Helicopter adjustable resonance power generation, shock absorption and vibration alarm system

Abstract

The invention provides an adjustable resonance power generation, shock absorption and vibration alarm system for a helicopter, which belongs to the technical field of power and vibration control and comprises a resonance power generation device and a fixed connection device. The resonance power generation device is fixed to a forecabin of a helicopter body or the rear end of a tail beam through the fixing and connecting device, and the resonance power generation device meets the fatigue strength requirement under the high vibration condition. Wherein the resonance power generation device comprises an energy conversion part and fixed permanent magnets, the energy conversion part is located between the two fixed permanent magnets, and the energy conversion part is used for converting vibration energy into electric energy and transmitting generated current to the helicopter power supply system through a wire; the vibration inherent frequency of the energy conversion component is close to the vibration frequency of the helicopter, and the vibration inherent frequency of the energy conversion component is adjustable. Resonance shock absorption is utilized, vibration energy is efficiently converted into electric energy, an additional voltage source is not needed, and additional weight cost is not needed; the device has the advantages of being convenient to install, capable of generating electricity and absorbing shock and the like.

Description

Technical Field

[0001] The present invention belongs to the technical field of electricity and vibration control, and particularly relates to a system for adjustable resonance power generation, shock absorption and vibration warning of a helicopter. Background Art

[0002] The vibration loads generated by the helicopter rotor and tail rotor make the whole aircraft in an extremely harsh vibration environment. The main frequency of its vibration is the passing frequency NΩ of the rotor (N is the number of rotor blades, and Ω is the rotor speed). The vibration at this frequency can cause a reduction in the work efficiency of the pilot, discomfort of the crew, shortening of the fatigue life of the airframe structure, and a decrease in the working reliability of the airborne equipment. The design of the helicopter airframe structure, components and equipment installation must avoid this excitation frequency. However, even if the airframe structure design meets the frequency design requirements, the vibration response of the whole aircraft still far cannot meet the vibration level requirements for the comfort of helicopter passengers. A series of effective vibration reduction design measures must be taken to control the vibration load and vibration response from the rotor, main reduction gear to the airframe. Helicopters have higher requirements for the comfort of the riding environment, and their vibration level is an important indicator reflecting their market competitiveness. Helicopters emphasize the comfort and work efficiency of the pilot. Civil aircraft not only need to ensure the comfort of the cockpit, but also need to ensure the comfort of the passenger cabin. The same requirements are for both the cockpit and the passenger cabin, which puts forward higher requirements for vibration control.

[0003] Shock absorbers are widely used in helicopter vibration control engineering. Compared with other shock absorbers, passive dynamic shock absorbers have the advantages of low energy consumption, simple operation and low cost. The passive shock absorber absorbs the vibration of the helicopter, and the self-vibration of the mass block can reach more than 10g. Using the passive dynamic shock absorber for power generation has the advantages of high-efficiency energy conversion, no need for an additional power source, no additional weight penalty, convenient installation, and the ability to generate electricity and absorb shock at the same time. Therefore, it is necessary to design a device with power generation and shock absorption. Summary of the Invention

[0004] In order to improve the disadvantages of high vibration level and poor riding comfort of helicopters, based on the existing electromagnetic vibration power generation, aiming at the characteristic that the main frequency of helicopter vibration is the passing frequency NΩ of the rotor (N is the number of rotor blades, and Ω is the rotor speed), a resonance power generation and shock absorption device is designed, that is, a method of using resonance to absorb shock and efficiently convert vibration energy into electrical energy. This vibration energy collection method does not require an additional voltage source, nor does it require an additional weight penalty. It has the advantages of convenient installation, the ability to generate electricity and absorb shock at the same time. In addition, by installing a current sensor, real-time vibration warning can be realized through the on-board avionics integrated processor. The technical solution is as follows:

[0005] In a first aspect, a system for adjustable resonance power generation, shock absorption, and vibration warning of a helicopter is provided, including: a resonance power generation device 1 and a fixed connection device 4; the resonance power generation device 1 is fixed to the front cabin of the helicopter fuselage or the rear end of the tail beam through the fixed connection device 4, and the resonance power generation device 1 meets the fatigue strength requirements under high vibration conditions;

[0006] Among them, the resonance power generation device 1 includes an energy conversion component (including an armature) and a fixed permanent magnet. The energy conversion component is located between the two fixed permanent magnets. When the armature winding on the energy conversion component (fixed permanent magnet) interacts with the magnetic field, an induced electromotive force will be generated, which is used to convert vibration energy into electrical energy and transmit the generated current to the helicopter power supply system through a wire. Moreover, the vibration natural frequency of the energy conversion component is close to the helicopter vibration frequency, and the vibration natural frequency of the energy conversion component is adjustable.

[0007] Optionally, the resonance power generation device 1 includes a fixed permanent magnet 1-1, a moving permanent magnet (including an armature) 1-2, a spring 1-3, and a connecting piece 1-4.

[0008] The energy conversion component includes: a spring and a moving permanent magnet (including an armature) located above the spring. There is a certain gap between the moving permanent magnet and the fixed permanent magnet, and the height of the fixed permanent magnet is greater than the amplitude of the up and down movement of the moving permanent magnet under the action of the spring elastic force; when the moving permanent magnet (including an armature) moves up and down under the action of the spring elastic force, it cuts the magnetic field lines between the fixed permanent magnets and generates an electric current.

[0009] Optionally, the resonance power generation device 1 includes a fixed permanent magnet 2-1, a moving permanent magnet (including an armature) 2-2, a flexible beam 2-3, and a connecting piece 2-4.

[0010] The energy conversion component includes: a flexible beam 2-3, a moving permanent magnet (including an armature) 2-2, and a fixed permanent magnet 2-1 located at one end of the flexible beam 2-3. There is a certain gap between the moving permanent magnet 2-2 and the fixed permanent magnet 2-1, and the height of the fixed permanent magnet is greater than the amplitude of the up and down movement of the moving permanent magnet under the action of the flexible beam elastic force; when the moving permanent magnet (including an armature) moves up and down under the action of the flexible beam elastic force, it cuts the magnetic field lines between the fixed permanent magnets and generates an electric current.

[0011] Among them, the deviation between the vibration natural frequency of the energy conversion component and the helicopter vibration frequency ≤ 5%, and the structural damping ratio ζ of the energy conversion component satisfies: 2% ≤ ζ ≤ 5%.

[0012] Among them, the vibration natural frequency of the energy conversion component is adjusted by adjusting the mass of the moving permanent magnet to meet the shock absorption requirements of different types of helicopters.

[0013] Further, the system further includes: a current acquisition system, an on-board power control and management system, an integrated processor. The resonance power generation device is connected to the current acquisition system, and the current acquisition system is connected to the on-board power control and management system and the integrated processor;

[0014] The current acquisition system acquires the magnitude of the current generated by the resonance power generation device and transmits it to the integrated processor. The integrated processor processes the magnitude of the current based on the fast Fourier algorithm to obtain the current amplitude corresponding to different frequencies, and determines whether the vibration of the helicopter exceeds the limit based on the current amplitude corresponding to different frequencies.

[0015] Among them, the integrated processor establishes the correspondence between the current amplitude corresponding to different frequencies and the vibration amplitude of the helicopter at different frequencies. When the vibration amplitude at the target frequency is detected to exceed the threshold, an alarm signal is issued.

[0016] Among them, the correspondence between the current amplitude corresponding to different frequencies and the vibration amplitude of the helicopter at different frequencies is:

[0017]

[0018] L is the wire length, R L is the load resistance, I(t) is the current amplitude, u r (t) is the vibration velocity of the energy conversion component.

[0019] Among them, the fixed connection device is a metal part, and the resonance power generation device is screwed to the load-bearing frame beam at the front cabin of the fuselage or the rear end of the tail beam through the metal part.

[0020] Among them, the system uses resonance to achieve continuous and efficient power generation, and at the same time can efficiently absorb shock at a fixed frequency.

[0021] The beneficial effects of the present invention are at least as follows:

[0022] Based on the existing electromagnetic vibration power generation, aiming at the characteristic that the main frequency of the helicopter vibration is the passing frequency NΩ of the rotor (N is the number of rotor blades, Ω is the rotor speed), a helicopter resonance power generation and shock absorption device is designed. Using a passive dynamic shock absorber for power generation has the advantages of high-efficiency energy conversion, no need for additional power supply, no additional weight cost, and is easy to install, and can both generate power and absorb shock;

[0023] By analyzing the magnitude of the output current of the resonance power generation and shock absorption device through the on-board electromechanical management computer, the vibration level of the moving permanent magnet can be analyzed, playing a role in vibration early warning;

[0024] Adopting a modular design, it has the advantages of convenient installation and strong versatility, and has good economic benefits. It can be widely applied to the vibration absorption of the main excitation frequency of the helicopter rotor speed, and can also be used for vibration absorption, power generation and safety warning under random excitation loads such as offshore platforms, bridges, and large buildings. Description of the Drawings

[0025] Figure 1 It is a system composition diagram of the present invention;

[0026] Figure 2 It is a data analysis flow chart of the vibration warning system of the present invention;

[0027] Figure 3 It is a composition diagram of an electromagnetic resonance power generation device of the present invention (spring - mass mode);

[0028] Figure 4 It is a composition diagram of another electromagnetic resonance power generation device of the present invention (cantilever beam form);

[0029] Figure 5 It is a schematic diagram of a simplified dynamic model of electromagnetic resonance energy conversion of the present invention;

[0030] Figure 6 It is a schematic diagram of the electromagnetic resonance displacement amplification coefficient curve involved in the implementation case of the present invention. Detailed Embodiments

[0031] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0032] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, many specific details are set forth in order to provide a thorough understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be practiced without some of these specific details. The following description of the embodiments is only intended to provide a better understanding of the present invention by showing examples of the present invention. The present invention is in no way limited to any specific settings and methods presented below, but covers any improvements, substitutions, and modifications of structures, methods, and devices without departing from the spirit of the present invention. Well - known structures and technologies are not shown in the drawings and the following description to avoid unnecessarily obscuring the present invention.

[0033] It should be noted that, without conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other, and each embodiment may be referred to and cited mutually.

[0034] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0035] Please refer to Figure 1 、 Figure 2 、 Figure 5 An adjustable resonance power generation, shock absorption and vibration warning system for a helicopter is provided in an embodiment of the present invention. It is characterized by including: a resonance power generation device 1 and a fixed connection device 4; the resonance power generation device 1 is fixed at the front cabin of the helicopter fuselage or the rear end of the tail beam through the fixed connection device 4, and the resonance power generation device 1 meets the fatigue strength requirements under high vibration conditions.

[0036] The resonance power generation device 1 includes an energy conversion component (including an armature) and a fixed permanent magnet. The energy conversion component is located between the two fixed permanent magnets. When the armature winding on the fixed permanent magnet interacts with the magnetic field, an induced electromotive force will be generated. The energy conversion component is used to convert vibration energy into electrical energy, and transmit the generated current to the helicopter power supply system through the armature. Moreover, the vibration natural frequency of the energy conversion component is close to the helicopter vibration frequency, and the vibration natural frequency of the energy conversion component is adjustable.

[0037] On the one hand, a spring-mass form is provided. Refer to Figure 3 The resonance power generation device 1 includes a fixed permanent magnet 1-1, a moving permanent magnet (including an armature) 1-2, a spring 1-3 and a connecting piece 1-4.

[0038] The energy conversion component includes: a spring 1-3 and a moving permanent magnet (including an armature) 1-2 located above the spring 1-3. There is a certain gap between the moving permanent magnet (including an armature) 1-2 and the fixed permanent magnet 1-1. The height of the fixed permanent magnet 1-1 is greater than the amplitude of the up and down movement of the moving permanent magnet (including an armature) 1-2 under the elastic force of the spring 1-3. When the moving permanent magnet (including an armature) 1-2 moves up and down under the elastic force of the spring 1-3, it cuts the magnetic force lines between the fixed permanent magnets 1-1, generating an electric current.

[0039] The embodiment of the present invention adopts an existing spring-mass single-degree-of-freedom shock absorber, and the frequency is set as the first-order passing frequency of the main rotor. Considering the power generation requirements, the mass block is set as the generator rotor (iron core and winding). Based on the resonance situation, the generator rotor is in a large-amplitude vibration state during helicopter flight, and can convert vibration energy into electrical energy to the greatest extent. By digitally collecting and FFT processing the current, the current amplitudes of different frequencies (rotor 1Ω, NΩ) can be separated, and the relationship between cockpit vibration and current amplitude can be established, so that vibration monitoring can be realized.

[0040] On the one hand, a cantilever beam form is provided. Refer to Figure 4 , the resonance power generation device 1 includes a fixed permanent magnet 2-1, a moving permanent magnet (including an armature) 2-2, a flexible beam 2-3 and a connecting member 2-4.

[0041] The energy conversion component includes: a flexible beam 2-3, a moving permanent magnet (including an armature) 2-2, and a fixed permanent magnet 2-1 located at one end of the flexible beam 2-3. There is a certain gap between the moving permanent magnet 2-2 and the fixed permanent magnet 2-1, and the height of the fixed permanent magnet 2-1 is greater than the amplitude of the up-and-down movement of the moving permanent magnet 2-2 under the elastic force of the flexible beam 2-3. When the moving permanent magnet (including an armature) 2-2 moves up and down under the elastic force of the flexible beam 2-3, it cuts the magnetic field lines between the fixed permanent magnets 2-1, and an induced current will be generated in the conductor of the moving permanent magnet 2-2.

[0042] In one embodiment, the deviation between the vibration natural frequency of the energy conversion component and the helicopter vibration frequency is ≤5%, and the structural damping ratio ζ of the energy conversion component satisfies: 2% ≤ ζ ≤ 5%.

[0043] In the present invention, the vibration natural frequency of the energy conversion component can be adjusted by adjusting the mass of the moving permanent magnet to meet the shock absorption requirements of different models of helicopters.

[0044] Refer to Figure 1 , in one embodiment, the system further includes: a current acquisition system 2, an on-board power control and management system 3, and an integrated processor 5. The resonance power generation device 1 is connected to the current acquisition system 2, and the on-board power control and management system 3 is connected to the current acquisition system 2 and the integrated processor 5;

[0045] The current acquisition system 2 acquires the magnitude of the current generated by the resonance power generation device 1, and transmits the magnitude of the current to the integrated processor 5 through the on-board power control and management system 3. The integrated processor 5 processes the magnitude of the current based on the fast Fourier transform algorithm FFT, obtains the current amplitudes corresponding to different frequencies, and determines whether the vibration of the helicopter exceeds the limit based on the current amplitudes corresponding to different frequencies. See Figure 2 .

[0046] In one embodiment, the integrated processor 5 can establish a correspondence between the current amplitudes corresponding to different frequencies and the vibration amplitudes of the helicopter at different frequencies. When the vibration amplitude at the target frequency is detected to exceed the threshold, an alarm signal is issued.

[0047] The correspondence between the current amplitudes corresponding to different frequencies and the vibration amplitudes of the helicopter at different frequencies is:

[0048]

[0049] Among them, L is the wire length, R Lis the load resistance, I(t) is the current amplitude, and u r (t) is the vibration velocity of the energy conversion component. Figure 6 Schematic diagram of the electromagnetic resonance displacement amplification factor in the embodiment of the present invention.

[0050] In one embodiment, the fixed connection device (4) can be a metal part, and the resonance power generation device is screwed to the load-bearing frame beam at the front cabin of the fuselage or the rear end of the tail beam through the metal part.

[0051] The system described in the embodiment of the present invention uses resonance to achieve continuous and efficient power generation, and at the same time can efficiently absorb shock at a fixed frequency.

[0052] The above only expresses the implementation manners of the present invention, and the description is relatively specific and detailed, but it cannot be understood as a limitation to the patent scope. It should be pointed out that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. In addition, the parts not detailed in the present invention are all conventional technologies.

Claims

1. A system for adjustable resonance power generation, shock absorption and vibration warning of a helicopter, characterized in that Including: A resonance power generation device (1) and a fixed connection device (4); the resonance power generation device (1) is fixed at the front cabin of the helicopter fuselage or the rear end of the tail beam through the fixed connection device (4), and the resonance power generation device (1) meets the fatigue strength requirements under high vibration conditions. Among them, the resonance power generation device (1) includes an energy conversion component and a fixed permanent magnet. The energy conversion component is located between the two fixed permanent magnets. The energy conversion component is used to convert vibration energy into electrical energy and transmit the generated current to the helicopter power supply system through a wire. Moreover, the vibration natural frequency of the energy conversion component is close to the helicopter vibration frequency, and the vibration natural frequency of the energy conversion component is adjustable.

2. The system according to claim 1, characterized in that, The resonance power generation device (1) includes a fixed permanent magnet (1-1), a moving permanent magnet (1-2), a spring (1-3) and a connecting piece (1-4). The connecting piece (1-4) is located at the bottom of the resonance power generation device (1). The energy conversion component includes: a spring (1-3) and a moving permanent magnet (1-2) located above the spring (1-3). There is a certain gap between the moving permanent magnet (1-2) and the fixed permanent magnet (1-1). The height of the fixed permanent magnet (1-1) is greater than the amplitude of the up and down movement of the moving permanent magnet (1-2) under the elastic force of the spring (1-3); when the moving permanent magnet (1-2) moves up and down under the elastic force of the spring (1-3), it cuts the magnetic field lines between the fixed permanent magnets (1-1) and generates an electric current.

3. The system according to claim 1, wherein The resonance power generation device (1) includes a fixed permanent magnet (2-1), a moving permanent magnet (2-2), a flexible beam (2-3) and a connecting piece (2-4). The connecting piece (2-4) is located at the bottom of the resonance power generation device (1). The moving permanent magnet (2-2) is located at the upper part of one end of the flexible beam (2-3). The energy conversion component includes: a flexible beam (2-3), a moving permanent magnet (2-2), and a fixed permanent magnet (2-1) located at one end of the flexible beam (2-3). There is a certain gap between the moving permanent magnet (2-2) and the fixed permanent magnet (2-1). And the height of the fixed permanent magnet (2-1) is greater than the amplitude of the up and down movement of the moving permanent magnet (2-2) under the elastic force of the flexible beam (2-3); when the moving permanent magnet (2-2) moves up and down under the elastic force of the flexible beam (2-3), it cuts the magnetic field lines between the fixed permanent magnets (2-1) and generates an electric current.

4. The system according to claim 2 or 3, characterized in that, The deviation between the vibration natural frequency of the energy conversion component and the helicopter vibration frequency ≤ 5%, and the structural damping ratio ζ of the energy conversion component satisfies: 2% ≤ ζ ≤ 5%.

5. The system according to claim 2 or 3, characterized in that, The vibration natural frequency of the energy conversion component is adjusted by adjusting the mass of the moving permanent magnet.

6. The system according to claim 1, wherein The system further includes: a current acquisition system, an on-board power supply control and management system, and an integrated processor. The resonance power generation device is connected to the current acquisition system. The on-board power supply control and management system is connected to the current acquisition system and the integrated processor. The current acquisition system acquires the magnitude of the current generated by the resonance power generation device, and transmits the magnitude of the current to the integrated processor through the on-board power control and management system. The integrated processor processes the magnitude of the current based on the fast Fourier algorithm to obtain the current amplitude corresponding to different frequencies, and determines whether the vibration of the helicopter exceeds the limit based on the current amplitude corresponding to different frequencies.

7. The system according to claim 6, wherein The integrated processor establishes the corresponding relationship between the current amplitude corresponding to different frequencies and the vibration amplitude of the helicopter at different frequencies. When the vibration amplitude at the target frequency is detected to exceed the threshold, an alarm signal is issued.

8. The system according to claim 7, characterized in that, The corresponding relationship between the current amplitude corresponding to different frequencies and the vibration amplitude of the helicopter at different frequencies is as follows: where L is the wire length, R L is the load resistance, I(t) is the current amplitude, and u r (t) is the vibration velocity of the energy conversion component.

9. The system according to claim 1, wherein The fixed connection device is a metal part, and the resonance power generation device is screwed to the load-bearing frame beam at the front cabin of the fuselage or the rear end of the tail beam through the metal part.

10. The system according to claim 1, characterized in that, The system utilizes resonance to achieve continuous and efficient power generation, and at the same time can efficiently absorb shock at a fixed frequency.

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