Split position sensor for a flap or a slot and monitoring method thereof

Abstract

This application discloses a split-type position sensor for flaps or slats and a monitoring method thereof. The split-type position sensor includes a reduction mechanism and a sensor mechanism, wherein the housings of the reduction mechanism and the sensor mechanism are connected by bolts, and the reduction mechanism is partially fixed to the aircraft structure. The sensor mechanism, as an independent replaceable line unit, is connected to the reduction mechanism via a backlash-free gear. In another aspect, a method for monitoring the split-type position sensor includes: calculating the square of the transformer ratio of the position sensor based on the sine and cosine voltage signals output by the resolver position sensor of the split-type position sensor; determining whether the square of the transformer ratio of the monitored position sensor is within a first or second monitoring threshold in response to whether the temperature is above or below the temperature threshold; and setting the split-type position sensor to invalid when the square of the transformer ratio exceeds the first or second monitoring threshold.

Description

Technical Field

[0001] This invention relates to aircraft position sensor devices, and more particularly to a split flap or slat position sensor employing a rotary transformer and a method for monitoring its effectiveness. Background Technology

[0002] Large civil aircraft typically have multiple leading-edge slats and trailing-edge flaps on their left and right wings. These are used to increase lift and reduce drag during takeoff and landing, ensuring safe takeoff and landing. Each wingtip is equipped with a flap position sensor and a slat position sensor to measure and report the positions of the flaps and slats, enabling closed-loop control of wing surface positions and monitoring of motion faults.

[0003] In civil aircraft, flap and slat position sensors typically use rotary transformer sensors, which mainly consist of a reduction gear assembly and a sensor assembly, such as... Figure 1 As shown. The reducer assembly proportionally converts the input angle into the effective measurement range of the sensor assembly, which then converts the measured mechanical angle signal into corresponding sine and cosine voltage signals for output. The flap or slat position sensors are Line Replaceable Units (LRUs). The left and right flap or slat position sensors are interchangeable, but the flap and slat position sensors are of different configurations and cannot be interchanged.

[0004] Incorrect position sensor signals can lead to catastrophic failures, such as excessive unauthorized flap and slat movement. Therefore, it is necessary to monitor the effectiveness of flap or slat position sensors.

[0005] Existing flap or slat position sensors and their effectiveness monitoring methods have the following problems:

[0006] Firstly, the position sensors for flaps and slats generally use rotary transformer sensors. The equipment structure and function are the same, only the transmission ratio of the reduction mechanism is different, which makes it impossible to interchange flap and slat position sensors.

[0007] Secondly, as a local unit (LRU), the flap or slat position sensor requires replacement of the entire sensor unit when it fails. However, the mechanical components of the position sensor are generally more reliable than the sensor itself, and failures often occur in the sensor assembly. The current configuration of flap or slat position sensors has relatively high repair costs.

[0008] Third, the traditional monitoring method for position sensors of rotary transformers only monitors the transformer ratio parameter of the sensor, which is a single characteristic value of the sensor. This results in poor anti-interference ability and easy triggering of alarms at low temperatures.

[0009] Therefore, there is an urgent need to propose an interchangeable flap / slat position sensor and a method for monitoring its effectiveness.

[0010] The present invention relates to the structure and effectiveness monitoring of flap or slat position sensor devices, which can improve the interchangeability of multiple flap or slat position sensors, reduce maintenance costs, and improve the reliability of flap or slat position sensor monitors. Summary of the Invention

[0011] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify the key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed descriptions that follow.

[0012] To address the aforementioned issues, this application proposes a split-type position sensor for flaps or slats of civil aircraft and a method for monitoring its effectiveness.

[0013] In one aspect, a split-type position sensor for flaps or slats of a civil aircraft includes a deceleration mechanism and a sensor mechanism, wherein the housings of the deceleration mechanism and the sensor mechanism are connected by bolts, and the deceleration mechanism is partially fixed to the aircraft structure, and the sensor mechanism is connected to the deceleration mechanism as an independent, replaceable flight path unit via a backlash-free gear.

[0014] Preferably, the sensor mechanism includes a rotary transformer.

[0015] Preferably, the tooth root of the backlash-eliminating gear is drilled and assembled using a pin; the backlash-eliminating gear includes a fixed gear, a moving gear, a torsion spring, a washer, a shaft elastic retaining ring, and a pin, wherein the fixed gear is fixed to the input shaft end of the sensor mechanism, and the moving gear is internally connected to the fixed gear by a torsion spring.

[0016] Preferably, holes are drilled at the roots of the fixed gear and the driven gear to serve as pin holes; the driven gear is rotated to compress the torsion spring so that the tooth profiles of the fixed gear and the driven gear are aligned and the pin is inserted, so that the tooth profiles are aligned to facilitate meshing connection; the backlash-free gear is meshed with the output shaft of the reduction mechanism; after the meshing connection, the pin is pulled out, and the gear of the output shaft of the reduction mechanism is locked under the force of the torsion spring between the driven gear and the fixed gear to clamp the gear.

[0017] Preferably, the zeroing operation is performed after the sensor mechanism and the deceleration mechanism are connected.

[0018] In another aspect, a method for monitoring a split-type position sensor used for flaps or slats includes: providing a sinusoidal excitation voltage to the split-type position sensor; calculating the square of the transformer ratio of the position sensor based on a sinusoidal voltage signal and a cosine voltage signal output by a rotary transformer position sensor of the split-type position sensor; determining a monitoring threshold as a first monitoring threshold in response to a temperature higher than a temperature threshold; determining the monitoring threshold as a second monitoring threshold in response to a temperature lower than the temperature threshold; determining whether the square of the transformer ratio of the monitored split-type position sensor is within the monitoring threshold; and setting the split-type position sensor to invalid when the square of the transformer ratio exceeds the monitoring threshold.

[0019] Preferably, setting the split-type position sensor to invalid includes: de-energizing the solenoid valve of the channel corresponding to the split-type position sensor; and latching the fault.

[0020] Preferably, the first monitoring threshold is a normal monitoring threshold, the second monitoring threshold is a low temperature monitoring threshold, and the second monitoring threshold has a larger margin than the first monitoring threshold.

[0021] Preferably, the first monitoring threshold is based on one or more of the following: the AC excitation tolerance of the rotary transformer position sensor; the tolerance caused by the cable voltage drop between the flap or slat computer and the rotary transformer position sensor; the error range of the transformer position sensor's transformer ratio TR; and the demodulation accuracy of the position sensor information of the flap or slat computer.

[0022] Preferably, the split-type position sensor includes a deceleration mechanism and a sensor mechanism, wherein the sensor mechanism includes the rotary transformer; the housings of the deceleration mechanism and the sensor mechanism are connected by bolts, and the deceleration mechanism is partially fixed to the aircraft structure; the sensor mechanism is connected to the deceleration mechanism as an independent line-changeable unit via a backlash-free gear.

[0023] This synopsis is provided to introduce some concepts in a simplified form, which will be further described in the detailed description below. This synopsis is not intended to identify key or essential features of the claimed subject matter, nor is it intended to limit the scope of the claimed subject matter. Other aspects, features, and / or advantages of the embodiments will be set forth in part in the description which follows, and will be apparent in part from the description, or may be learned by practice of this disclosure. Attached Figure Description

[0024] To gain a detailed understanding of the manner in which the above-described features of the invention are employed, a more specific description of the above-briefly summarized content can be provided with reference to various embodiments, some of which are illustrated in the accompanying drawings. However, it should be noted that the drawings only illustrate certain typical aspects of the invention and should not be considered as limiting its scope, as this description may allow for other equivalent aspects. In the drawings, similar reference numerals are consistently used for similar purposes. It should be noted that the described drawings are merely schematic and non-limiting. In the drawings, the dimensions of some components may be enlarged and are not drawn to scale for illustrative purposes.

[0025] Figure 1 This is a structural diagram of the flap slat position sensor in existing technology;

[0026] Figure 2 This is a flap or slat position sensor deceleration mechanism according to an embodiment of the present invention;

[0027] Figure 3 It is a flap or slat position sensor portion according to an embodiment of the present invention;

[0028] Figure 4 It is a split flap or slat position sensor according to an embodiment of the present invention;

[0029] Figure 5 The tooth profiles of the fixed gear and the moving gear in the unassembled state according to an embodiment of the present invention;

[0030] Figure 6 The pin holes at the root of the fixed gear and the moving gear are according to an embodiment of the present invention;

[0031] Figure 7 This is a flap or slat position sensor monitoring method according to an embodiment of the present invention;

[0032] Figure 8 This is an electrical interface diagram of a flap or slat position sensor according to an embodiment of the present invention;

[0033] Figure 9 This is a schematic diagram of the installation of a flap or slat position sensor according to an embodiment of the present invention. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to specific embodiments and the accompanying drawings. In the following detailed description, numerous specific details are set forth to provide a thorough understanding of the described exemplary embodiments. However, it will be apparent to those skilled in the art that the described embodiments can be practiced without some or all of these specific details. In other exemplary embodiments, well-known structures or processing steps have not been described in detail to avoid unnecessarily obscuring the concepts of this disclosure.

[0035] In this specification, unless otherwise stated, the term "A or B" as used herein refers to "A and B" and "A or B", and does not imply that A and B are exclusive.

[0036] Large civil aircraft typically have multiple leading-edge slats and trailing-edge flaps on their left and right wings. During takeoff and landing, the pilot manipulates the flap and slat handles to control the retraction and extension of the flaps and slats, increasing lift and reducing drag to ensure safe takeoff and landing. Each wingtip is equipped with a flap position sensor and a slat position sensor to measure and report the flap and slat surface positions, enabling closed-loop control of wing surface positions and monitoring of motion faults.

[0037] In civil aircraft, flap and slat position sensors typically use rotary transformer sensors, which mainly consist of a reduction gear assembly and a sensor assembly, such as... Figure 1 As shown. The reducer assembly proportionally converts the input angle into the effective measurement range of the sensor assembly, which then converts the measured mechanical angle signal into corresponding sine and cosine voltage signals for output. The flap or slat position sensors are Line Replaceable Units (LRUs). The left and right flap or slat position sensors are interchangeable, but the flap and slat position sensors are of different configurations and cannot be interchanged. Figure 1 The flap slat electronic control unit (FSECU) includes command and monitoring branches for distributed control of each resolver sensor. For example, FSECU1 can control sensor channel 1 on the left and / or right, while FSECU2 can control sensor channel 2 on the left and / or right.

[0038] According to the safety analysis of high-lift systems, erroneous position sensor signals can lead to catastrophic failures, such as excessive unauthorized flap and slat movement. Therefore, it is necessary to monitor the effectiveness of flap or slat position sensors.

[0039] To address the problems of poor interchangeability, high maintenance costs, and poor reliability of existing flap or slat position sensors, this invention proposes a split-type flap or slat position sensor for civil aircraft and its effectiveness monitoring method, as described in reference [reference needed]. Figures 2 to 6 The explanation. Figure 2 This is a flap or slat position sensor deceleration mechanism according to an embodiment of the present invention; Figure 3 It is a flap or slat position sensor portion according to an embodiment of the present invention; Figure 4 It is a split flap or slat position sensor according to an embodiment of the present invention; Figure 5 The tooth profiles of the fixed gear and the moving gear in the unassembled state according to an embodiment of the present invention; Figure 6 It is a pin hole at the root of the fixed gear and the moving gear according to an embodiment of the present invention.

[0040] In the embodiments of this application, the flap or slat position sensor can be split into two LRUs: a reduction gear mechanism and a rotary transformer sensor. The two housings are connected by bolts, with the reduction gear mechanism fixed to the aircraft structure, and the sensor mechanism connected to the reduction gear mechanism as an independent LRU via a backlash-free gear.

[0041] In embodiments of this application, the design of the split flap or slat position sensor can be as follows: Figure 4 As shown. The deceleration mechanism of the flap or slat position sensor is as follows. Figure 2 As shown in the box, the rotary transformer sensor section is as follows: Figure 3 As shown in the box. Due to changes in the internal connection between the reduction mechanism and the sensor section, and considering installation accuracy issues, the original backlash-free gear underwent a design innovation. Because the backlash-free gear has the characteristics of low speed and low connection load capacity, holes were drilled at the root of the backlash-free gear teeth and assembled using a pin method.

[0042] In the embodiments of this application, the backlash-eliminating gear consists of a fixed gear, a moving gear, a torsion spring, a washer, a shaft retaining ring, and a pin. The fixed gear is fixed to the sensor input shaft end, and the moving gear is internally connected to the fixed gear via a torsion spring. In the unassembled state, the teeth of the fixed gear and the moving gear are not aligned, such as... Figure 5 As shown. For assembly, holes are drilled at the roots of the fixed gear and the driven gear to serve as pin holes, as shown. Figure 6 As shown. Rotating the moving gear compresses the torsion spring to align the teeth of the fixed gear and the moving gear, and inserting a pin to facilitate meshing. The backlash-eliminating gear meshes with the output shaft of the reduction mechanism. After meshing, the pin is pulled out, and the gear is locked under the force of the torsion spring between the moving gear and the fixed gear, clamping the output shaft gear of the reduction mechanism, thereby achieving the purpose of eliminating backlash.

[0043] Figure 7 This is a flap or slat position sensor monitoring method according to an embodiment of the present invention.

[0044] In the embodiments of this application, the validity of the output signals of the flap or slat position sensors is monitored. Different sensor monitoring thresholds are used in both ground-based and low-altitude / high-altitude operating environments to improve the reliability of the sensor monitor and reduce the probability of false alarms. The specific logic of this monitoring method is as follows: Figure 7 As shown:

[0045] a) Provide a sinusoidal excitation voltage Vexc to the position sensor, and calculate the squared value of the sensor transformer ratio based on the sinusoidal and cosine voltage signals Vsin and Vcos output by the sensor.

[0046] b) Based on the aircraft's atmospheric temperature data, set the normal monitoring threshold (R) and the low temperature monitoring threshold (L) respectively;

[0047] c) When the temperature is above -50℃, determine whether the square of the transformer ratio of the monitored position sensor is within the normal monitoring threshold. If the temperature is below -50℃ (for example, the temperature is below -50℃ for 1 second), determine whether the square of the transformer ratio of the monitored sensor is within the low temperature monitoring threshold.

[0048] d) When the square of the transformer ratio exceeds the normal or low-temperature monitoring threshold (e.g., exceeding the temperature monitoring threshold for 0.25 seconds), the flap or slat position sensor is set to invalid, the flap or slat computer controls the solenoid valve of the corresponding channel to de-energize, and the fault is latched. In embodiments of this application, the fault can be latched in the flap or slat computer.

[0049] Figure 8 This is an electrical interface diagram of a flap or slat position sensor according to an embodiment of the present invention.

[0050] The flap and slat control system for civil aircraft includes: a flap and slat control handle, two flap and slat computers, two power drive units, flap and slat drive lines, multiple flap and slat actuators, and multiple flap and slat position sensors. The flap or slat position sensors are typically located at the outer ends of the flap and slat drive lines on the left and right wings, feeding back the positions of the flap and slat actuators to the flap or slat computers in the form of electrical signals. These sensors are used to calculate the flap and slat surface positions and monitor asymmetric faults in the flap or slat surfaces of both wings.

[0051] In embodiments of this application, the flap or slat computer provides a sinusoidal excitation voltage to the flap and slat position sensors and receives the sinusoidal signal Vsin and cosine signal Vcos output by the sensors. The electrical connection between the flap or slat position sensors and the flap or slat computer is as follows: Figure 8As shown, the flap slat electronic control unit (FSECU) includes command and monitoring branches for distributed control of each resolver sensor. For example, FSECU1 can control sensor channel 1 on the left and / or right, while FSECU2 can control sensor channel 2 on the left and / or right.

[0052] In the embodiments of this application, the split flap or slat rotary transformer position sensor mainly includes: a reduction mechanism LRU and a rotary transformer sensor LRU. The reduction mechanism LRU is fixed at the flap or slat sensor position. Since the reduction mechanism LRU is a purely mechanical component, it has high reliability and can be fixed at the flap and slat position sensor mounting locations at different positions on the wing to achieve different reduction ratios.

[0053] In the embodiments of this application, when the flap or slat position sensor fails and needs to be replaced, the maintenance personnel can retain the deceleration mechanism LRU, and only need to remove the rotary transformer sensor LRU part and replace it with the rotary transformer sensor LRU in the spare parts library.

[0054] In the embodiments of this application, the rotary transformer sensor LRUs of flap and slat position sensors at different stations adopt the same configuration. In this way, the airline does not need to prepare spare parts for rotary transformer sensors at each station, but only needs to prepare a small number of rotary transformer sensor LRUs to meet the aircraft operation requirements.

[0055] In the embodiments of this application, the mounting between the two LRUs of the split flap or slat position sensor is achieved through a backlash-free gear. The backlash-free gear consists of a fixed gear, a moving gear, a torsion spring, a washer, a shaft retaining ring, and a pin. It features low rotational speed and low torque; therefore, holes are drilled at the root of the gear teeth, and assembly is achieved using a pin. The fixed gear is fixed to the sensor input shaft end, and the moving gear is internally connected to the fixed gear via a torsion spring. When the sensor is not assembled, the teeth of the fixed gear and the moving gear are not aligned.

[0056] In the embodiments of this application, the installation and maintenance personnel rotate the moving gear to compress the torsion spring, so that the tooth profiles of the fixed gear and the moving gear are aligned and a pin is inserted. The tooth profile alignment facilitates meshing, and the backlash-eliminating gear meshes with the output shaft of the reduction mechanism. After meshing, the pin is pulled out, and the gear is locked under the force of the torsion spring between the moving gear and the fixed gear, thus clamping the output shaft gear of the reduction mechanism and achieving the purpose of eliminating backlash.

[0057] Figure 9 This is a schematic diagram of the installation of a flap or slat position sensor according to an embodiment of the present invention.

[0058] In the embodiments of this application, the separate flap and slat position sensors are fixed to the aircraft via sensor supports and connected to the flap or slat drive shaft via splines, such as... Figure 1 or Figure 9 As shown.

[0059] In the embodiments of this application, during normal system operation, the AC excitation V from the position sensor of the split flap or slat rotary transformer is provided by the flap or slat computer. EXC =7Vrms (Vrms refers to the effective voltage value). A single flap or slat computer is connected to a single channel of a separate flap or slat rotary transformer position sensor. After receiving its position feedback signals Vsin and Vcos, the signals are filtered and demodulated before the rotary transformer position sensor's effectiveness is monitored. The method is as follows:

[0060] The first step is to filter and demodulate the sensor output values ​​Vsin and Vcos.

[0061] The second step is to receive temperature information T, filter it, perform redundancy voting, compare and monitor it to determine the validity of the temperature data, and select a reliable temperature.

[0062] The third step is to calculate the square of the transformer ratio of the rotary transformer position sensor;

[0063]

[0064] Fourth, based on the temperature T selected in step two, different sensor transformer ratio squared monitoring thresholds are chosen to monitor sensor effectiveness. The monitoring method is as follows:

[0065] 1) If the current temperature T > temperature threshold (e.g., -50℃), the rotary transformer position sensor is considered to be operating in a normal environment. The normal monitoring threshold or the first monitoring threshold is determined based on the sensor transformer ratio error, cable error and computer demodulation error.

[0066] 2) If the current temperature T ≤ temperature threshold (-50℃), the position sensor is considered to be operating in a low-temperature environment. Considering the influence of temperature on the sensor output value, a certain margin (e.g., 5% margin) is added to the first monitoring threshold to reach the low-temperature monitoring threshold or the second monitoring threshold, so as to avoid the monitor from generating false alarms due to the influence of the low-temperature environment.

[0067] 3) If the temperature is invalid, then the first monitoring threshold shall be used for monitoring.

[0068] Fifth, when the square of the transformer ratio exceeds the first monitoring threshold or the second monitoring threshold (different monitoring thresholds are used in response to different ambient temperatures), the flap or slat position signal is set to invalid, the flap or slat computer controls the solenoid valve of the corresponding channel (e.g., the channel corresponding to the flap or slat position sensor) to de-energize, and the fault is latched.

[0069] The normal monitoring threshold design considers one or more of the following factors: AC excitation tolerance of the rotary transformer position sensor; tolerance caused by cable voltage drop between the flap or slat computer and the rotary transformer position sensor; and the transformer ratio T of the rotary transformer position sensor LRU. R Error range; demodulation accuracy of position sensor information from flaps or slats computers, etc.

[0070] In the embodiments of this application, after installing the rotary transformer sensor LRU, a zeroing operation needs to be performed again to ensure that the transformer sensor is at zero position and to guarantee its accuracy. The zeroing steps are as follows:

[0071] a) Retract the flaps and slats to the 0 position;

[0072] b) Select to enter maintenance mode;

[0073] c) Select the appropriate zeroing mode;

[0074] d) The flap or slat computer will collect the flap or slat position sensor values ​​as zeroing data;

[0075] e) The flap or slat computer stores zeroing data, aircraft serial number, and computer ID in non-volatile memory (NVM).

[0076] f) The flap or slat computer sends a zeroing completion status message to the maintenance system;

[0077] g) End maintenance mode.

[0078] The above describes the split flap or slat position sensor and its effectiveness monitoring method according to the present invention. Compared with the prior art, the method of the present invention has at least the following advantages:

[0079] (1) By treating the sensor assembly as a single LRU, the interchangeability and spare parts utilization of flap and slat position sensors on the aircraft can be improved, and maintenance costs can be reduced.

[0080] (2) The flap or slat position sensor adopts a dual threshold monitoring method to improve the reliability of the sensor monitor and reduce the probability of false triggering of the slat position sensor monitor during flight line operation.

[0081] (3) The split flap or slat position sensor proposed in this invention has strong adaptability and good economy.

[0082] Throughout this specification, reference has been made to "embodiments," meaning that a particular described feature, structure, or characteristic is included in at least one embodiment. Therefore, the use of these phrases may refer to more than one embodiment. Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0083] The various steps and modules of the methods and apparatus described above can be implemented in hardware, software, or a combination thereof. If implemented in hardware, the various illustrative steps, modules, and circuits described in connection with this disclosure can be implemented or executed using a general-purpose processor, digital signal processor (DSP), application-specific integrated circuit (ASIC), field-programmable gate array (FPGA), or other programmable logic components, hardware components, or any combination thereof. A general-purpose processor can be a processor, microprocessor, controller, microcontroller, or state machine, etc. If implemented in software, the various illustrative steps and modules described in connection with this disclosure can be stored as one or more instructions or codes on a computer-readable medium or transmitted. Software modules implementing the various operations of this disclosure can reside in a storage medium, such as RAM, flash memory, ROM, EPROM, EEPROM, registers, hard disk, removable disk, CD-ROM, cloud storage, etc. The storage medium can be coupled to a processor so that the processor can read and write information from / to the storage medium and execute corresponding program modules to implement the various steps of this disclosure. Moreover, software-based embodiments can be uploaded, downloaded, or remotely accessed through appropriate communication means. Such appropriate means of communication include, for example, the Internet, the World Wide Web, intranets, software applications, cables (including fiber optic cables), magnetic communication, electromagnetic communication (including RF microwave and infrared communication), electronic communication, or other such means of communication.

[0084] The numerical values ​​given in the various embodiments are merely examples and are not intended to limit the scope of the invention. Furthermore, as a whole, there are other components or steps not listed in the claims or specification of this invention. Moreover, a single name for a component does not preclude other names for that component.

[0085] It should also be noted that these embodiments may be described as processes depicted as flowcharts, flow diagrams, structure diagrams, or block diagrams. Although a flowchart may describe the operations as a sequential process, many of these operations can be executed in parallel or concurrently. Furthermore, the order of these operations can be rearranged.

[0086] The disclosed methods, apparatuses, and systems should not be limited in any way. Rather, this disclosure covers all novel and non-obvious features and aspects of the various disclosed embodiments (individually and in various combinations and sub-combinations of each other). The disclosed methods, apparatuses, and systems are not limited to any particular aspect or feature or combination thereof, and no disclosed embodiment is required to have any one or more specific advantages or to solve any particular or all technical problems.

[0087] This invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other modifications based on the teachings of this invention without departing from the spirit and scope of the claims. All of these modifications are within the scope of protection of this invention.

[0088] Those skilled in the art will recognize that these embodiments can be practiced without one or more specific details or using other methods, resources, materials, etc. In other cases, well-known structures, resources, or operations are not shown or described in detail merely for the purpose of observing obscure aspects of the embodiments.

[0089] While embodiments and applications have been described and illustrated, it should be understood that the embodiments are not limited to the precise configurations and resources described above. Various modifications, substitutions, and improvements that will be apparent to those skilled in the art may be made in the arrangement, operation, and details of the methods and systems disclosed herein without departing from the scope of the claimed embodiments.

[0090] As used herein, the terms “and,” “or,” and “and / or” may include a variety of meanings, which are also contemplated, at least in part, depending on the context in which such terms are used. Generally, “or,” when used to relate a list such as A, B, or C, is intended to mean A, B, and C (in the inclusive sense) and A, B, or C (in the exclusive sense). Additionally, the term “one or more” as used herein may be used to describe any feature, structure, or property in its singular form, or to describe multiple features, structures, or characteristics, or some other combination thereof. However, it should be noted that this is merely an illustrative example, and the claimed subject matter is not limited to this example.

[0091] While the features currently considered exemplary have been explained and described, those skilled in the art will understand that various other modifications can be made and equivalents can be substituted without departing from the claimed subject matter. Additionally, numerous modifications can be made to adapt a particular scenario to the teachings of the claimed subject matter without departing from the central concepts described herein.

[0092] One implementation (1) can be a split position sensor for flaps or slats of a civil aircraft, comprising: a deceleration mechanism and a sensor mechanism, wherein the housings of the deceleration mechanism and the sensor mechanism are connected by bolts, and the deceleration mechanism is partially fixed to the aircraft structure, and the sensor mechanism is connected to the deceleration mechanism as an independent line-changeable unit via a backlash-free gear.

[0093] Some implementations (2) of the above sensor (1) may exist, wherein the sensor mechanism includes a rotary transformer.

[0094] Some implementations (3) of the above sensor (1) may exist, wherein a hole is drilled at the root of the backlash-eliminating gear and assembled in the form of a pin; the backlash-eliminating gear includes a fixed gear, a moving gear, a torsion spring, a washer, a shaft elastic retaining ring and a pin, wherein the fixed gear is fixed to the input shaft end of the sensor mechanism, and the moving gear is internally connected to the fixed gear by a torsion spring.

[0095] Some implementations (4) of the above sensor (1) may exist, wherein holes are drilled at the roots of the fixed gear and the moving gear as pin holes; the moving gear is rotated to compress the torsion spring so that the tooth profiles of the fixed gear and the moving gear are aligned and a pin is inserted to facilitate meshing; the backlash-free gear is meshed with the output shaft of the reduction mechanism; after the meshing connection, the pin is pulled out and locked under the force of the torsion spring between the moving gear and the fixed gear to clamp the gear of the output shaft of the reduction mechanism.

[0096] Some implementations (2) of the above sensor (1) may exist, wherein a zeroing operation is performed after the sensor mechanism is connected to the deceleration mechanism.

[0097] One implementation (6) could be a method for monitoring a split-type position sensor used for flaps or slats, comprising: providing a sinusoidal excitation voltage to the split-type position sensor; calculating the square of the transformer ratio of the position sensor based on a sinusoidal voltage signal and a cosine voltage signal output by a rotary transformer position sensor of the split-type position sensor; determining a monitoring threshold as a first monitoring threshold in response to a temperature higher than a temperature threshold; determining the monitoring threshold as a second monitoring threshold in response to a temperature lower than the temperature threshold; determining whether the square of the transformer ratio of the monitored split-type position sensor is within the monitoring threshold; and setting the split-type position sensor to invalid when the square of the transformer ratio exceeds the monitoring threshold.

[0098] Some implementations (7) of the above method (6) may exist, wherein setting the split position sensor to invalid includes: de-energizing the solenoid valve of the channel corresponding to the split position sensor; and latching the fault.

[0099] Some implementations (8) of the above method (6) may exist, wherein the first monitoring threshold is a normal monitoring threshold, the second monitoring threshold is a low temperature monitoring threshold, and the second monitoring threshold has a larger margin than the first monitoring threshold.

[0100] Some implementations (9) of the above method (6) may exist, wherein the first monitoring threshold is based on one or more of the following: the AC excitation tolerance of the rotary transformer position sensor; the tolerance caused by the cable voltage drop between the flap or slat computer and the rotary transformer position sensor; the error range of the transformer position sensor's transformer ratio TR; and the demodulation accuracy of the position sensor information of the flap or slat computer.

[0101] Some implementations (10) of the above method (6) may exist, wherein the split position sensor includes: a deceleration mechanism and a sensor mechanism, wherein the sensor mechanism includes the rotary transformer; the housings of the deceleration mechanism and the sensor mechanism are connected by bolts, and the deceleration mechanism is partially fixed to the aircraft structure, and the sensor mechanism is connected to the deceleration mechanism as an independent line replaceable unit through a backlash-free gear.

Claims

1. A method for monitoring a split-type position sensor used for flaps or slats, comprising: A sinusoidal excitation voltage is provided to the split-type position sensor; The square of the transformer ratio of the position sensor is calculated based on the sinusoidal and cosine voltage signals output by the rotary transformer position sensor of the split-type position sensor. In response to a temperature exceeding a temperature threshold, the monitoring threshold is determined as the first monitoring threshold; In response to the temperature being lower than the temperature threshold, the monitoring threshold is determined as a second monitoring threshold; Determine whether the square of the transformer ratio of the monitored split-type position sensor is within the monitoring threshold. as well as When the square of the transformer ratio exceeds the monitoring threshold, the solenoid valve of the channel corresponding to the split position sensor is de-energized, and the fault is latched. Wherein, the first monitoring threshold is a normal monitoring threshold, the second monitoring threshold is a low temperature monitoring threshold, and the second monitoring threshold has a larger margin than the first monitoring threshold.

2. The method as described in claim 1, characterized in that, The first monitoring threshold is based on one or more of the following: AC excitation tolerance of the rotary transformer position sensor; Tolerance caused by cable voltage drop between the flap or slat computer and the rotary transformer position sensor; The error range of the transformer position sensor's turns ratio TR; Demodulation accuracy of position sensor information from flaps or slats in computers.

3. The method as described in claim 1, characterized in that, The split-type position sensor includes: A speed reduction mechanism and a sensor mechanism, wherein the sensor mechanism includes the rotary transformer; The housings of the deceleration mechanism and the sensor mechanism are connected by bolts. Furthermore, the deceleration mechanism is partially fixed to the aircraft structure. The sensor mechanism, as an independent route-changeable unit, is connected to the deceleration mechanism via a backlash-free gear.

4. The method as described in claim 3, characterized in that, The sensor mechanism includes a rotary transformer.

5. The method as described in claim 3, characterized in that: Holes are drilled at the root of the backlash-free gear and assembled using pins; The backlash-eliminating gear includes a fixed gear, a moving gear, a torsion spring, a washer, a shaft elastic retaining ring, and a pin, wherein the fixed gear is fixed to the input shaft end of the sensor mechanism, and the moving gear is internally connected to the fixed gear via a torsion spring.

6. The method as described in claim 5, characterized in that, Assembly using pins includes: Holes are drilled at the roots of the fixed gear and the moving gear to serve as pin holes; Rotate the moving gear to compress the torsion spring so that the tooth profiles of the fixed gear and the moving gear are aligned and a pin is inserted, so that the tooth profiles are aligned to facilitate meshing and connection; The backlash-free gear is meshed with the output shaft of the reduction mechanism; After the engagement is completed, the pin is pulled out, and the gear of the reduction mechanism is locked under the force of the torsion spring between the moving gear and the stationary gear to clamp the output shaft.

7. The method as described in claim 3, characterized in that: After the sensor mechanism and the deceleration mechanism are connected, a zeroing operation is performed.

Images