Helicopter anti-icing and deicing system applying rotor kinetic energy recovery and operation method

Abstract

The invention relates to the field of helicopter wing anti-icing and deicing, in particular to a helicopter anti-icing and deicing system applying rotor wing kinetic energy recovery and an operation method. The helicopter anti-icing and deicing system applying rotor wing kinetic energy recovery comprises an electric heating deicing device, a kinetic energy recovery device and a helicopter rotor wing key assembly. The electric heating deicing device is composed of a high-resistivity metal heating wire and an icing detector, and the device transfers heat to the surface of the wing for deicing through heating of the high-resistivity heating wire. The kinetic energy recovery device is composed of an electric energy rectification, voltage stabilization and energy storage device, a permanent magnet and a magnetic induction coil. Kinetic energy generated when the rotor rotates is converted into electric energy through the electromagnetic induction technology and stored in a battery pack. The helicopter rotor key assembly is composed of a helicopter blade and a helicopter swash plate and is a key component of the helicopter rotor. According to the invention, the kinetic energy of the helicopter rotor is recovered to prevent and remove ice, so that the overall energy utilization efficiency is improved, and the environmental adaptability and safety of the system are also improved.

Description

Technical Field

[0001] The invention relates to a helicopter anti-icing system and an operating method using rotor kinetic energy recovery, belonging to the field of helicopter wing anti-icing. Background Art

[0002] In a low-temperature and high-humidity flight environment, when a helicopter passes through a cloud layer containing supercooled droplets, the wing surface is easily impacted and ice is formed. This not only affects flight performance, but may also damage the fuselage structure, and in severe cases even lead to flight accidents. At present, helicopters usually use electric thermal anti-icing, mechanical anti-icing, and chemical anti-icing to ensure flight safety and efficiency. However, these traditional anti-icing technologies still face the challenges of high energy consumption and increased weight, which in turn affects fuel efficiency and flight performance. To meet these challenges, the future needs to focus on optimizing system design, improving efficiency, and considering economy and environmental protection to ensure flight safety.

[0003] Some patents have proposed helicopter wing anti-icing technology and its application. Patent CN109558650B designs an analysis method for the impact of helicopter rotor icing on rotor performance. The main feature is to use numerical analysis and simulation technology to determine the parameters of the helicopter rotor anti-icing system and the flight dynamics model, calculate the flow field distribution and ice type structure, compare the aerodynamic characteristics of the airfoil before and after icing, and evaluate the impact of icing on rotor performance, so as to provide a theoretical basis for designing a safer anti-icing system; however, the calculation process is complex and requires a lot of resources, and the accuracy of the model affects the reliability of the results. It still remains in the theoretical analysis stage and is not suitable for dynamic monitoring and adjustment in real-time flight; Patent CN110474279A designs a helicopter-mounted oil-electric hybrid hot water deicing system and its control method, the main feature of which is to use an oil-electric hybrid system, and provide power for the helicopter hot water deicing system through a combination of a gasoline engine, a generator, an electric motor and a battery. The control module of the system controls the operation of each component according to the ice thickness and ambient temperature, optimizes the power combination and energy management, improves deicing efficiency, and reduces energy consumption; however, the system relies on the energy of the helicopter engine, and its use will result in limited helicopter endurance.

[0004] The present invention proposes a helicopter anti-icing system that uses rotor kinetic energy recovery. The electromagnetic induction technology is used to convert the rotor kinetic energy into electrical energy and transfer it to a battery pack for storage. The electrical energy stored in the battery is converted into thermal energy due to resistance heating at the heating wire through an electric heating circuit. The heat is transferred to the wing skin through heat conduction to increase the wing surface temperature to achieve anti-icing. The present invention uses kinetic energy recovery for anti-icing, which improves the overall energy utilization efficiency while reducing greenhouse gas and other harmful emissions, simplifying the system structure, reducing operating costs, and improving the stability of the system and environmental adaptability. Summary of the invention

[0005] The present invention provides a helicopter anti-icing system using rotor kinetic energy recovery, which helps to promote the application of helicopter anti-icing technology and kinetic energy recovery technology.

[0006] The embodiment of the present application provides a helicopter anti-icing system using rotor kinetic energy recovery, which is composed of an electric heating deicing device, a kinetic energy recovery device, and key components of the helicopter rotor;

[0007] The electric deicing device is composed of a first high-resistivity metal heating wire 1-1, a second high-resistivity metal heating wire 1-2, a third high-resistivity metal heating wire 1-3, and an ice detector 5;

[0008] The first high-resistivity metal heating wire 1-1, the second high-resistivity metal heating wire 1-2, and the third high-resistivity metal heating wire 1-3 are respectively arranged between the upper and lower surfaces of the first helicopter blade 6-1, the second helicopter blade 6-2, and the third helicopter blade 6-3, and buried in the helicopter wing; the ice detector 5 is installed on the upper surface of the helicopter blade 6;

[0009] The kinetic energy recovery device is composed of an electric energy rectification, voltage stabilization, energy storage device 2, a first permanent magnet 3-1, a second permanent magnet 3-2, and a magnetic induction coil 4;

[0010] The upper interface of the electric energy rectification, voltage stabilization and energy storage device 2 is connected to the first high-resistance metal heating wire 1-1, the second high-resistance metal heating wire 1-2 and the third high-resistance metal heating wire 1-3 in sequence after passing through the helicopter swash plate 7 through the circuit perforation, and the lower interface of the electric energy rectification, voltage stabilization and energy storage device 2 is connected to the upper interface of the magnetic induction coil 4; the first permanent magnet 3-1 and the second permanent magnet 3-2 are fixedly installed on both sides of the magnetic induction coil 4; the upper interface of the magnetic induction coil 4 is connected to the electric energy rectification, voltage stabilization and energy storage device 2;

[0011] The key components of the helicopter rotor are composed of the helicopter blades 6 and the helicopter swash plate 7;

[0012] The helicopter blade 6 is fixed on the top of the helicopter, and the helicopter swash plate 7 is located below the helicopter blade 6, and the two are connected through a connecting rod mechanical structure.

[0013] Furthermore, the first high-resistivity metal heating wire 1 - 1 , the second high-resistivity metal heating wire 1 - 2 , and the third high-resistivity metal heating wire 1 - 3 are made of nickel-chromium alloy.

[0014] Furthermore, the electric energy rectification, voltage stabilization and energy storage device 2 integrates three modules of rectification circuit, voltage stabilization circuit and energy storage battery pack, and the energy storage battery pack adopts lithium battery.

[0015] Furthermore, the magnetic induction coil 4 of the kinetic energy recovery device is made of copper.

[0016] Furthermore, the method for operating a helicopter anti-icing system using rotor kinetic energy recovery is characterized by:

[0017] It includes two operating methods: helicopter kinetic energy recovery and helicopter electric heating anti-icing;

[0018] How helicopter kinetic energy recovery works:

[0019] During the flight of the helicopter, the rotation of the shaft drives the magnetic induction coil 4 to rotate, so that the magnetic induction coil 4 continuously cuts the magnetic flux lines of the magnetic field formed by the first permanent magnet 3-1 and the second permanent magnet 3-2. The magnetic induction coil 4 generates electricity by electromagnetic induction in a closed loop, and the generated current is transmitted upward along the circuit to the electric energy rectification, voltage stabilization, and energy storage device 2 to convert AC to DC, stabilize the voltage and store it in the lithium battery module. When it is detected that the battery pack is fully charged, the circuit of the magnetic induction coil 4 is disconnected to stop charging. When it is detected that the battery pack power reaches 20%-30%, the circuit of the magnetic induction coil 4 is reconnected to start charging, completing the energy storage cycle of kinetic energy recovery;

[0020] How to operate the helicopter electric heating anti-icing system:

[0021] When the ice detector 5 detects the formation of ice crystals on the leading edge of the wing, the anti-icing system is activated, and the current is transmitted from the electric energy rectification, voltage stabilization, and energy storage device 2 to the first high-resistance metal heating wire 1-1, the second high-resistance metal heating wire 1-2, and the third high-resistance metal heating wire 1-3. The first high-resistance metal heating wire 1-1, the second high-resistance metal heating wire 1-2, and the third high-resistance metal heating wire 1-3 generate heat after being energized. The heat passes through the first high-resistance metal heating wire 1-1, the second high-resistance metal heating wire 1-2, and the third high-resistance metal heating wire 1-3. -2. The third high-resistivity metal heating wire 1-3 is transmitted to the surface of the first helicopter blade 6-1, the second helicopter blade 6-2, and the third helicopter blade 6-3. The surface of the first helicopter blade 6-1, the second helicopter blade 6-2, and the third helicopter blade 6-3 absorbs heat and heats the droplets flowing through the area, thereby increasing the air temperature in the area, heating and melting the ice accumulated on the surface of the helicopter blade 6. When the ice detector 5 does not detect ice accumulation, the electric heating anti-icing circuit is closed, thereby completing a cycle.

[0022] Furthermore, the ice detector 5 is a fiber optic ice detector; the ice detector 5 detects icing by continuously monitoring key parameters of the helicopter surface. Once icing is detected, the ice detector 5 will immediately send an alarm to the flight control system and can trigger the anti-icing system to ensure flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Attached Figure 1 It is a schematic diagram of the appearance of the present invention;

[0024] Attached Figure 1 The reference numbers are as follows: 1-1. First high-resistivity metal heating wire, 1-2. Second high-resistivity metal heating wire, 1-3. Third high-resistivity metal heating wire, 2. Electric energy rectification, voltage stabilization and storage device, 3-1. First permanent magnet, 3-2. Second permanent magnet, 4. Magnetic induction coil, 5-1. First ice detector, 5-2. Second ice detector, 5-3. Third ice detector, 6-1. First helicopter blade, 6-2. Second helicopter blade, 6-3. Third helicopter blade, 7. Helicopter tilt plate.

[0025] Attached Figure 2 This is a partial enlarged view of the first helicopter blade;

[0026] Attached Figure 2 The reference numerals in the figure are as follows: 1-1. first high-resistivity metal heating wire, 5-1. first ice detector, 6-1. first helicopter blade, 7. helicopter tilting plate.

[0027] Attached Figure 3 This is a diagram of some parts of electromagnetic induction power generation;

[0028] Attached Figure 3 The label names are: 2. Electric energy rectification, voltage stabilization, storage device, 3-1. First permanent magnet, 3-2. Second permanent magnet, 4. Magnetic induction coil.

[0029] Attached Figure 4 This is a system operation flow chart of a helicopter anti-icing system that uses rotor kinetic energy recovery. DETAILED DESCRIPTION

[0030] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0031] like Figure 1 As shown, a helicopter anti-icing system using rotor kinetic energy recovery includes a first high-resistance metal heating wire 1-1, a second high-resistance metal heating wire 1-2, a third high-resistance metal heating wire 1-3, an electric energy rectification, voltage stabilization, and storage device 2, a first permanent magnet 3-1, a second permanent magnet 3-2, a magnetic induction coil 4, a first ice detector 5-1, a second ice detector 5-2, a third ice detector 5-3, a first helicopter blade 6-1, a second helicopter blade 6-2, a third helicopter blade 6-3, and a helicopter swash plate 7.

[0032] When the helicopter takes off, the kinetic energy recovery device starts, and the magnetic induction coil 4 continuously cuts the magnetic flux lines in the magnetic field formed by the first permanent magnet 3-1 and the second permanent magnet 3-2 as the main shaft rotates. The magnetic induction coil 4 generates current in a closed loop through electromagnetic induction. The current is transmitted upward to the electric energy rectification, voltage stabilization, and storage device 2 for conversion from AC to DC and stable voltage, and then stored in the lithium battery pack. The kinetic energy recovery device continuously recovers kinetic energy and converts it into electrical energy storage. When the battery pack is fully charged, the system automatically disconnects the loop of the magnetic induction coil and stops charging to protect the battery pack from overcharging damage.

[0033] When the aircraft passes through an icing area during flight, the icing detector 5 determines whether the wing is iced according to the received light signal, makes corresponding instructions and implements anti-icing. The specific deicing method of the present invention is as follows:

[0034] Example 1 detects that the wing is not iced:

[0035] When the aircraft passes through the icing area, the leading edge of the wing hits the supercooled liquid droplets in the atmosphere head-on, and the ice detector 5 does not detect the formation of ice crystals on the wing surface. Figure 1 The ice detector 5 transmits a signal to the digital anti-icing controller, and the anti-icing control panel displays the deicing status. The electric anti-icing switch for deicing does not need to be turned on. Figure 1 The kinetic energy recovery component is in continuous operation, and the system uses electromagnetic induction to recover and store kinetic energy.

[0036] Example 2: Wing icing detected:

[0037] When the temperature of the supercooled droplets further decreases, ice crystals begin to form on the surface of the helicopter blade 6. The ice detector 5 detects the formation of ice crystals and Figure 4 As shown in the figure, a signal is sent to the digital anti-icing controller, and the controller will respond as follows after receiving the signal. Figure 4 The anti-icing control system is started as shown, and a command is sent to start the electric deicing device.

[0038] When the electric heating deicing device is turned on, the high-resistance metal heating wire 1 generates heat due to the Joule heating effect after being energized. Figure 1 As shown, heat is rapidly transferred from the high-resistance metal heating wire 1 to the skin of the helicopter blade 6. The helicopter blade 6 skin absorbs heat and heats the droplets flowing through the area, thereby increasing the air temperature in the area and heating and melting the ice accumulated on the helicopter blade 6.

[0039] When the ice crystals on the wing surface of the ice detector 5 are completely melted, a command is sent to the electric thermal deicing device, at which time the switch of the electric thermal deicing device is disconnected and the electric thermal deicing device is turned off.

[0040] This helicopter anti-icing system that uses rotor kinetic energy recovery uses rotor kinetic energy recovery technology to effectively reduce the consumption of traditional energy, improve energy utilization efficiency, and has good environmental performance; at the same time, the system's own structure is relatively compact, thereby reducing the overall weight of the helicopter, which helps to improve the helicopter's flight performance and load capacity, enabling it to perform various tasks more flexibly; the system structure is relatively simple, reducing the complexity and cost of maintenance and repair; the system can work in various environments, is not restricted by external energy supply, and improves the environmental adaptability and safety of the helicopter.

Claims

1. A helicopter anti-icing system using rotor kinetic energy recovery, characterized in that: It consists of an electric de-icing device, a kinetic energy recovery device, and key components of the helicopter rotor; The electric heating deicing device is composed of a first high-resistivity metal heating wire (1-1), a second high-resistivity metal heating wire (1-2), a third high-resistivity metal heating wire (1-3), and an ice detector (5); the first high-resistivity metal heating wire (1-1), the second high-resistivity metal heating wire (1-2), and the third high-resistivity metal heating wire (1-3) are arranged in sequence between the upper and lower surfaces of the first helicopter blade (6-1), the second helicopter blade (6-2), and the third helicopter blade (6-3), respectively, and are buried in the helicopter wing; the ice detector (5) is installed on the upper surface of the helicopter blade (6); The kinetic energy recovery device is composed of an electric energy rectification, voltage stabilization, energy storage device (2), a first permanent magnet (3-1), a second permanent magnet (3-2), and a magnetic induction coil (4); the upper interface of the electric energy rectification, voltage stabilization, energy storage device (2) is connected to the upper first high-resistance metal heating wire (1-1), the second high-resistance metal heating wire (1-2), and the third high-resistance metal heating wire (1-3) through a circuit perforation and a helicopter swash plate (7) in sequence, and the lower interface of the electric energy rectification, voltage stabilization, energy storage device (2) is connected to the upper interface of the magnetic induction coil (4); the first permanent magnet (3-1) and the second permanent magnet (3-2) are fixedly mounted on both sides of the magnetic induction coil (4); the upper interface of the magnetic induction coil (4) is connected to the electric energy rectification, voltage stabilization, energy storage device (2); The key components of the helicopter rotor are composed of a helicopter blade (6) and a helicopter swash plate (7); the helicopter blade (6) is fixed on the top of the helicopter, and the helicopter swash plate (7) is located below the helicopter blade (6), and the two are connected through a mechanical structure such as a connecting rod.

2. A helicopter anti-icing system using rotor kinetic energy recovery according to claim 1, characterized in that: The first high-resistivity metal heating wire (1-1), the second high-resistivity metal heating wire (1-2) and the third high-resistivity metal heating wire (1-3) are made of nickel-chromium alloy.

3. The helicopter anti-icing system using rotor kinetic energy recovery according to claim 1 is characterized in that: The electric energy rectification, voltage stabilization and energy storage device (2) integrates three modules: a rectification circuit, a voltage stabilization circuit and an energy storage battery pack. The energy storage battery pack adopts lithium batteries.

4. The helicopter anti-icing system using rotor kinetic energy recovery according to claim 1, characterized in that: The material of the magnetic induction coil (4) of the kinetic energy recovery device is copper.

5. The method for operating a helicopter anti-icing system using rotor kinetic energy recovery according to claim 1, characterized in that: It includes two operating methods: helicopter kinetic energy recovery and helicopter electric heating anti-icing; How helicopter kinetic energy recovery works: During the flight of the helicopter, the rotation of the shaft drives the magnetic induction coil (4) to rotate, so that the magnetic induction coil (4) continuously cuts the magnetic flux lines of the magnetic field formed by the first permanent magnet (3-1) and the second permanent magnet (3-2), and the magnetic induction coil (4) generates electricity by electromagnetic induction in a closed loop. The generated current is transmitted upward along the circuit to the electric energy rectification, voltage stabilization, and energy storage device (2) to convert AC to DC, stabilize the voltage, and store it in the lithium battery module. When it is detected that the battery pack is fully charged, the circuit of the magnetic induction coil (4) is disconnected to stop charging. When it is detected that the battery pack power reaches 20%-30%, the circuit of the magnetic induction coil (4) is reconnected to start charging, thereby completing the electric energy storage cycle of kinetic energy recovery. How to operate the helicopter electric heating anti-icing system: When the ice detector (5) detects the formation of ice crystals on the leading edge of the wing, the anti-icing system is activated, and current is transmitted from the electric energy rectification, voltage stabilization, and energy storage device (2) to the first high-resistance metal heating wire (1-1), the second high-resistance metal heating wire (1-2), and the third high-resistance metal heating wire (1-3). The first high-resistance metal heating wire (1-1), the second high-resistance metal heating wire (1-2), and the third high-resistance metal heating wire (1-3) generate heat after being energized. The heat is transmitted through the first high-resistance metal heating wire (1-1), the second high-resistance metal heating wire (1-2), and the third high-resistance metal heating wire (1-3). -2), and the third high-resistivity metal heating wire (1-3) is transferred to the surface of the first helicopter blade (6-1), the second helicopter blade (6-2), and the third helicopter blade (6-3). The surface of the first helicopter blade (6-1), the second helicopter blade (6-2), and the third helicopter blade (6-3) absorbs heat and heats the droplets flowing through the area, thereby increasing the air temperature in the area and heating and melting the ice accumulated on the surface of the helicopter blade (6). When the ice detector (5) does not detect ice accumulation, the electric heating anti-icing circuit is closed, thereby completing a cycle.

6. The method for operating a helicopter anti-icing system using rotor kinetic energy recovery according to claim 5, characterized in that: The ice detector (5) is a fiber optic ice detector; the ice detector (5) detects ice formation by continuously monitoring key parameters of the helicopter surface. Once ice formation is detected, the ice detector (5) will immediately send an alarm to the flight control system and can trigger an anti-icing system to ensure flight safety.

Images