047] Figure 11 The external field-of-view projection curve of the rotor reference position propeller tip lamp provided in the embodiment of the present invention;

[0048] Figure 12 The external field-of-view projection curve of the rotor tip lamp at the highest initial position provided in the embodiments of the present invention;

[0049] Figure 13 A schematic diagram of the visual angle of a wingman observing the formation lights of a lead aircraft, provided in an embodiment of the present invention;

[0050] Figure 14 This is a schematic diagram of the conformal design of the transparent cover provided in an embodiment of the present invention;

[0051] Figure 15 This is a schematic diagram of the conformal design of the left and right wing ribs provided in an embodiment of the present invention;

[0052] Figure 16 This is a schematic diagram illustrating the adjustment of the light emission angle of the emitter according to an embodiment of the present invention. Detailed Implementation

[0053] The technical solution of the present invention will be described in detail below with reference to the accompanying drawings.

[0054] This invention relates to a propeller tip light for a rotorcraft, see Figures 1-5 As shown.

[0055] The rotor blade tip light 001 is made by Figure 1 Located inside the fairing at the tip of the propeller blade, the transparent housing of the propeller tip light 001 adopts a conformal penetration design, enabling the light-emitting device to emit light to meet the needs of ground crew and pilots in the air.

[0056] The rotor blades of the rotorcraft are made of 100 Figure 2 The blade consists of a blade tip light 001, a blade body 090, a leading edge sheath 091, and a cable plug 092. The blade tip light 001 is located at the tip of the blade, and its shape is consistent with the theoretical aerodynamic shape of the blade design. It is connected to the blade body 090 by bolts and other connecting parts.

[0057] The propeller tip light 001 and the propeller body 090 are mechanically and electrically connected via the propeller tip bracket 093 and the cable socket 094, such as... Figure 3As shown, a blade tip support 093 and a cable socket 094 are pre-installed at the tip of the blade body 090. The blade tip support 093 is a high-strength structural component with pre-installed connecting threads and is manufactured integrally with the blade body 090. To improve the reliability of the blade tip lamp 001, two or more cable sockets 094 are arranged in a limited space. The cables of the multi-channel cable socket 094 are manufactured integrally with the blade body 090.

[0058] The rotor blade tip light 001 is made by Figure 4 The propeller consists of: a propeller tip cover 002, a right wing rib 003, a left wing rib 004, mounting bolts 005, and a propeller tip lamp light-emitting body 010. The propeller tip cover 002 is a thin-walled structure made of metal or composite materials, and foam is filled around the right wing rib 003 and left wing rib 004 to meet the aerodynamic requirements of the high-speed rotation of the propeller blades. The dimensions of the right wing rib 003 and left wing rib 004 are determined according to the propeller blade airfoil and the dimensions of the propeller tip lamp light-emitting body 010.

[0059] The main body of the paddle tip lamp 010 is composed of Figure 5 The propeller blade consists of: a transparent cover 011, a first sealing gasket 012, a second sealing gasket 013, a light shield 014, a fixing bolt 015, a light emitter 016, a cable 017, a base 018, a counterweight 019, a counterweight bolt 020, and a plug 021. The transparent cover 011 is made of transparent material, and its shape matches the airfoil of the propeller blade. The first sealing gasket 012 and the second sealing gasket 013 are placed between the transparent cover 011 and the propeller tip cover 002 to prevent electrostatic corrosion, frictional corrosion, and moisture ingress. The light shield 014 is made of an opaque plastic sheet, its concave shape fitting the bottom of the light emitter 016, and can be cut to size as needed. The light emitter 016 is an LED or laser array with visible and infrared light, adjustable brightness, and a beam angle greater than 210°. The base 018 is a metal alloy part with a concave inner cavity, which can be used to install the light emitter 016, which is fixed by fixing bolts 015. A space for a cable 017 is reserved in the concave part of the base, and an interface for installing the counterweight 019 and counterweight bolts 020 is also provided. The counterweight 019 consists of a vulcanized rubber layer and a steel core, and is a configuration of multiple cylindrical pads. It is fixed to the groove in the inner cavity of the base 018 with counterweight bolts 020, holding the counterweight 019 in a specified position.

[0060] To ensure that the rotor tip lights of rotorcraft meet operational requirements, a detailed and comprehensive design process was developed based on the forward design approach of systems engineering and in accordance with airworthiness requirements. The proposed rotor tip light device is closely integrated with the rotor structure of the rotorcraft, and its implementation is clear and feasible, greatly improving the safety of rotorcraft during ground maintenance operations or formation flights at night or in adverse weather conditions.

[0061] Step 1: Analyze the ground usage scenarios for rotorcraft tip lights (S1).

[0062] Step 2: Review the aerial use scenarios of rotorcraft tip lights (S2).

[0063] Step 3: Complete the usage requirements of the paddle tip light based on the usage scenario (S3).

[0064] Step 4: Conduct a visibility assessment of the paddle tip light based on typical usage scenarios (S4).

[0065] Step 5: Conduct test flights of rotorcraft propeller tip lights based on the scenario (S5).

[0066] The ground usage scenarios for rotorcraft tip lights include: Moving a rotorcraft from outside to inside the hangar in complete darkness at night. At this point, the rotorcraft's collective pitch is at its lowest; ground crew in the cockpit should constantly observe the distance between the rotor blades and other obstacles. Starting the rotorcraft on the ground in complete darkness at night, with the collective pitch at 0 lift, the pilot in the cockpit should observe the approximate distance between the rotor blades and other obstacles. Starting the rotorcraft on the ground in complete darkness at night, with the rotor blades at maximum lift, preparing for takeoff. At this point, the pilot in the cockpit should not easily observe the rotor blade position unless specifically looking for it.

[0067] The aerial usage scenarios for rotorcraft tip lights include: close formation flight of rotorcraft in low-light conditions at night, where wingmen constantly observe the lead aircraft's position and determine formation distance based on the rotor disc outline. Due to the different performance and speeds of the helicopters within the formation, each type of helicopter typically adjusts its speed to form a flight formation en route to the starting point. Formation formation primarily depends on weather and enemy activity. Under simple daytime weather conditions, multi-aircraft formations are usually employed, with batches following each other, maintaining a certain time interval between waves and batches. Figure 6 As shown. Wave formations can be dense, sparse, or dispersed in a "trapezoidal" pattern (see...). Figure 7 As shown in Table 1, the relative angles of pilots during formation of each crew in "straight", "staggered", "parallel", and "cruising" formations are as follows.

[0068] Table 1. Relative angles of pilots during crew formation.

[0069]

[0070] Visibility assessment of rotor tip lights in ground use scenarios for rotorcraft: Based on the arrangement requirements of the rotor tip lights and the actual digital model, an electronic prototype evaluation is conducted. When the rotorcraft is parked on the ground, based on the overall aerodynamic shape, with the collective pitch stick at its lowest position and the Design Eye Point (DEP) as the reference, the rotor's droop relative to the forward fuselage is 20°. The external field-of-view projection of the rotor tip lights is plotted, with the thick red line representing the projection. It can be seen that the lights are visible through the left windshield, middle windshield, right windshield, left cabin door, and right cabin door. (See...) Figure 10 As shown; with the collective pitch at 0°, the Design Eye Point (DEP) is used as the reference. At this time, the rotor is perpendicular to the main shaft. The external field of view projection of the propeller tip light is plotted, with the thick black line representing its projection. It can be seen that it is visible on the left and right roof glass and the middle windshield. Figure 11 As shown; when the collective pitch lever is raised, the rotor flaps at its maximum, forming a 15° cone with the initial plane. A projection of the propeller tip light's external field of view is made, with the thick blue line representing its projection. It can be seen that the light is visible through the right-hand roof glass. Figure 12 As shown. By considering the angles of the collective pitch rods on the ground, the position of the propeller tip lights in the external field of view projection is clearly analyzed to determine the rationality of the propeller tip light arrangement, such as... Figure 8 As shown.

[0071] Based on the usage scenarios, the following requirements for propeller tip lights were met: The propeller tip lights of rotorcraft should be located at the tips of the blades; the propeller tip lights should conform to the rotor's starting profile; the design of the propeller tip lights should meet the static and dynamic balance requirements of the blades; the propeller tip lights should be capable of emitting visible light at night; the propeller tip lights should be capable of emitting infrared light in low-visibility concealment environments; the beam angle of the propeller tip lights should be adjustable to meet the requirements for ground and air use, such as... Figure 9 As shown; the propeller tip lamp should be able to withstand cyclic alternating loads; the propeller tip lamp should meet general quality characteristics requirements; the propeller tip lamp should have high reliability.

[0072] Visibility Assessment of Rotor Tip Lights in Aerial Use Scenarios: During formation flying, the rotor blades rotate at high speeds. Due to the persistence of vision in the human eye, the illumination of the rotor tip lights creates a circular trajectory. Pilots can easily judge the distance between two aircraft by observing the rotor disc outline. Based on Table 1, the relative angle and distance between the wingman and the lead aircraft are listed for each formation scenario. A detailed analysis is conducted, and the visibility of the rotor tip lights is provided. Figure 13 As shown.

[0073] Specifically, in this invention, a rotor blade tip light 001 is installed on the tip structure of a rotor blade and serves as a light-emitting device. A transparent cover 011 conforms to the airfoil of the blade 100 and penetrates the upper and lower surfaces of the blade tip. Its conformal design is described in [details omitted]. Figure 14As shown. The rotor blade tip light 001 has a counterweight 020 to meet the static and dynamic balance adjustment of the blade. An adjustable number of counterweights 020 are used, which are fixed to the grooves inside the base 018 by counterweight bolts 020, holding the counterweights 019 in a specified position. The rotor blade tip light adopts a conformal rib design, with left rib 003 and right rib 004. Left rib 003 and right rib 004 are fixed to the base 018, capable of meeting cyclic alternating loads and effectively transmitting aerodynamic loads. The conformal design is shown in [reference needed]. Figure 15 As shown, cross-sections at distances of 60mm and 163mm from the edge of the rotor tip cover 002 are extracted along the rotor radial direction to create the left wing rib 004 and right wing rib 003, respectively. After strength optimization, a reduced opening is created to form the wing rib design. The rotor tip light of the rotorcraft has a wide viewing angle and achieves adjustable light emission angle through circuit control of the light-emitting array, eliminating the need for rotating mechanical structures. The emitter 016 is an LED with visible and infrared light and adjustable brightness. Each row of LEDs on the emitter 016 can emit light individually. The light shield 014 works in conjunction with the emitter 016 to form an electrically adjustable variable-angle light-emitting device. See Figure 16 As shown, the rotor blade tip light employs a conformal wing sealing strip design to prevent electrostatic corrosion, frictional corrosion, and moisture ingress. This design presents a method for rotor blade tip light design based on a systems engineering forward design approach.

[0074] In this invention, the rotor blade tip light is installed on the tip structure of the rotor blade. It is a light-emitting device that provides a schematic diagram of the rotor disk outline on the ground or in the air, eliminating the need to turn on all lights in the hangar at night and preventing collisions between the rotor blades and the hangar or other aircraft. During nighttime formation flying, it displays the range of motion of the large rotor blades, helping wingmen determine their relative position and distance to the lead aircraft and avoiding mid-air collisions. The rotor blade tip light is installed at the front of the rotor blade tip, and its luminous surface matches the airfoil of the blade tip, preventing aerodynamic damage caused by adding light to the rotor blade, which would affect the rotor's aerodynamic lift and noise. The rotor blade tip light uses a bolt-fixed and sealed gasket structure, reducing the cumbersome procedure of disassembly and assembly using a screwdriver under normal circumstances, improving disassembly and assembly efficiency, and greatly enhancing maintenance efficiency. The rotor blade tip light utilizes a multi-channel power supply and employs connectors at the blade tips, significantly improving reliability. The cables are pre-embedded within the blade beam, adapting well to the blade structure and featuring a universal design. A light shield is added to the rotor blade tip light's illumination range, allowing for adjustable illumination angles to meet the visibility requirements at the blade tips. The rotor blade tip light offers multiple illumination modes and brightness adjustments, operating in both conventional and infrared modes, facilitating the provision of a full aircraft silhouette during covert operations in law enforcement and law enforcement situations. The rotor blade tip light also features blade counterweight adjustment, eliminating weight errors introduced during component manufacturing and providing rapid adjustment for the dynamic and static balance of the blades.

Claims

1. A rotor tip light device for a rotary-wing aircraft, characterized in that, The propeller tip light device is disposed within the fairing at the tip of the propeller blade, and the propeller tip light device includes: Propeller tip cover (002), right wing rib (003), left wing rib (004), mounting bolt (005), propeller tip lamp light body (010); The propeller tip cover (002) adopts a thin-walled structure of metal or composite material, and is filled with foam on the outside of the right wing rib (003) and left wing rib (004). The right wing rib (003) and left wing rib (004) are determined according to the airfoil of the propeller blade and the size of the propeller tip lamp light body (010).

2. The rotor tip light device for a rotary-wing aircraft according to claim 1, characterized in that, Along the rotor radial direction, select cross sections at distances of 60mm and 163mm from the edge of the rotor tip cover (002) to construct the left wing rib (004) and the right wing rib (003) respectively.

3. The rotor tip light device for a rotary-wing aircraft according to claim 1, characterized in that, The paddle tip lamp light-emitting body (010) includes: a transparent cover (011), a first sealing gasket (012), a second sealing gasket (013), a light shield (014), a fixing bolt (015), a light emitter (016), a cable (017), a base (018), a counterweight (019), a counterweight bolt (020), and a plug (021); The transparent cover (011) is made of transparent material and its shape is consistent with the airfoil of the propeller blade; The first sealing gasket (012) and the second sealing gasket (013) are placed between the transparent cover (011) and the paddle tip cover (002), and are conformal to the transparent cover (011); The light shield (014) is made of an opaque plastic sheet, which is concave in shape and fits into the bottom of the light emitter (016); The light emitter (016) is an LED with visible light and infrared light, adjustable brightness, and a light emission angle greater than 210°; The base (018) is a metal alloy part with a concave inner cavity, used to install the light emitter (016). The base (018) and the light emitter (016) are both fixed by fixing bolts (015). A space is reserved in the concave part of the base for a cable (017) channel, and an installation interface is reserved for the counterweight (019) and counterweight bolt (020); The counterweight (019) is composed of a vulcanized rubber layer and a steel core, and is a configuration of multiple cylindrical pads. It is fixed to the groove in the inner cavity of the base (018) by counterweight bolts (020).

4. The rotor tip light device for a rotary-wing aircraft according to claim 3, characterized in that, The light emitter (016) is equipped with multiple rows of LEDs, each row of LEDs can emit light independently, and each row of LEDs has a different emission angle through the light shield (014). By controlling the light emission of different rows of LEDs, a light-emitting device with a variable angle is formed.

5. A rotor blade for a rotary-wing aircraft, characterized in that, The blade includes: a blade tip light device as described in any one of claims 1-4, a blade body (090), a leading edge cladding (091), and a cable plug (092); The tip lamp is located at the tip of the blade, and its shape is consistent with the theoretical aerodynamic shape of the blade design. It is connected to the blade body (090) through a connector.

6. The rotor blade of a rotary-wing aircraft according to claim 5, characterized in that, The connector includes: a propeller tip bracket (093) and a cable socket (094); used to realize the mechanical and electrical connection of the propeller tip lamp device; A blade tip bracket (093) and a cable socket (094) are reserved at the tip of the blade body (090). The blade tip bracket (093) is a high-strength structural component with reserved connecting threads, which is integrally manufactured with the blade body (090). Two or more cable sockets (094) are arranged inside the tip of the blade body (090). The cables of the multiple cable sockets (094) are integrally manufactured with the blade body (090).

7. A method of using a rotor tip light device for a rotary-wing aircraft, characterized in that, The method is implemented using the paddle tip lamp device as described in any one of claims 1-4, and the method includes: In the absence of light at night: Move the rotorcraft from outside the hangar to inside the hangar. At this time, the rotorcraft's collective pitch is at its lowest, and the light angle of the blade tip light device is adjusted to its maximum, so that the ground crew in the pilot position can always observe the distance between the blades and other obstacles. When the rotorcraft is started on the ground with the collective pitch at 0 lift, the rotorcraft is taxiing on the ground. The illumination angle of the propeller tip light device is adjusted to the first illumination angle so that the pilot in the pilot's seat can observe the distance between the propeller blades and other obstacles; the first illumination angle is less than the maximum illumination angle. The rotorcraft is started on the ground, with the rotor blades at the maximum lift position, ready for takeoff. The illumination angle of the rotor tip lights is adjusted to be less than the first illumination angle.

8. The method of using the propeller tip light device of a rotorcraft according to claim 7, characterized in that, The method includes: In the absence of light at night: When rotorcraft fly in formation, the wingman adjusts the beam angle of the propeller tip light device to the minimum beam angle so that the wingman can observe the position of the lead aircraft and judge the formation distance based on the propeller disk outline.

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