An ice detection device for a helicopter

Abstract

The application discloses an icing detection device for a helicopter. The device comprises a self-rotating support rod (6) provided with a hovering probe main body (5) extending radially outward, the support rod (6) is provided with a flight state icing detection assembly on a windward surface, and the hovering probe main body (5) is provided with a hovering state icing detection assembly on an outer wall surface. The application effectively solves the icing detection problem of large rotor unmanned aerial vehicles in high-altitude areas.

Description

Technical Field

[0001] This invention belongs to the field of aircraft icing detection technology, specifically relating to an icing detection device for helicopters. Background Technology

[0002] In the field of helicopter icing detection, icing detectors located on the helicopter fuselage typically determine whether the aircraft is in an icing environment based on the principle of resonance. When ice accumulates on the collection rod, the resonant frequency of the collection rod changes. By collecting the frequency signal, it can be determined whether ice has formed on the collection rod. The intensity of icing is determined based on the icing rate and the calculated liquid water content, and finally, an icing alarm signal is output to remind the crew.

[0003] However, this type of resonant icing detector is highly dependent on the airspeed of the helicopter. When the helicopter is hovering or flying at low speed, there is not enough wind speed at the leading edge of the collection rod, resulting in a slow icing rate or difficulty in icing on the collection rod. The icing detector cannot perform its intended function, and the helicopter is in a state where it cannot detect the icing environment, which poses a safety hazard to helicopter personnel and property.

[0004] Furthermore, resonant icing detectors have specific requirements regarding their installation location on helicopters. In certain locations on the helicopter, uneven flow fields can obstruct the airflow that should pass through the detector, causing it to fail to issue timely icing warning signals at critical icing points, thus posing a hazard to the helicopter and personnel.

[0005] Although some resonant detectors have been improved to address the drawback of helicopters relying on airspeed by adding an air intake device to the detector, allowing it to still detect icing while the helicopter is hovering, this air intake detection method is difficult to integrate with airspeed when calculating liquid water content, resulting in a certain deviation between the measured liquid water content and the true value. Summary of the Invention

[0006] The purpose of this invention is to provide an icing detection device for helicopters. This invention effectively solves the problem of icing detection for large rotary-wing UAVs in high-altitude areas.

[0007] The technical solution of the present invention is: an icing detection device for helicopters, comprising a self-rotating support rod, on which a hovering probe body extending radially outward is provided; the support rod is provided with a flight state icing detection component on its windward side, and a hovering state icing detection component is provided on the outer wall of the hovering probe body.

[0008] In the aforementioned icing detection device for helicopters, the support rod is cylindrical in shape, and the windward side of the cylindrical structure is designed with an installation plane for mounting the icing detection components in flight.

[0009] The aforementioned icing detection device for helicopters also includes a flange, a base on the bottom of the flange, a motor drive unit inside the base, and the motor drive unit is connected to a support rod via a drive shaft passing through the flange.

[0010] In the aforementioned icing detection device for helicopters, the flange surface is also provided with an air gap annular groove, the center of which is located on the central axis of the drive shaft, and the air gap annular groove is connected to the air source via air duct A; the support rod and the hovering probe body are provided with air duct B, the air inlet of air duct B is located on the bottom end face of the support rod and aligned with the air gap annular groove, the exhaust port of air duct B is on the side wall of the hovering probe body, and the axis of the exhaust port is parallel to the flange plane.

[0011] In the aforementioned icing detection device for helicopters, the air source is provided by the bleed air from the helicopter engine.

[0012] In the aforementioned icing detection device for helicopters, the bleed air channel A is equipped with a gas pressure regulating valve.

[0013] In the aforementioned icing detection device for helicopters, the hovering icing detection component includes an icing rod A disposed along the axial direction of the hovering probe body on the surface of the hovering probe body, with a photoelectric receiver and a laser emitter respectively disposed at both ends of the icing rod A.

[0014] In the aforementioned icing detection device for helicopters, the flight state icing detection component includes an icing rod B arranged along the axial direction of the support rod on the windward side of the support rod, and photoelectric receiver B and laser emitter B are respectively provided at both ends of the icing rod B.

[0015] In the aforementioned icing detection device for helicopters, ceramic layers are used for insulation between the icing rods A / B and the hovering probe body / support rod.

[0016] In the aforementioned icing detection device for helicopters, the icing rods A / B are made of nickel-chromium alloy and are designed with serpentine wiring to increase resistance.

[0017] The advantages of this invention are: The icing detection device proposed in this invention has the characteristics of high reliability, simple measurement, and strong applicability. There are many mature and reliable solutions for the devices and circuit schemes required to realize this method. The design can be reasonably optimized according to specific circumstances. All devices are commercially available and easy to assemble.

[0018] This invention, by controlling the rotation speed of the support rod, can calculate the icing rate of the current environment using a formula under various helicopter flight speeds. Even in hovering, it can effectively achieve icing detection, providing icing warnings for pilots. Furthermore, this invention employs a dual-redundant probe rotation control method, allowing the probe to be driven by either a motor or bleed air, with both speeds controllable, thus improving product reliability.

[0019] In addition, this invention can also be used in facilities in some high-rise buildings that require icing detection. When used in conjunction with an anemometer, compared with other methods, the icing detector made according to this method can still accurately perform the icing detection function when the wind speed is low, providing convenience for people's production and life.

[0020] Furthermore, this invention can also be extended to scenarios requiring calibration of liquid water content in the air. In some helicopter icing detection tests, a spray rake is used to simulate the actual icing environment. However, due to insufficient wind speed, other similar icing detection devices cannot calibrate the liquid water content of the test environment. Using this invention, the liquid water content of the test environment can be calibrated in the absence of wind, helping testers to more easily adjust the calibration and providing a more accurate liquid water content environment for helicopters.

[0021] Furthermore, this invention can also be extended to the field of large quadcopter drones. In some high-altitude areas, there are situations where large rotary-wing drones are used to transport goods. This invention can be miniaturized and applied to such drones, including reducing the size of the support rod and probe, and replacing them with lighter materials. This effectively solves the problem of icing detection for large rotary-wing drones in high-altitude areas. Attached Figure Description

[0022] Figure 1 This is a structural diagram of the present invention; Figure 2 This is a cross-sectional view of the present invention; Figure 3 This is a schematic diagram of the flange structure of the present invention. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be described in more detail below with reference to the accompanying drawings. The described embodiments are some, but not all, embodiments of this invention. The embodiments described below are exemplary and intended to explain this invention, not to limit it. Based on the embodiments of this invention, other similar embodiments obtained by those skilled in the art without making significant innovations are all within the protection scope of this invention. The embodiments of this invention will be described in detail below.

[0024] To address the issue that icing detectors may not function properly when helicopters are hovering or at low speeds, an icing detection device for helicopters has been designed. The main technical problems it solves are as follows: ① This solves the problem that helicopters cannot effectively collect ice when hovering or at low speeds, which leads to the failure of icing detection. ② Design a reasonable structure to improve the sensitivity and reliability of the icing detector.

[0025] ③ Design dual measurement points and dual measurement modes to save energy.

[0026] The following is in conjunction with the appendix Figure 1 Appendix Figure 2 Appendix Figure 3 The icing detection device for helicopters of the present invention will be described in further detail below. Example 1

[0027] Firstly, as attached Figure 1 Appendix Figure 2 As shown, the present invention discloses an icing detection device for helicopters, which consists of a probe, a support rod, a flange, and a base.

[0028] The probe includes a hovering probe body 5, an icing rod A2, a laser emitter A3, a photoelectric receiver A1, and a heater. The hovering probe body 5 provides mechanical strength support, and the icing rod, located on the probe body, is a conductive sheet, as shown in the attached diagram. Figure 1 As shown, to prevent short circuits, a ceramic layer 13 is used to isolate the icing rod A2 from the hovering probe body 5; the laser emitter A3 and the photoelectric receiver A1 are located at the two ends of the axial direction of the icing rod, respectively, and are fixed with a special clamp, with the center of the laser emitter A3 and the photoelectric receiver A1 on the axis of the center of the icing rod; the heater is located inside the icing rod and the probe body.

[0029] The icing rod A2 is made of nickel-chromium alloy. It can collect ice and also temporarily remove ice by applying a certain voltage to both ends of the rod. Since the resistance of the nickel-chromium alloy icing rod is generally in the tens of milliohms, a large current is required through the icing rod A2 to achieve the desired de-icing power. Therefore, a high-power output transformer is needed for isolation. The secondary coil of the transformer is only connected to the icing rod A2, and the transformer's turns ratio is designed according to the de-icing power of the icing rod A2 and the input voltage of the transformer's primary coil. If it is necessary to increase the resistance of the icing rod, the conductive sheet of the icing rod can be designed with a serpentine wiring pattern.

[0030] Laser emitter A3 uses a laser diode. To avoid the influence of visible light and infrared radiation, a laser diode in the near-infrared wavelength range is used, or the laser diode control signal is modulated by software. Since a normal laser diode has a certain divergence angle, a collimating lens or a fixed-focus lens is installed in front of the laser diode in order to make more of the emitted light received by the photodetector A1. To ensure the stability of the laser diode, a constant current source circuit is used to drive the laser diode.

[0031] The photodetector A1 uses a photodiode that works in conjunction with a laser diode, and employs a transimpedance amplifier circuit to acquire and amplify the light intensity signal. To improve anti-interference capabilities, a filter is added in front of the photodiode to filter out unwanted light.

[0032] The support rod 6 is a circular rod that can rotate 360° around its axis, used to connect the probe 5 and the flange 11, and simultaneously drive the probe 5 to rotate. The rotation of the support rod 6 can be controlled by a motor, and the rotation speed can be adjusted according to the helicopter's flight conditions. A flat surface is provided on the windward side of the support rod 6, where a set of detection devices is designed: an icing rod B10, a laser emitter B9, and a photoelectric receiver B8, for use during medium- or high-speed helicopter flight. The laser emitter B9 and photoelectric receiver B10 on the support rod 6 are identical to those on the probe body.

[0033] When the helicopter is flying at low speed or hovering, the motor drives the support rod 6 to rotate, which in turn rotates the hovering probe body 5, giving the icing rod A2 a certain linear velocity. This allows ice to accumulate even when the helicopter is hovering. The laser emitter A3 and photoelectric receiver A1 located on both sides of the icing rod A2 output alarm signals due to the icing, alerting the crew to the icing situation. When the helicopter is flying at medium or high speed, the motor-driven rotation of the support rod 6 consumes too much energy. Therefore, the icing rod B10 of the support rod 6, the laser emitter B9, and the photoelectric receiver B8 are used for icing detection, ensuring that the icing rod B10 of the support rod 6 always faces the oncoming airflow.

[0034] To prevent the support rod 6 and the hovering probe body 5 from freezing during normal operation, armored heaters are embedded on the surfaces of the support rod 6 and the hovering probe body 5. By designing a reasonable heater layout path, the heaters can achieve the effect of de-icing or preventing ice during heating.

[0035] The base 7 is a cylindrical outer casing, which contains a transmitter drive circuit, a receiver circuit, a heater heating circuit, a motor drive circuit, a calculation circuit, and a power supply circuit. It is connected to other systems through a circular socket 12. Example 2

[0036] In this embodiment, since the motor-driven rotation of the support rod consumes a significant amount of electricity, helicopter engine bleed air can be introduced through the base, allowing the bleed air to flow through the support rod and reach the probe, as shown in the attached diagram. Figure 2 As shown, an exhaust port 4 is opened at the position of the hovering probe body 5. The purpose of probe rotation can also be achieved by using bleed air. In order to avoid the heat of the bleed air affecting the icing process of the icing rod, colder bleed air can be used, and heat insulation material is added between the bleed air pipe and the icing rod.

[0037] In this embodiment, when the probe is rotated by a motor, the motor drives the support rod to rotate around its axis. The support rod and the flange are connected by components such as bearings. The rotation speed of the probe can be controlled by controlling the motor speed. When the probe is rotated by bleed air, the bleed air passes through the air pressure regulating valve, reaches the air gap annular groove 18 of the flange 11, and then passes through the bleed air channel B20 of the support rod 6 and the suspended probe body 5, and is ejected from the exhaust port 4, thus achieving the purpose of bleed air driving the probe 5 to rotate. Example 3

[0038] In this embodiment, by adjusting the motor speed and the air pressure regulating valve, the probe's windward speed can be made equivalent to the helicopter's flight speed, thus improving the accuracy of calculating the icing rate. The following is the formula for calculating the motor speed: V1 = 2πL × V2 + V3 Where V1 is the equivalent aircraft speed, L is the distance from the center point of the probe icing rod to the axis of the support rod, V2 is the motor speed, and V3 is the current aircraft speed. This formula can be used to establish the relationship between the motor speed and the equivalent aircraft speed.

[0039] The rotational speed of the strut can be controlled by adjusting the pressure of the air pressure regulating valve. The calculation formula is as follows: V4 = f(F) V1 = V4 + V3, where V1 is the equivalent aircraft speed, V4 is a function of the strut speed and the air pressure regulating valve pressure, V2 is the motor speed, V3 is the current aircraft speed, and f(F) is a function of the air pressure regulating valve pressure. This formula establishes the relationship between the air pressure regulating valve pressure and the equivalent aircraft speed.

[0040] In summary, the icing detection device for helicopters of this invention uses a motor or bleed air to drive a rotating support rod, which in turn drives a collecting rod to rotate. This provides sufficient wind speed for the icing rod when the helicopter is hovering, enabling icing detection to be completed even when the helicopter is hovering or at low speeds. This method can be used in the field of icing detection to improve the icing warning capability of helicopters when hovering or at low speeds, and has significant practical application value.

[0041] Example 4. An icing detection device for helicopters, see [link to example]. Figure 1-3The system includes a self-rotating support rod 6, on which a hovering probe body 5 extends radially outward. The support rod 6 has a flight icing detection component on its windward side, and the hovering probe body 5 also has a hovering icing detection component on its outer wall. When the helicopter is hovering or at low speed, rotating the support rod 6 will cause the hovering probe body 5 to rotate, enabling icing detection using the hovering icing detection component. When the helicopter is at medium or high speed, the support rod 6 can be fixed in position, allowing for icing detection using the flight icing detection component, thus reducing energy consumption.

[0042] The support rod 6 has an overall cylindrical structure, and the windward side of the cylindrical structure is designed with an installation plane 19 for installing the icing detection component in flight.

[0043] The aforementioned icing detection device for helicopters also includes a flange 11, a base 7 on the bottom surface of the flange 11, a motor drive device 15 inside the base 7, and the motor drive device 15 is connected to the support rod 6 via a drive shaft 17 passing through the flange 11.

[0044] The flange 11 is also provided with an air gap annular groove 18. The center of the air gap annular groove 18 is located on the central axis of the drive shaft 17. The air gap annular groove 18 is connected to the air source through the air intake channel A16. The support rod 6 and the hovering probe body 5 are provided with an air intake channel B20. The air intake port of the air intake channel B20 is located on the bottom end face of the support rod 6 and is aligned with the air gap annular groove 18. The exhaust port 4 of the air intake channel B20 is suspended on the side wall of the hovering probe body 5, and the axis of the exhaust port 4 is parallel to the plane of the flange 11.

[0045] The aforementioned air source is provided by bleed air from the helicopter engine.

[0046] The aforementioned air intake channel A16 is equipped with a gas pressure regulating valve 14.

[0047] The aforementioned hovering icing detection component includes an icing rod A2 axially mounted on the surface of the hovering probe body 5. A photoelectric receiver A1 and a laser emitter A3 are respectively located at both ends of the icing rod A2. In the ice-free state, the photoelectric receiver receives all emitted signals. As ice gradually increases, the received signal gradually decreases due to signal obstruction. The time for one ice growth cycle is recorded during detection. The icing rate is obtained by dividing the ice thickness by the time, thus determining the icing intensity. The liquid water content can be calculated based on the icing rate. The key factor is the wind speed in front of the icing rod. The rotational speed of the rotating probe needs to be converted to the actual linear velocity, and the actual helicopter speed needs to be considered to obtain a relatively accurate wind speed in front of the icing rod. The photoelectric receiver and laser emitter should be selected with low heat generation and low vibration to avoid the influence of heat and vibration on icing detection. The icing rod A2 has a planar ice position on its windward side, facilitating the collection of regular ice shapes and measurement of ice thickness. The laser emitter A3 can be replaced with an ultrasonic, surface wave, or acoustic wave generator, all of which can detect the presence of ice. The support rod and hovering probe body 5 require armored heaters with good insulation. The heaters for the support rod and hovering probe body 5 use flexible heating wires. When arranging the heating wires on the support rod and hovering probe body 5, care should be taken to avoid excessive contact between the heating wires and the transmitting and receiving devices, which could burn out the components.

[0048] The aforementioned flight icing detection component includes an icing rod B10 arranged along the axial direction of the support rod 6 on the windward side of the support rod 6, with a photoelectric receiver B8 and a laser emitter B9 respectively at both ends of the icing rod B10.

[0049] The icing rods A / B are insulated from the hovering probe body 5 / support rod 6 using a ceramic layer 13.

[0050] The icing rods A and B are made of nickel-chromium alloy and feature a serpentine wiring design to increase resistance, facilitating de-icing.

[0051] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the present invention should be included within the scope of protection of the present invention.

Claims

1. An ice detection device for a helicopter, characterized in that, It includes a self-rotating support rod (6), on which a hovering probe body (5) extends radially outward; the support rod (6) is provided with a flight state icing detection component on the windward side, and the hovering probe body (5) is provided with a hovering state icing detection component on the outer wall surface. It also includes a flange (11), a base (7) on the bottom surface of the flange (11), a motor drive device (15) inside the base (7), and the motor drive device (15) is connected to the support rod (6) via a drive shaft (17) passing through the flange (11). The flange (11) surface is also provided with an air gap annular groove (18), the center of which is located on the central axis of the drive shaft (17). The air gap annular groove (18) is connected to the air source through the air intake channel A (16). The support rod (6) and the hovering probe body (5) are provided with an air intake channel B (20). The air intake port of the air intake channel B (20) is located on the bottom end face of the support rod (6) and aligned with the air gap annular groove (18). The exhaust port (4) of the air intake channel B (20) is on the side wall of the hovering probe body (5), and the axis of the exhaust port (4) is parallel to the plane of the flange (11).

2. The icing detection device for helicopters according to claim 1, characterized in that, The support rod (6) has a cylindrical structure, and the windward side of the cylindrical structure is designed with an installation plane (19) for installing the icing detection component in flight.

3. The icing detection device for helicopters according to claim 1, characterized in that, The air source is provided by bleed air from the helicopter engine.

4. The icing detection device for helicopters according to claim 1, characterized in that, The gas venting channel A (16) is equipped with a gas pressure regulating valve (14).

5. The icing detection device for helicopters according to claim 1, characterized in that, The hovering state icing detection component includes an icing rod A (2) arranged along the axial direction of the hovering probe body (5) on the surface of the hovering probe body (5). The two ends of the icing rod A (2) are respectively provided with a photoelectric receiver A (1) and a laser emitter A (3).

6. The icing detection device for helicopters according to claim 1, characterized in that, The flight state icing detection component includes an icing rod B (10) arranged along the axial direction of the support rod (6) on the windward side of the support rod (6), and photoelectric receiver B (8) and laser emitter B (9) are respectively provided at both ends of the icing rod B (10).

7. The icing detection device for helicopters according to claim 5 or 6, characterized in that, A ceramic layer (13) is used to insulate and isolate the icing rod A / B from the hovering probe body (5) / support rod (6).

8. The icing detection device for helicopters according to claim 5 or 6, characterized in that, The icing rods A and B are made of nickel-chromium alloy and feature a serpentine wiring design to increase resistance.

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