A method for enhancing and adjusting the output amplitude of a variable reluctance aircraft wheel speed sensor

Abstract

The invention discloses an output amplitude enhancement adjustment method for a variable reluctance aircraft wheel speed sensor, and relates to the technical field of wheel speed acquisition. The method comprises, on the one hand, adjusting the gap between a rotor and a magnetic conductor in combination with a real object, respectively performing output amplitude measurement experiments on a plurality of different variable reluctance aircraft wheel speed sensors corresponding to different gaps, and determining a certain gap for maximizing the output amplitude; on the other hand, combining the real object with adding an iron core for connecting the rotor to the internal shaft of the sensor, respectively performing output amplitude measurement experiments on two different variable reluctance aircraft wheel speed sensors with and without the addition of the iron core, and determining a certain iron core addition condition for making the output amplitude larger; finally, according to the certain gap and the certain iron core addition condition, the output amplitude enhancement adjustment is performed on the aircraft wheel speed sensor, and a new variable reluctance aircraft wheel speed sensor with significantly improved sensor output amplitude can be obtained, and has the characteristics of low cost and simple and easy implementation.

Description

Technical Field

[0001] The invention belongs to the technical field of wheel speed acquisition, and in particular relates to an output amplitude enhancement adjustment method for a variable reluctance aircraft wheel speed sensor. Background Art

[0002] The function of the aircraft wheel speed sensor is to measure the wheel speed of the aircraft during taxiing. Its application requirements were first proposed in the aircraft anti-skid braking system: in order to ensure safety and obtain the maximum braking effect when the aircraft lands, reduce the aircraft landing distance, and avoid tire bursting on dry concrete or slipping on icy runways and reduce tire wear, the wheel speed of the aircraft during taxiing must be monitored at all times to prevent the tires from locking and slipping. Some aircraft also use the wheel speed sensor signal as feedback input for spoilers or other landing systems to control the weight carried on the wheels during landing. The anti-skid braking system has been accompanied by the birth of aircraft and has experienced nearly a hundred years of vigorous development. As a key feedback measurement component, the aircraft wheel speed sensor has also been innovatively studied by many industry insiders, and a variety of principles and structures have been proposed.

[0003] The wheel speed sensors of different aircrafts have different structures, but according to their basic working principles, traditional wheel speed sensors can be roughly divided into two categories: variable reluctance wheel speed sensors and DC generator wheel speed sensors. At present, most Boeing and Airbus civil aircraft use variable reluctance wheel speed sensors, so the wheel speed sensors based on this principle have the most abundant types and structures, which can be specifically classified into electric excitation wheel speed sensors, permanent magnet wheel speed sensors, concentric wheel speed sensors and shaft-side wheel speed sensors.

[0004] The basic structure of the variable reluctance wheel speed sensor consists of a stator, a rotor, a rotating shaft, a magnetic conductor, and several supporting bearings. The stator and the rotor are both made of soft magnetic materials, and the same number of teeth are arranged on the air gap surface of the stator and the rotor, and a coil is wound on the stator. The basic working principle of the variable reluctance wheel speed sensor is: the excitation circuit outputs current to the stator coil to establish a constant magnetic field or the permanent magnet establishes a constant magnetic field. When the rotor rotates with the wheel, if the teeth between the stator and the rotor are opposite to each other, the magnetic resistance of the magnetic circuit is small, and if the teeth are opposite to the slots, the magnetic resistance is large. This change in magnetic resistance will cause the inductance of the stator coil to change, thereby inducing an AC signal with a frequency proportional to the wheel speed in the excitation current.

[0005] However, when the speed of the variable reluctance wheel speed sensor is lower than a certain speed, the output amplitude of the AC signal will drop below the acquisition threshold, so that the output signal cannot be collected. The existing solution is usually to add a planetary gear mechanism or occupy the space of the brake device and the inner edge of the wheel and increase the speed ratio in the form of gear meshing, so that the sensor can increase the output amplitude in terms of speed to meet the signal collection needs.

[0006] Although the above solution can increase the output amplitude of the sensor in terms of rotational speed to meet the needs of signal acquisition, it will also greatly increase the weight of the sensor and occupy the brake space on the wheel. Therefore, how to provide a new optimization solution for variable reluctance wheel speed sensor that is low in cost, simple to implement and can effectively improve the reliability and signal acquisition amplitude of the wheel speed sensor during aircraft takeoff and landing is a topic that technical personnel in this field urgently need to study. Summary of the invention

[0007] The purpose of the present invention is to provide an output amplitude enhancement adjustment method for a variable reluctance aircraft wheel speed sensor, so as to solve the problem that when the output amplitude of the existing aircraft wheel speed sensor is increased, the weight of the sensor will be greatly increased and the brake space on the wheel will be occupied.

[0008] In order to achieve the above object, the present invention adopts the following technical solutions:

[0009] In a first aspect, a method for enhancing and adjusting the output amplitude of a variable reluctance aircraft wheel speed sensor is provided, comprising:

[0010] Using simulation software to perform magnetic field simulation analysis on a three-dimensional model of a variable reluctance aircraft wheel speed sensor, and obtaining a magnetic field simulation analysis result, wherein the variable reluctance aircraft wheel speed sensor includes a stator, a rotating shaft, a rotor and a magnetic conductor, and the rotor shaft is connected to the rotating shaft;

[0011] According to the magnetic field simulation analysis results, it is determined that the strongest point of the magnetic field distribution of the magnetizer is close to the fitting surface between the rotor and the magnetizer;

[0012] By adjusting the gap between the rotor and the magnetic conductor in combination with the actual object, a plurality of first variable reluctance aircraft wheel speed sensors corresponding to different gaps are obtained, wherein the first variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor with the corresponding gap;

[0013] Performing output amplitude measurement experiments on the plurality of first variable reluctance aircraft wheel speed sensors respectively to obtain first experimental results including sensor output amplitudes under different plurality of gaps;

[0014] According to the first experimental result, determining a certain gap for maximizing the sensor output amplitude;

[0015] Adding an iron core for connecting the rotor to the internal axis of the sensor in combination with the physical object, a second variable reluctance aircraft wheel speed sensor and a third variable reluctance aircraft wheel speed sensor are obtained, wherein the second variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor without the iron core, and the third variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor with the iron core added;

[0016] Performing the output amplitude measurement experiment on the second variable reluctance aircraft wheel speed sensor and the third variable reluctance aircraft wheel speed sensor respectively, and obtaining a second experimental result including the sensor output amplitude with and without the addition of the iron core;

[0017] According to the second experimental result, determining a certain iron core addition situation for making the sensor output amplitude larger, wherein the certain iron core addition situation is a situation where the iron core is not added or a situation where the iron core is added;

[0018] According to the certain gap and the certain iron core addition condition, the output amplitude enhancement adjustment of the variable reluctance aircraft wheel speed sensor is performed to obtain a new variable reluctance aircraft wheel speed sensor with the certain gap and the certain iron core addition condition.

[0019] Based on the above invention, a new optimization scheme of variable reluctance wheel speed sensor with low cost and simple and easy implementation is provided, that is, on the one hand, the gap between the rotor and the magnetic conductor is adjusted in combination with the actual object, and the output amplitude measurement experiments are respectively carried out on a plurality of different variable reluctance aircraft wheel speed sensors corresponding to different gaps, and a certain gap for making the sensor output amplitude maximum is determined; on the other hand, an iron core for connecting the rotor to the internal shaft of the sensor is added in combination with the actual object, and the output amplitude measurement experiments are respectively carried out on two different variable reluctance aircraft wheel speed sensors with and without the addition of the iron core, and a certain gap for making the sensor output amplitude maximum is determined. A certain iron core is added, and finally, according to the certain gap and the certain iron core addition situation, the output amplitude of the variable reluctance aircraft wheel speed sensor is enhanced and adjusted, so that a new variable reluctance aircraft wheel speed sensor with significantly improved sensor output amplitude can be obtained. Compared with the existing aircraft wheel speed sensor optimization scheme, since the weight of the iron core is much lower than that of the planetary gear mechanism, the increase in sensor weight can be reduced, and there is no need to occupy the brake space on the wheel, thereby effectively improving the reliability and signal acquisition amplitude of the wheel speed sensor during aircraft take-off and landing, and has the characteristics of low cost and simple and easy implementation, which is convenient for practical application and promotion.

[0020] In a possible design, according to the certain gap and the certain iron core addition condition, the variable reluctance aircraft wheel speed sensor is adjusted to enhance the output amplitude, so as to obtain a novel variable reluctance aircraft wheel speed sensor having the certain gap and the certain iron core addition condition, comprising:

[0021] The number of teeth of the rotor is adjusted in combination with the actual object to obtain a plurality of fourth variable reluctance aircraft wheel speed sensors corresponding to different numbers of teeth, wherein the fourth variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor having a corresponding number of teeth;

[0022] Performing the output amplitude measurement experiment on the plurality of fourth variable reluctance aircraft wheel speed sensors respectively to obtain a third experimental result including the sensor output amplitudes under the plurality of different tooth numbers;

[0023] According to the third experimental result, determining a certain number of teeth for maximizing the sensor output amplitude;

[0024] According to the certain number of teeth, the certain gap and the certain iron core addition condition, the output amplitude enhancement adjustment of the variable reluctance aircraft wheel speed sensor is performed to obtain a new variable reluctance aircraft wheel speed sensor with the certain number of teeth, the certain gap and the certain iron core addition condition.

[0025] In a possible design, the value range of the certain number of teeth is [3,20].

[0026] In a possible design, the value range of the certain gap is [0.8mm, 1.2mm], and the certain iron core addition situation is the situation of adding the iron core.

[0027] In a possible design, the rotor is a ring gear rotor or a gear rotor.

[0028] In a possible design, the rotor and the rotating shaft are connected by laser welding.

[0029] In a possible design, the iron core and the rotor shaft are connected by welding.

[0030] In a possible design, the magnetic conductor is a hollow magnetic steel seat, and the iron core runs through the interior of the magnetic steel seat and has no contact with the magnetic steel seat.

[0031] In a possible design, the stator includes an induction coil and a plurality of teeth arranged on the surface of the air gap.

[0032] In a possible design, the variable reluctance aircraft wheel speed sensor adopts an electrically excited wheel speed sensor, a permanent magnet wheel speed sensor, a concentric wheel speed sensor or an axle-side wheel speed sensor.

[0033] Beneficial effects of the above scheme:

[0034] (1) The present invention creatively provides a new optimization scheme for variable reluctance wheel speed sensors that is low in cost and easy to implement. That is, on the one hand, the gap between the rotor and the magnetic conductor is adjusted in combination with the actual object, and output amplitude measurement experiments are performed on multiple different variable reluctance aircraft wheel speed sensors corresponding to different multiple gaps to determine a certain gap for maximizing the sensor output amplitude. On the other hand, an iron core is added to the internal shaft of the sensor to connect the rotor, and output amplitude measurement experiments are performed on two different variable reluctance aircraft wheel speed sensors with and without the addition of the iron core to determine a certain gap for maximizing the sensor output amplitude. A certain iron core addition condition, and finally, according to the certain gap and the certain iron core addition condition, the variable reluctance aircraft wheel speed sensor is adjusted to enhance the output amplitude, so that a new variable reluctance aircraft wheel speed sensor with significantly improved sensor output amplitude can be obtained. Compared with the existing aircraft wheel speed sensor optimization scheme, since the iron core weight is much lower than the planetary gear mechanism, the increase in sensor weight can be reduced, and there is no need to occupy the brake space on the wheel, thereby effectively improving the reliability and signal acquisition amplitude of the wheel speed sensor during aircraft take-off and landing, and has the characteristics of low cost and simple and easy implementation, which is convenient for practical application and promotion;

[0035] (2) It is also possible to first adjust the number of teeth of the rotor in combination with the actual object, and conduct output amplitude measurement experiments on multiple different variable reluctance aircraft wheel speed sensors corresponding to different numbers of teeth, and determine a certain number of teeth for maximizing the sensor output amplitude. Then, based on the certain number of teeth, the certain gap, and the certain iron core addition, the variable reluctance aircraft wheel speed sensor is adjusted to enhance the output amplitude, so as to obtain a new variable reluctance aircraft wheel speed sensor with further improved sensor output amplitude. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0037] Figure 1 A schematic flow chart of a method for enhancing and adjusting the output amplitude of a variable reluctance aircraft wheel speed sensor provided in an embodiment of the present application.

[0038] Figure 2 A simulated magnetic field distribution cloud map provided in an embodiment of the present application.

[0039] Figure 3 A schematic diagram of the positional relationship between a rotor and a magnetizer in a variable reluctance aircraft wheel speed sensor for achieving output amplitude enhancement provided in an embodiment of the present application.

[0040] Figure 4 A schematic diagram of the structure comparison before and after adding an iron core to a variable reluctance aircraft wheel speed sensor for achieving output amplitude enhancement provided in an embodiment of the present application.

[0041] In the above drawings: 3-rotor; 4-magnetic conductor; 5-iron core. DETAILED DESCRIPTION

[0042] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the present invention will be briefly introduced below in combination with the drawings and the description of the embodiments or the prior art. Obviously, the following description of the structure of the drawings is only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. It should be noted that the description of these embodiments is used to help understand the present invention, but does not constitute a limitation of the present invention.

[0043] It should be understood that although the terms first and second, etc. may be used herein to describe various objects, these objects should not be limited by these terms. These terms are only used to distinguish one object from another object. For example, a first object can be referred to as a second object, and similarly, a second object can be referred to as a first object without departing from the scope of the exemplary embodiments of the present invention.

[0044] It should be understood that the term "and / or" that may appear in this article is merely a description of the association relationship of associated objects, indicating that there may be three relationships. For example, A and / or B can indicate three situations: A exists alone, B exists alone, or A and B exist at the same time. For another example, A, B and / or C can indicate the existence of any one of A, B and C or any combination of them. The term " / and" that may appear in this article describes another type of association object relationship, indicating that there may be two relationships. For example, A / and B can indicate two situations: A exists alone or A and B exist at the same time. In addition, the character " / " that may appear in this article generally indicates that the previous and next associated objects are in an "or" relationship.

[0045] Example:

[0046] like Figure 1 As shown, the output amplitude enhancement adjustment method of the variable reluctance aircraft wheel speed sensor provided in the first aspect of this embodiment includes but is not limited to the following steps S1 to S9.

[0047] S1. Use simulation software to perform magnetic field simulation analysis on the three-dimensional model of the variable reluctance aircraft wheel speed sensor to obtain magnetic field simulation analysis results, wherein the variable reluctance aircraft wheel speed sensor includes but is not limited to a stator, a rotating shaft, a rotor 3 and a magnetizer 4, and the rotor 3 shaft is connected to the rotating shaft.

[0048] In step S1, the stator, the rotating shaft, the rotor 3 and the magnetizer 4 are all conventional components in the existing variable reluctance aircraft wheel speed sensor, wherein the stator includes but is not limited to an induction coil and a plurality of teeth arranged on the air gap surface; the rotating shaft is used to connect the aircraft wheel; the rotor 3 is also arranged with a plurality of teeth on its air gap surface (the number of teeth is equal to the number of teeth on the stator), and is connected to the rotating shaft through an axis to follow the aircraft wheel; specifically, the rotor 3 can be but is not limited to a ring gear rotor or a gear rotor, etc.; the magnetizer 4 is used to conduct magnetism to the stator, specifically but not limited to a magnetic steel seat. In addition, specifically, the variable reluctance aircraft wheel speed sensor can be but is not limited to an electrically excited wheel speed sensor, a permanent magnet wheel speed sensor, a concentric wheel speed sensor or an axle side wheel speed sensor.

[0049] In step S1, the simulation software may be implemented by, but is not limited to, conventional 3D electromagnetic simulation software such as CST (Computer Simulation Technology) or Ansoft, and the three-dimensional model of the variable reluctance aircraft wheel speed sensor may also be conventionally modeled. The specific process of the magnetic field simulation analysis is also prior art. The final result of the magnetic field simulation analysis may be exemplified as follows: Figure 2 The simulated magnetic field distribution cloud diagram is shown.

[0050] S2. According to the magnetic field simulation analysis results, determine that the strongest point of the magnetic field distribution of the magnetizer 4 is close to the fitting surface between the rotor and the magnetizer.

[0051] In step S2, Figure 2 As shown in the figure, the strongest magnetic field distribution of the magnetizer 4 is close to the fitting surface between the rotor and the magnetizer, indicating that the gap between the rotor and the magnetizer can be adjusted (i.e. Figure 3 L) shown in the figure achieves the purpose of increasing the output amplitude of the wheel speed sensor.

[0052] S3. Adjust the gap between the rotor 3 and the magnetic conductor 4 in combination with the actual object to obtain a plurality of first variable reluctance aircraft wheel speed sensors corresponding to different plurality of gaps, wherein the first variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor with the corresponding gap.

[0053] In the step S3, for example, if the plurality of gaps include 0.8 mm, 1.0 mm, 1.2 mm, 1.5 mm and 2.0 mm, five of the first variable reluctance aircraft wheel speed sensors can be obtained.

[0054] S4. Performing output amplitude measurement experiments on the plurality of first variable reluctance aircraft wheel speed sensors respectively, and obtaining first experimental results including sensor output amplitudes under different of the plurality of gaps.

[0055] In step S4, the specific process of the output amplitude measurement experiment is a prior art method. For example, the first experimental result can be specifically shown in Table 1 below:

[0056] Table 1. Results of the relationship between the gap L between the rotor and the magnet, the speed and the sensor output amplitude (in V)

[0057]

[0058] According to the above first experimental result, the smaller the value of the gap L is, the higher the sensor output amplitude will be. However, if the gap L is too narrow, it will affect the operation of the sensor, thereby causing the sensor output amplitude to drop.

[0059] S5. According to the first experimental result, determine a certain gap for maximizing the sensor output amplitude.

[0060] In step S5, based on Table 1, it can be found that when the gap is 1.0 mm, the sensor output amplitude can be maximized, that is, the certain gap is 1.0 mm. Generally, the certain gap is more suitable when the value range is [0.8 mm, 1.2 mm].

[0061] S6. Adding an iron core 5 for connecting the rotor 3 to the internal axis of the sensor in combination with the actual object, a second variable reluctance aircraft wheel speed sensor and a third variable reluctance aircraft wheel speed sensor are obtained, wherein the second variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor without the iron core 5, and the third variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor with the iron core 5 added.

[0062] In step S6, the iron core 5 is an additional component based on the existing variable reluctance aircraft wheel speed sensor, and its arrangement relationship is as follows: Figure 4As shown, the upper variable reluctance aircraft wheel speed sensor is the second variable reluctance aircraft wheel speed sensor, and the lower variable reluctance aircraft wheel speed sensor is the third variable reluctance aircraft wheel speed sensor. In addition, specifically, the axial connection method of the iron core 5 and the rotor 3 can be but is not limited to welding; and considering that the iron core 5 will follow the rotor and the wheel, in order to avoid friction between the iron core 5 and the fixed magnetic conductor 4, preferably, the magnetic conductor 4 is designed as a hollow magnetic steel seat, and the iron core 5 runs through the interior of the magnetic steel seat and does not contact the magnetic steel seat.

[0063] S7. Perform the output amplitude measurement experiment on the second variable reluctance aircraft wheel speed sensor and the third variable reluctance aircraft wheel speed sensor respectively to obtain a second experimental result including the sensor output amplitude with and without the addition of the iron core 5.

[0064] In the step S7, for example, the second experimental result may be specifically shown in the following Table 2:

[0065] Table 2. Measurement results of the relationship between the rotor shaft and the core and the speed and the sensor output amplitude (in V)

[0066]

[0067] According to the above experimental results, after adding the iron core 5, the output amplitude of the sensor is significantly improved accordingly.

[0068] S8. According to the second experimental result, determine a certain iron core addition condition for making the sensor output amplitude larger, wherein the certain iron core addition condition is a condition where the iron core 5 is not added or a condition where the iron core 5 is added.

[0069] In the step S8, based on the above Table 2, it can be known that the certain iron core addition situation is the situation of adding the iron core 5.

[0070] S9. According to the certain gap and the certain iron core addition condition, the output amplitude enhancement adjustment is performed on the variable reluctance aircraft wheel speed sensor to obtain a new variable reluctance aircraft wheel speed sensor with the certain gap and the certain iron core addition condition.

[0071] In step S9, when the value range of the certain gap is [0.8mm, 1.2mm] and the certain iron core addition condition is the condition of adding the iron core 5, the novel variable reluctance aircraft wheel speed sensor obtained after the output amplitude enhancement adjustment of the variable reluctance aircraft wheel speed sensor may specifically include but not limited to a stator, a rotating shaft, a rotor 3, a magnetizer 4 and an iron core 5, wherein the rotor 3 is axially connected to the rotating shaft, wherein the gap between the rotor 3 and the magnetizer 4 is between 0.8 and 1.2mm, and the iron core 5 is located inside the sensor and axially connected to the rotor 3. In addition, the shaft connection between the rotor 3 and the rotating shaft adopts a laser welding method, which can be more stable and reliable compared to the existing crimping structure, so that the sensor output amplitude is higher and more stable.

[0072] Therefore, based on the output amplitude enhancement adjustment method described in detail in the aforementioned steps S1 to S9, a new optimization scheme for variable reluctance wheel speed sensors with low cost and simple and easy implementation is provided, that is, on the one hand, in combination with the actual object, the gap between the rotor and the magnetic conductor is adjusted, and output amplitude measurement experiments are respectively performed on multiple different variable reluctance aircraft wheel speed sensors corresponding to different multiple gaps to determine a certain gap for maximizing the sensor output amplitude; on the other hand, in combination with the actual object, an iron core for connecting the rotor to the internal shaft of the sensor is added, and output amplitude measurement experiments are respectively performed on two different variable reluctance aircraft wheel speed sensors with and without the addition of the iron core to determine the maximum output amplitude of the sensor. A certain iron core is added to make the sensor output amplitude larger, and finally, according to the certain gap and the certain iron core addition, the output amplitude of the variable reluctance aircraft wheel speed sensor is enhanced and adjusted, so that a new variable reluctance aircraft wheel speed sensor with significantly improved sensor output amplitude can be obtained. Compared with the existing aircraft wheel speed sensor optimization scheme, since the weight of the iron core is much lower than that of the planetary gear mechanism, the increase in sensor weight can be reduced, and there is no need to occupy the brake space on the wheel, thereby effectively improving the reliability and signal acquisition amplitude of the wheel speed sensor during aircraft take-off and landing, and has the characteristics of low cost and simple and easy implementation, which is convenient for practical application and promotion.

[0073] Based on the technical solution of the first aspect mentioned above, this embodiment further provides a possible design for further enhancing the output amplitude of the sensor, that is, according to the certain gap and the certain iron core addition, the output amplitude of the variable reluctance type aircraft wheel speed sensor is enhanced and adjusted to obtain a new variable reluctance type aircraft wheel speed sensor with the certain gap and the certain iron core addition, including but not limited to the following steps S91 to S94.

[0074] S91. Adjust the number of teeth of the rotor 3 in combination with the actual object to obtain a plurality of fourth variable reluctance aircraft wheel speed sensors corresponding to different numbers of teeth, wherein the fourth variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor with the corresponding number of teeth.

[0075] In step S91, the practical basis for adjusting the number of teeth of the rotor 3 to optimize the output amplitude of the enhanced sensor is based on the data correspondence between the wheel speed, the number of rotor teeth and the output frequency as shown in Table 3 below:

[0076] Table 3. Corresponding relationship between wheel speed, rotor teeth number and output frequency

[0077]

[0078]

[0079] It can be seen that when the number of teeth is 10, 20, 32 and 40, as the wheel speed increases, the output frequency increases, thereby exploring the linear or nonlinear relationship between the number of teeth and the sensor output amplitude. For example, if the plurality of numbers of teeth include 10, 20, 32 and 40, four fourth variable reluctance aircraft wheel speed sensors can be obtained.

[0080] S92. Perform the output amplitude measurement experiment on the plurality of fourth variable reluctance aircraft wheel speed sensors respectively to obtain a third experimental result including the sensor output amplitudes at different numbers of teeth.

[0081] In the step S92, for example, the third experimental result may be specifically shown in the following Table 4:

[0082] Table 4. Results of the relationship between the number of rotor teeth and speed and the sensor output amplitude (in V)

[0083]

[0084]

[0085] According to the above third experimental result, the smaller the number of rotor teeth, the higher the sensor output amplitude will be.

[0086] S93. According to the third experimental result, determine a certain number of teeth for maximizing the sensor output amplitude.

[0087] In step S93, based on Table 4, it can be found that when the number of teeth is 10, the sensor output amplitude can be maximized, that is, the certain number of teeth is 10. Generally, the certain number of teeth is more suitable when the value range is [3, 20].

[0088] S94. According to the certain number of teeth, the certain gap and the certain iron core addition, the output amplitude enhancement adjustment is performed on the variable reluctance type aircraft wheel speed sensor to obtain a new variable reluctance type aircraft wheel speed sensor with the certain number of teeth, the certain gap and the certain iron core addition.

[0089] Therefore, based on the above possible design one, the number of teeth of the rotor can be adjusted in combination with the actual object, and output amplitude measurement experiments can be performed on multiple different variable reluctance aircraft wheel speed sensors corresponding to different numbers of teeth to determine a certain number of teeth for maximizing the sensor output amplitude. Then, according to the certain number of teeth, the certain gap and the certain iron core addition, the output amplitude enhancement adjustment of the variable reluctance aircraft wheel speed sensor can be performed, so as to obtain a new variable reluctance aircraft wheel speed sensor with further improved sensor output amplitude.

[0090] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for enhancing and adjusting the output amplitude of a variable reluctance aircraft wheel speed sensor, characterized in that: include: Using simulation software to perform magnetic field simulation analysis on a three-dimensional model of a variable reluctance aircraft wheel speed sensor, a magnetic field simulation analysis result is obtained, wherein the variable reluctance aircraft wheel speed sensor comprises a stator, a rotating shaft, a rotor (3) and a magnetic conductor (4), wherein the rotor (3) is connected to the rotating shaft; According to the magnetic field simulation analysis results, it is determined that the strongest point of the magnetic field distribution of the magnetizer (4) is close to the fitting surface between the rotor and the magnetizer; In combination with the actual object, the gap between the rotor (3) and the magnetic conductor (4) is adjusted to obtain a plurality of first variable reluctance aircraft wheel speed sensors corresponding to the different plurality of gaps, wherein the first variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor having the corresponding gap; Performing output amplitude measurement experiments on the plurality of first variable reluctance aircraft wheel speed sensors respectively to obtain first experimental results including sensor output amplitudes under different plurality of gaps; According to the first experimental result, determining a certain gap for maximizing the sensor output amplitude; By adding an iron core (5) for connecting the rotor (3) to the sensor shaft, a second variable reluctance aircraft wheel speed sensor and a third variable reluctance aircraft wheel speed sensor are obtained, wherein the second variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor without the iron core (5), and the third variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor with the iron core (5) added, the iron core (5) and the rotor (3) are connected by welding, the magnetic conductor (4) is a hollow magnetic steel seat, and the iron core (5) passes through the interior of the magnetic steel seat and does not contact the magnetic steel seat; Performing the output amplitude measurement experiment on the second variable reluctance aircraft wheel speed sensor and the third variable reluctance aircraft wheel speed sensor respectively, and obtaining a second experimental result including the sensor output amplitude with and without the addition of the iron core (5); According to the second experimental result, determining a certain iron core addition condition for making the sensor output amplitude larger, wherein the certain iron core addition condition is a condition in which the iron core (5) is not added or a condition in which the iron core (5) is added; According to the certain gap and the certain iron core addition condition, the output amplitude enhancement adjustment of the variable reluctance aircraft wheel speed sensor is performed to obtain a new variable reluctance aircraft wheel speed sensor with the certain gap and the certain iron core addition condition.

2. The output amplitude enhancement adjustment method according to claim 1, characterized in that: According to the certain gap and the certain iron core addition condition, the variable reluctance aircraft wheel speed sensor is adjusted to enhance the output amplitude, so as to obtain a novel variable reluctance aircraft wheel speed sensor having the certain gap and the certain iron core addition condition, comprising: The number of teeth of the rotor (3) is adjusted in combination with the actual object to obtain a plurality of fourth variable reluctance aircraft wheel speed sensors corresponding to different numbers of teeth, wherein the fourth variable reluctance aircraft wheel speed sensor refers to the variable reluctance aircraft wheel speed sensor having a corresponding number of teeth; Performing the output amplitude measurement experiment on the plurality of fourth variable reluctance aircraft wheel speed sensors respectively to obtain a third experimental result including the sensor output amplitudes under the plurality of different tooth numbers; According to the third experimental result, determining a certain number of teeth for maximizing the sensor output amplitude; According to the certain number of teeth, the certain gap and the certain iron core addition condition, the output amplitude enhancement adjustment of the variable reluctance aircraft wheel speed sensor is performed to obtain a new variable reluctance aircraft wheel speed sensor with the certain number of teeth, the certain gap and the certain iron core addition condition.

3. The output amplitude enhancement adjustment method according to claim 2, characterized in that: The value range of the certain number of teeth is [3,20].

4. The output amplitude enhancement adjustment method according to claim 1, characterized in that: The value range of the certain gap is [0.8 mm, 1.2 mm], and the certain iron core addition situation is the situation of adding the iron core (5).

5. The output amplitude enhancement adjustment method according to claim 1, characterized in that: The rotor (3) is a gear ring rotor or a gear rotor.

6. The output amplitude enhancement adjustment method according to claim 1, characterized in that: The rotor (3) and the rotating shaft are connected by laser welding.

7. The output amplitude enhancement adjustment method according to claim 1, characterized in that: The stator includes an induction coil and a plurality of teeth arranged on the surface of the air gap.

8. The output amplitude enhancement adjustment method according to claim 1, characterized in that: The variable reluctance aircraft wheel speed sensor adopts an electric excitation wheel speed sensor, a permanent magnet wheel speed sensor, a concentric wheel speed sensor or an axle side wheel speed sensor.

Images