Rotor wing device capable of transmitting information

Abstract

The utility model discloses a rotor device capable of transmitting information, and belongs to the technical field of aviation information interaction. According to the rotor wing device, display units (including LED light bands / lamp beads or light reflecting units) are integrated on the rotor wings of the helicopter, the constant-speed rotation characteristic of the rotor wings is utilized, the time sequence of light emitting or signal reflecting is controlled, and continuous characters, symbols, warning or image information is formed in the air. The display part adopts a thin or embedded design, does not influence the aerodynamic performance of the rotor wing, can be applied to scenes such as post-disaster rescue and wartime radio silence, and realizes information interaction without communication dependence between the helicopter and the ground. Compared with a traditional wireless or fixed display screen, the device has the advantages of being feasible in information transmission, high in anti-interference performance, high in concealment, wide in dynamic display range and the like.

Description

Technical Field

[0001] This application relates to the field of aircraft information transmission technology, specifically to a rotor device capable of transmitting information, which is particularly suitable for scenarios where electromagnetic radiation information transmission is lacking or cannot be used, such as rescue missions and covert military communications. Background Technology

[0002] In scenarios such as natural disasters and war, conventional radio communication has serious shortcomings: disasters such as earthquakes can damage communication base stations, causing communication interruptions that severely hinder disaster relief efforts; in military operations, enemy electronic interference and radio detection limit the effectiveness of communication, especially during radio silence when electromagnetic radiation information transmission is not possible, and information interruptions can even affect the course of war. Existing solutions include: reflective markings (traditional military ground-to-ground signal boards), but these cannot dynamically update information and depend on lighting conditions; flag signals or light signals are not effective due to the instability of helicopters and require professional assistance, making air-to-ground information transmission both unstable and inefficient.

[0003] Based on the constant speed characteristics of helicopter rotors, this application proposes a technical solution that integrates dynamic light sources / reflective units into the rotor body, comprehensively addressing the core pain points of existing technologies. Summary of the Invention

[0004] The purpose of this application is to provide a rotor device capable of transmitting information to solve the problem of air-to-ground information transmission when radio communication is not available or is not possible.

[0005] The technical solution of this application includes: a rotor device capable of transmitting information, comprising a rotor part, a display part, a control part, and a power unit; the rotor part is a rotor body and a drive unit; the display part is a sheet mounted on the rotor body, and the maximum height of the protruding rotor surface is ≤1% of the rotor thickness, the display part displays text, symbols, or images to transmit information; the control part is a dynamic synchronous control, including a rotor speed sensor, an angle decoder, a display timing generator, and a transmission unit.

[0006] Furthermore, the transmission unit is in wired transmission mode, transmitting control and power through an electrical isolation device unit on the drive unit, wherein the electrical isolation device is a slip ring.

[0007] Furthermore, the display portion is a self-emissive module, which is composed of surface-mount LEDs, and the curvature deviation between its mounting plane and the rotor surface is <0.1mm.

[0008] Furthermore, the surface-mount LED integrates a PWM dimming chip.

[0009] Furthermore, the transmission unit is in wireless transmission mode. The transmitting unit of the control part transmits control signals, which are received by the receiving unit of the display part to control the display part. The wireless transmission mode supports LoRa / WiFi6 dual-mode communication protocol. The display part is powered by a sensing unit on it. The sensing unit is an induction coil, a power storage circuit, and an excitation unit. The induction coil and the power storage circuit are installed on the rotor, and the excitation unit is correspondingly installed on the fuselage.

[0010] Furthermore, the display portion is a reflection module, which contains regularly arranged microprism structures with a unit size of 20-200μm and a reflection efficiency of >85%.

[0011] Furthermore, the microprism array is coated with a composite reflective film layer.

[0012] Furthermore, the dynamic synchronization control of the control section includes an optimized autoregressive data processing algorithm and a de-jitter filtering algorithm to eliminate image jitter caused by speed fluctuations.

[0013] Furthermore, the display section can be controlled in segments, divided into 3-12 independent control areas along the rotor span.

[0014] Furthermore, rotor imaging transmits encoded information including geographic coordinates, material requirements, warnings, and alerts.

[0015] The beneficial effects of this application are as follows: This application discloses a rotor device capable of transmitting information. By integrating a display unit (including LED light strips / light beads or reflective units) on the helicopter rotor, and utilizing the constant speed rotation of the rotor, the timing of the emitted or reflected signals is controlled to form continuous text, symbols, or image information in the air. The use of helicopter rotors to display text, symbols, warnings, images, and other information solves the problem of air-to-ground information transmission when radio is unavailable. The display unit of this application is thin or embedded, which does not affect the aerodynamic performance of the rotor. It can be applied to scenarios such as disaster relief and wartime radio silence, realizing communication-free information interaction between helicopters and the ground. Compared with traditional radio or fixed display screens, this device has advantages such as feasible information transmission, strong anti-interference, high concealment, and wide dynamic display range. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of a rotor device capable of transmitting information according to this application.

[0017] Figure 2 This is a schematic diagram illustrating the information transmission of a rotor device capable of transmitting information according to this application.

[0018] Figure descriptions: 100 - Rotor section; 101 - Rotor body; 102 - Drive unit; 200 - Display section; 201 - Self-illuminating module / reflection module; 202 - Laser generator; 203 - Display information illustration; 300 - Control section; 400 - Power unit; 500 - Helicopter. Detailed Implementation

[0019] In the description of this application, it should be noted that the terms "center", "upper", "lower", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only used to simplify the description of the present invention and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the present invention.

[0020] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0021] like Figure 1-2 As shown, this application discloses a rotor device capable of transmitting information. This device is mounted on the upper part of a helicopter 500 and includes a rotor section 100, a display section 200, a control section 300, and a power unit 400. The rotor section 100 is located on the upper part of the helicopter 500 fuselage and consists of a rotor body 101 and a drive unit 102. The drive unit 102 drives the rotor body 101 to rotate, enabling the helicopter 500 to perform flight functions such as ascent, descent, and landing. The display section 200 is a sheet-like structure mounted on the rotor body 101, with the maximum protrusion height on the rotor surface ≤ 1% of the rotor thickness, reducing drag during rotor rotation and ensuring the aerodynamic characteristics of the rotor. The rotor 200 displays text, symbols, or images while rotating, dynamically conveying specific information in real time, such as warnings through continuous rapid flashing. The control unit 300 is mounted on the fuselage of the helicopter 500 and is capable of dynamic synchronous control. It includes a rotor speed sensor, an angle decoder, a display timing generator, and a transmission unit. The power unit 400 is powered by a battery or a hybrid induction and battery system, providing power to the control and display units and adjusting the different display information (schematic 203) of the display unit 200. Furthermore, the power unit 400 is distributed at the power consumption points. Example 1

[0022] The display portion 200 is embedded, with an embedded mounting groove (depth < 20% of rotor thickness) opened on the surface of the rotor body 101 to embed the display portion 200.

[0023] Furthermore, the mounting groove is mounted on a trapezoidal groove with a machining depth of 3mm at the leading edge of the rotor.

[0024] Furthermore, the display portion 200 is a self-emissive module 201, which is composed of surface-mount LEDs and is in sheet or film form. The curvature deviation between its mounting plane and the rotor surface is <0.1mm, reducing wind resistance during rotor rotation. Furthermore, the self-emissive module 201 refreshes at a frequency of 400-800Hz to form a visual persistence pattern. Preferably, the LED driving circuit integrates a PWM dimming chip, and the LEDs are high-brightness flexible LED strips (spacing ≤3mm) covered with a light-transmitting and wear-resistant polycarbonate layer (0.2mm thick) to protect the LED strips. Furthermore, the transmission unit of the self-emissive module 201 is a wired transmission mode, transmitting control and power through a slip ring unit on the driving unit.

[0025] Furthermore, the dynamic synchronization control of the control section 300 includes an optimized autoregressive data processing algorithm and a de-jitter filtering algorithm to eliminate image jitter caused by rotation speed fluctuations; preferably, the timing controller is an FPGA timing controller with a trigger accuracy of 0.1ms, and is equipped with a light intensity adjustment module that automatically compensates for brightness according to ambient light, thereby synchronously coordinating rotor rotation and LED light emission / laser emission to stabilize the information transmission displayed through the rotor.

[0026] Furthermore, the display section 200 can be segmented and divided into 3-12 independent control areas along the rotor span, which improves the ability of the display section 200 to display information 203.

[0027] Furthermore, rotor imaging can transmit coded information including geographic coordinates and material requirements.

[0028] Furthermore, the control module reads the rotation speed signal and operates according to the following timing sequence: 1. Each revolution is divided into 512 angle intervals (0.703° resolution); 2. The FPGA triggers the corresponding LED according to the pre-stored character coordinates (such as the rescue sign "+"); 3. The brightness adaptive algorithm adjusts the output current (range 5-50mA). Example 2

[0029] The display section 200 is a reflection module, with a microprism array laser-etched on the upper surface of the rotor, in conjunction with an airborne Nd:YAG pulsed laser generator 202.

[0030] Furthermore, the reflection module 201 includes regularly arranged microprism structures with unit sizes of 20-200 μm and a reflection efficiency >85%. The microprism array is coated with a composite reflective film to facilitate reflection and ensure the aerodynamic characteristics of the wing surface. Furthermore, the airborne pulsed laser generator 202 of the reflection module 201 emits laser light (wavelength 532 nm / 650 nm), which generates an image through spatiotemporal encoding of reflection points on the rotor body 101. Preferably, the microprism array unit size is 50 μm × 50 μm, and the composite reflective wax layer is a highly reflective metal coating. Furthermore, the transmission unit of the reflection module 201 is in wireless transmission mode. The transmitting unit of the control part 300 transmits control signals, which are received by the receiving unit of the display part 200 to control the display part 200. The wireless transmission mode supports LoRa / WiFi6 dual-mode communication protocol. The display part 200 is powered by the sensing unit on it. The sensing unit is an induction coil, a power storage circuit, and an excitation unit. The induction coil and the power storage circuit are installed on the rotor. The power storage circuit balances and stores power to provide stable power supply. The excitation unit is correspondingly installed on the fuselage.

[0031] Furthermore, the control module reads the rotation speed signal and operates according to the following timing sequence: 1. The laser is synchronized with the rotor angle encoder; 2. The reflected light spot density is controlled by a 50ns pulse width; 3. A high-sensitivity CCD imaging system is set up at the ground observation point.

[0032] Technical verification data was obtained through experiments on a rotor device capable of transmitting information according to this application:

[0033] 1. Wind tunnel test: Aerodynamic efficiency loss in the light strip area at a wind speed of 300 km / h < 2.1%;

[0034] 2. Display clarity: Characters 25cm high can be recognized at a distance of 200m;

[0035] 3. Anti-interference test: The reflection mode maintains a 72% recognition rate in rainy and foggy weather. Example 3

[0036] The display unit 200 is installed on the tail rotor of the helicopter 500. It uses the rotation imaging of the tail rotor to transmit information. The coded information is transmitted in multiple dimensions through the rotation imaging of the upper and tail rotors of the helicopter, which improves the ability of the display unit 200 to display information 203. This information can be a flashing warning information to remind ground crew and other personnel to take evasive action during takeoff preparation or landing to avoid accidents.

[0037] The various embodiments in this specification are described in a related manner. The same or similar parts between the various embodiments can be referred to each other. Each embodiment focuses on describing the differences from other embodiments.

Claims

1. A rotor device capable of transmitting information, characterized in that... include: The system comprises a rotor section, a display section, a control section, and a power unit; the rotor section consists of a rotor body and a drive unit; the display section is a sheet mounted on the rotor body, with the maximum protrusion height on the rotor surface ≤ 1% of the rotor thickness, and displays text, symbols, warnings, or images to convey information; the control section is a dynamic synchronous control system, including a rotor speed sensor, an angle decoder, a display timing generator, and a transmission unit.

2. The rotor device capable of transmitting information according to claim 1, characterized in that: The transmission unit is a wired transmission mode, transmitting control and power through an electrical isolation device unit on the drive unit, wherein the electrical isolation device is a slip ring.

3. A rotor device capable of transmitting information according to claim 2, characterized in that: The display section is a self-emissive module, which is composed of surface-mount LEDs, and the curvature deviation between its mounting plane and the rotor surface is <0.1mm.

4. A rotor device capable of transmitting information according to claim 3, characterized in that: The surface-mount LED integrated PWM dimming chip.

5. A rotor device capable of transmitting information according to claim 1, characterized in that... The transmission unit is in wireless transmission mode. The transmitting unit of the control part transmits control signals, which are received by the receiving unit of the display part to control the display part. The wireless transmission mode supports LoRa / WiFi6 dual-mode communication protocol. The display part is powered by sensing units on it. The sensing units are induction coils, power storage circuits and excitation units. The induction coils and power storage circuits are installed on the rotor, and the excitation units are correspondingly installed on the fuselage.

6. A rotor device capable of transmitting information according to claim 1, characterized in that: The display part is a reflection module, which contains regularly arranged microprism structures with a unit size of 20-200μm and a reflection efficiency of >85%.

7. A rotor device capable of transmitting information according to claim 6, characterized in that: The microprism array is coated with a composite reflective film.

8. A rotor device capable of transmitting information according to claim 1, characterized in that: The dynamic synchronization control of the control section includes an optimized autoregressive data processing algorithm and a de-jitter filtering algorithm to eliminate image jitter caused by speed fluctuations.

9. A rotor device capable of transmitting information according to claim 3 or 4, characterized in that: The display section can be controlled in segments, divided into 3-12 independent control areas along the rotor span.

10. A rotor device capable of transmitting information according to claim 1, characterized in that: Rotor imaging transmits coded information containing geographic coordinates and material requirements.

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