CN117308996A - Health monitoring method and system for jamming of attack angle sensor blade - Google Patents
Health monitoring method and system for jamming of attack angle sensor blade Download PDFInfo
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Abstract
The health monitoring method and system for the jamming of the blades of the angle of attack sensor comprise the following steps: acquiring attack angle detection data of historical flights, and acquiring an attack angle threshold interval according to the attack angle detection data of the cruising stage; acquiring attack angle detection data of a first attack angle sensor, a second attack angle sensor and a third attack angle sensor of an airplane to be detected in a take-off stage, and calculating difference values between the attack angle detection data recorded by the three sensors at the same moment in the take-off stage to obtain a 1-2 difference value group, a 1-3 difference value group and a 2-3 difference value group; respectively performing probability density function fitting on the three difference value groups to obtain 1-2 offset, 1-3 offset and 2-3 offset; and the three offset values are subjected to one-to-one correspondence difference with the three offset values of the attack angle sensor of a normal aircraft, the health degree of the attack angle sensor is judged according to the difference value, the long-term monitoring of the health condition of the attack angle sensor blade is realized, the flight safety of the aircraft is ensured, and the maintenance efficiency of the aircraft is improved.
Description
Technical Field
The invention relates to the field of aircraft anomaly detection, in particular to the field of a health monitoring method and a system of an attack angle sensor.
Background
Referring to fig. 1, fig. 1 is a schematic view of an angle of attack of an aircraft, and for a fixed wing aircraft, an angle between a direction of wing relative to airflow and a chord (different from a fuselage axis) is called an angle of attack (α angle), which is a reference for determining an angle of attack of a wing in airflow. The aircraft uses an attack angle sensor to detect the attack angle, sends the attack angle to ADIRU calculation output and sends the attack angle to a flight control computer, and essentially calculates the lift force condition of the aircraft by using the attack angle, so that the safe flight of the aircraft is controlled, and the civil aircraft has instantaneous attack angle calculation and monitoring on the attack angle sensor because the attack angle is the basis of the flight attitude and the flight control and the flight lift force, but lacks long-term health monitoring on the attack angle blade of the attack angle sensor. And the flight angle is regulated and controlled according to the attack angle detected by the attack angle sensor in the navigation process of the aircraft, when the attack angle sensor fails, the accident stop of the aircraft can be caused, the difficulty in flight control is caused when the accident stop is serious, and the problems of the aircraft such as the flight stop and the like can be further caused seriously.
Disclosure of Invention
Based on the problems, the method comprises the steps of determining the normal attack angle threshold interval of the attack angle sensor of the aircraft unit by utilizing big data, carrying out difference operation on detection data of three attack angle sensors of the aircraft to be detected in a take-off stage to obtain three difference groups, then respectively carrying out probability density function fitting on the three difference groups to obtain the distribution of the three difference groups, judging the operation condition of the attack angle sensor according to the attack angle detection data difference distribution among the attack angle sensors in the take-off stage, and finally realizing long-term health monitoring on jamming of attack angle blades of the attack angle sensor, ensuring the flight safety of the aircraft and reducing the maintenance difficulty of the aircraft.
The invention is realized by the following technical scheme:
in one aspect, the invention provides a health monitoring method for blade jamming of an attack angle sensor, comprising the following steps:
acquiring attack angle detection data of historical flights, and acquiring an attack angle threshold interval according to the attack angle detection data of the historical flights in a cruising stage;
acquiring attack angle detection data of a first attack angle sensor, a second attack angle sensor and a third attack angle sensor of an aircraft to be detected in a take-off stage, and calculating difference values between the attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage to obtain a 1-2 difference value group, a 1-3 difference value group and a 2-3 difference value group;
respectively performing probability density function fitting on the three difference value groups to obtain 1-2 offset, 1-3 offset and 2-3 offset;
and carrying out difference solving on the three offset values and the 1-2 offset values, the 1-3 offset values and the 2-3 offset values of the attack angle sensor of a normal airplane in a one-to-one correspondence manner, and judging the health degree of the attack angle sensor according to the difference values.
Further, the health monitoring method for the jamming of the attack angle sensor blade provided by the invention further comprises the following steps:
and decoding and scale transforming the acquired attack angle detection data in advance, and unifying the recording time intervals of all the attack angle detection data.
Further, after acquiring the attack angle detection data of the first attack angle sensor, the second attack angle sensor and the third attack angle sensor in the take-off stage in the single flight, the method further comprises the following steps:
and calculating the number of parameters which are not in the attack angle threshold value interval in the attack angle detection data, and if the number of parameters which are not in the attack angle threshold value interval exceeds a threshold value, calculating the difference value between the attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage.
Further, the probability density function is specifically as follows:
wherein x is a single attack angle detection value, f (x) is the total data amount of which the attack angle detection value is x, and u is the average value; sigma is variance.
On the other hand, the invention also provides a health monitoring system for the jamming of the attack angle sensor blade, which comprises:
a threshold interval generation module: the method comprises the steps of acquiring attack angle detection data of historical flights, and acquiring an attack angle threshold interval according to the attack angle detection data of the historical flights in a cruising stage;
the attack angle detection data difference value calculation module: the method comprises the steps of acquiring attack angle detection data of a first attack angle sensor, a second attack angle sensor and a third attack angle sensor of an aircraft to be detected in a take-off stage, and calculating difference values between the attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage to obtain a 1-2 difference value group, a 1-3 difference value group and a 2-3 difference value group;
an attack angle detection data offset calculating module: the method comprises the steps of respectively carrying out probability density function fitting on the three difference value groups to obtain 1-2 offset, 1-3 offset and 2-3 offset;
the attack angle sensor health evaluation module: and the three offset values are used for carrying out one-to-one correspondence between the three offset values and 1-2 offset values, 1-3 offset values and 2-3 offset values of an attack angle sensor of a normal aircraft, and judging the health degree of the attack angle sensor according to the difference values.
Further, the health monitoring system for blade sticking of the attack angle sensor further comprises:
and a data preprocessing module: the method is used for decoding and scale-transforming the acquired attack angle detection data in advance and unifying the recording time intervals of all the attack angle detection data.
Further, the attack angle detection data difference value calculating module further includes:
fault pre-determination submodule: and the method is used for calculating the number of all parameters which are not in the attack angle threshold value interval in the attack angle detection data, and calculating the difference value between every two attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage if the number of the parameters which are not in the attack angle threshold value interval exceeds a threshold value.
In another aspect, the present invention also provides a computer device comprising at least one memory and at least one processor;
the memory is used for storing one or more programs; the one or more programs, when executed by the at least one processor, cause the at least one processor to implement the steps of a method of health monitoring of angle of attack sensor blade stuck as set forth in any of the preceding claims.
In another aspect, the present invention also provides a computer readable storage medium storing a computer program, which when executed by a processor, implements the steps of a method for monitoring the health of an angle of attack sensor blade stuck as set forth in any one of the preceding claims.
In summary, the health monitoring method for the jamming of the blades of the attack angle sensor provided by the invention is based on the health monitoring system of the attack angle sensor, firstly, the attack angle detection data of each historical flight of a target type aircraft are obtained, a normal attack angle threshold interval is determined according to the attack angle detection data of a cruising stage, the attack angle detection data of three attack angle sensors detected by the aircraft to be detected in a take-off stage are obtained, whether the abnormality exists is judged according to the data quantity exceeding the attack angle threshold interval, if the abnormality exists, the attack angle detection data recorded by the three attack angle sensors at the same moment are subjected to difference between every two to obtain three groups of difference values, three probability distribution fitting is respectively carried out according to the data of the three groups of difference values, the distribution rule of the difference values is found, and three offset values are obtained. And comparing the three offset values with a pre-stored standard offset value, finding an attack angle sensor which participates in calculation of the two offset values simultaneously when the difference value between the two offset values and the standard offset value exceeds a preset threshold value, prompting that the sensor needs to be replaced, effectively monitoring the health condition of the attack angle sensor blade for a long time, ensuring the flight safety of an airplane, and improving the maintenance efficiency of the airplane.
For a better understanding and implementation, the present invention is described in detail below with reference to the drawings.
Drawings
FIG. 1 is a schematic view of the angle of attack of an aircraft;
FIG. 2 is a flow chart of a method for health monitoring of an angle of attack sensor according to the present invention;
FIG. 3 is a block diagram of a health monitoring system that performs the angle of attack blade jamming of FIG. 2;
fig. 4 is a time-dependent change of the angle of attack of the aircraft in the take-off phase.
Detailed Description
Aiming at the problem that the aircraft has jamming of the angle of attack sensor in the background art, the inventor conducts intensive study on the jamming reason of the fault angle of attack sensor, firstly conducts friction force test on the fault angle of attack sensor, finds that friction force of all measurement points of each fault angle of attack sensor exceeds standard, further disassembles the fault angle of attack sensor, and finds that obvious jamming condition exists when the outer bearing rotates and jamming condition exists in the inner bearing. After the bearing dust cover is decomposed, grease inside the bearing is dried and blackened, a plurality of sediments are found after the bearing dust cover is cleaned, and the disassembled part is further decomposed and checked, so that a large amount of sediments which are slowly formed in the interior are found. These deposits affect the bearing rotation causing jamming of the angle of attack sensor which requires replacement or repair when they accumulate to have affected the normal voyage of the aircraft. However, the attack angle sensor cannot be replaced every time or at fixed intervals in the aircraft maintenance process, but is replaced after the fault, and after the attack angle sensor has a problem, the aircraft is required to stop nearby and then emergency ordering parts are replaced, so that the navigation is safe, and great hidden danger exists in the aircraft maintenance. In order to solve the above problems, a method capable of monitoring the health condition of the angle of attack sensor for a long period of time is urgently needed.
Based on this, the present invention provides a health monitoring method and system for an attack angle sensor, please refer to fig. 2 and 3, fig. 2 is a flowchart of the health monitoring method for an attack angle sensor of the present invention, and fig. 3 is a block diagram of a health monitoring system for executing the attack angle blade clamping stagnation of fig. 2. The health monitoring method of the attack angle sensor specifically comprises the following steps:
s10: and acquiring the attack angle detection data of the historical flight, and acquiring an attack angle threshold interval according to the attack angle detection data of the historical flight in the cruising stage. Step S10 is performed by the threshold interval generation module 10.
An aircraft can be generally divided into three stages in a voyage mission: a take-off stage, a cruising stage and a landing stage; of these three phases, the cruise phase is operated with steady movement in the horizontal direction and with little longitudinal displacement, so that the cruise phase can be regarded as a steady operation. In an ideal situation, the angle of attack should be 0 ° during cruising, but due to the interference of the air-powered waves, the effect of boundary layers, the effect of the washing flow of the fuselage or other appearance parts of the aircraft, etc. The angle of attack will be caused to fluctuate around 0 deg., so that a normal angle of attack threshold interval is determined from the angle of attack detection data during the cruise phase.
In another embodiment, the obtained attack angle detection data is decoded and scaled in advance, and recording time intervals of all attack angle detection data are unified. This step is performed by the data preprocessing module.
The existing aircraft units collect various system data of the aircraft through FDIMU (flight data interface management component) and transmit the data to DAR (digital aircraft integrated data recorder) and QAR (flight recorder), but the formats of the data recorded by different aircraft units are not uniform, the data types or byte lengths are different, the format differences of 1024/512/256WPS are different for the byte lengths, and finally the data types can be read through decoding and conversion by decoding software. Therefore, when data monitoring is carried out, the model of the aircraft and the configuration FDIMU/DAR/QAR of the aircraft storage equipment are firstly determined to carry out decoding under different conditions, and the recording parameters of one navigation section are restored; this data preprocessing affects whether the operation of the subsequent steps is one second for one frame or one second for multiple frames, but the final result is easily affected due to the fact that the data formats are not uniform. The invention decodes and scale-transforms the data in advance, unifies all the data formats, unifies the incidence angle detection data to record time intervals, keeps the uniformity of data dimension, ensures the accuracy of calculation, and converts the collection time interval of the finally operated incidence angle data into a second level according to the requirement of data monitoring.
S20: acquiring attack angle detection data of a first attack angle sensor, a second attack angle sensor and a third attack angle sensor of an airplane to be detected in a take-off stage, and calculating differences between attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage to obtain a 1-2 difference group, a 1-3 difference group and a 2-3 difference group. Step S20 is performed by the attack angle detection data difference calculation module.
The take-off stage and the landing stage of the aircraft are accompanied by climbing and landing of the aircraft during one-time cruising, which means that the take-off and landing are accompanied by severe attack angle changes, and the lifting of the aircraft is regulated according to the attack angle changes, so that the take-off stage and the landing stage are dynamically changed by attack angle detection data. Referring to fig. 4, fig. 4 shows a time-dependent change process of an attack angle of an aircraft in a take-off stage provided by the invention, it can be seen that the take-off process of the aircraft can be divided into a linear static part and a nonlinear part, and corresponds to the process of accelerating the aircraft from sliding to climbing off the ground, accelerating the aircraft nose from a static state, sliding the aircraft, lifting the aircraft horizontally, and taking off the aircraft off the ground, in which, in the process, initial attack angle data exceeds an attack angle threshold interval, but with climbing of the aircraft, a normal attack angle sensor rapidly reduces an output attack angle detection value according to a track angle of the aircraft and a speed vector of the aircraft to return to the attack angle threshold interval; the time for the attack angle detection value output by the failure attack angle sensor to return to the attack angle threshold value interval becomes longer than that of the normal attack angle sensor because the blade of the failure attack angle sensor is jammed. However, due to different flight settings and different airlines, the flight altitude of the same aircraft may change to cause climbing time, and only the time difference that the attack angle detection value output by the attack angle sensor returns to the attack angle threshold interval is not enough to accurately judge whether the attack angle sensor fails, based on the analysis of the invention, the inventor further analyzes that three attack angle sensors are provided on the aircraft, and the attack angle detection value between each attack angle sensor is consistent or the difference is small under normal conditions, so that the difference between the attack angle detection data of the three attack angle sensors is used as a judgment parameter, and the influence of different flight settings and different airlines on the judgment result can be ignored.
In another embodiment, after acquiring the attack angle detection data of the first attack angle sensor, the second attack angle sensor and the third attack angle sensor in the take-off stage in the single flight, the method further includes:
and calculating the number of parameters which are not in the attack angle threshold value interval in the attack angle detection data, and if the number of parameters which are not in the attack angle threshold value interval exceeds a threshold value, calculating the difference values of the attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage to obtain a 1-2 difference value group, a 1-3 difference value group and a 2-3 difference value group. The discrimination process of this step is performed by the failure pre-discrimination submodule.
The flight data is pre-screened, and as the time for the attack angle detection value output by the fault attack angle sensor to return to the attack angle threshold value interval is longer than that of a normal attack angle sensor, the number of parameters corresponding to the record is increased, so that the number of parameters which are not in the attack angle threshold value interval can be counted to preliminarily judge whether the attack angle sensor is likely to have faults, and if the number of the record parameters does not exceed a set threshold value, the situation that jamming does not occur can be considered, and the calculation resource is saved.
S30: and respectively performing probability density function fitting on the three difference value groups to obtain 1-2 offset, 1-3 offset and 2-3 offset. Step S30 is performed by the attack angle detection data offset calculation module 30.
Wherein the probability density function is:
wherein x is a single attack angle detection value, f (x) is the total data amount of which the attack angle detection value is x, and u is the average value; sigma is variance. . And calculating the average value corresponding to each difference value group by using a fitting tool as an offset, wherein mu can embody the areas in which the data set in one group of data is distributed on the image, so that the data distribution in three difference value groups is calculated to show the deviation degree of each attack angle sensor and the data detected by other attack angle sensors.
S40: and carrying out difference solving on the three offset values and the 1-2 offset values, the 1-3 offset values and the 2-3 offset values of the attack angle sensor of a normal airplane in a one-to-one correspondence manner, and judging the health degree of the attack angle sensor according to the difference values. Step S40 is performed by the angle of attack sensor health assessment module.
Taking 1-2 offset, 1-3 offset and 2-3 offset of an attack angle sensor of an aircraft under normal conditions as standard references, presetting different health zones, and determining the health degree of each attack angle sensor of the aircraft to be detected according to the difference value of the 1-2 offset, 1-3 offset and 2-3 offset of the aircraft to be detected and the standard 1-2 offset, 1-3 offset and 2-3 offset, wherein for example, the value of the defined offset in the zone [ -2.5,2.5] is better, belonging to an excellent zone (zone A), and the AOA can be quickly moved to the correct position along with airflow; [ -7.5, -2.5] and [2.5,7.5] are good zones (interval B), with the AOA being able to move quickly to the correct position with the air flow; [ -10, -7.5] and [7.5, 10] are that the clamping stagnation in the inner part of the declining zone (zone C) has a certain layering performance, and more than 10 or less than-10 are replacement zones, and need to be replaced. When the first angle of attack sensor fails and others are normal, the 1-2 offset should be greater than 10, then the 1-3 offset should also be greater than 10, and the 2-3 offset should be between [ -2.5,2.5 ]. Finally, the monitoring and the judgment of the health degree of each attack angle sensor are completed.
In summary, according to the health monitoring method for the jamming of the blades of the attack angle sensor provided by the invention, based on the health monitoring system of the attack angle sensor, attack angle detection data of each historical flight of a target type aircraft are firstly obtained, a normal attack angle threshold interval is determined according to the attack angle detection data of a cruising stage, attack angle detection data of three attack angle sensors detected by the aircraft to be detected in a take-off stage are obtained, whether abnormality exists or not is judged according to the data quantity exceeding the attack angle threshold interval, if abnormality exists, differences are obtained between every two attack angle detection data recorded by the three attack angle sensors at the same moment, three difference groups are obtained, three probability distribution fitting is respectively carried out according to the data of the three difference groups, the distribution rule of the difference groups is found, and three offset values are obtained. And comparing the three offset values with a pre-stored standard offset value, finding an attack angle sensor which participates in calculation of the two offset values simultaneously when the difference value between the two offset values and the standard offset value exceeds a preset threshold value, prompting that the sensor needs to be replaced, and effectively monitoring the health condition of the attack angle sensor blade and improving the maintenance efficiency of the aircraft.
Based on the same inventive concept, the present invention further provides an electronic device, which may be a terminal device such as a server, a desktop computing device, or a mobile computing device (e.g., a laptop computing device, a handheld computing device, a tablet computer, a netbook, etc.). The device comprises one or more processors and a memory, wherein the processors are used for executing programs to realize the health monitoring method of the blade clamping stagnation of the attack angle sensor; the memory is used for storing a computer program executable by the processor.
Based on the same inventive concept, the present invention also provides a computer readable storage medium, corresponding to the foregoing embodiment of a health monitoring method for blade jamming of an attack angle sensor, having stored thereon a computer program, which when executed by a processor, implements the steps described in any of the foregoing embodiments.
The present invention may take the form of a computer program product embodied on one or more storage media (including, but not limited to, magnetic disk storage, CD-ROM, optical storage, etc.) having program code embodied therein. Computer-usable storage media include both permanent and non-permanent, removable and non-removable media, and information storage may be implemented by any method or technology. The information may be computer readable instructions, data structures, modules of a program, or other data. Examples of storage media for a computer include, but are not limited to: phase change memory (PRAM), static Random Access Memory (SRAM), dynamic Random Access Memory (DRAM), other types of Random Access Memory (RAM), read Only Memory (ROM), electrically Erasable Programmable Read Only Memory (EEPROM), flash memory or other memory technology, compact disc read only memory (CD-ROM), digital Versatile Disks (DVD) or other optical storage, magnetic cassettes, magnetic tape magnetic disk storage or other magnetic storage devices, or any other non-transmission medium, may be used to store information that may be accessed by the computing device.
The above examples illustrate only a few embodiments of the invention, which are described in detail and are not to be construed as limiting the scope of the invention. It should be noted that modifications and improvements can be made by those skilled in the art without departing from the spirit of the invention, and the invention is intended to encompass such modifications and improvements.
Claims (9)
1. A health monitoring method for blade clamping stagnation of an attack angle sensor comprises the following steps:
acquiring attack angle detection data of historical flights, and acquiring an attack angle threshold interval according to the attack angle detection data of the historical flights in a cruising stage;
acquiring attack angle detection data of a first attack angle sensor, a second attack angle sensor and a third attack angle sensor of an aircraft to be detected in a take-off stage, and calculating difference values between the attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage to obtain a 1-2 difference value group, a 1-3 difference value group and a 2-3 difference value group;
respectively performing probability density function fitting on the three difference value groups to obtain 1-2 offset, 1-3 offset and 2-3 offset;
and carrying out difference solving on the three offset values and the 1-2 offset values, the 1-3 offset values and the 2-3 offset values of the attack angle sensor of a normal airplane in a one-to-one correspondence manner, and judging the health degree of the attack angle sensor according to the difference values.
2. The method for health monitoring of angle of attack sensor blade sticking in accordance with claim 1, further comprising:
and decoding and scale transforming the acquired attack angle detection data in advance, and unifying the recording time intervals of all the attack angle detection data.
3. The method for monitoring the health of the blade jamming of the attack angle sensor according to claim 2, wherein after acquiring the attack angle detection data of the first attack angle sensor, the second attack angle sensor and the third attack angle sensor in the take-off phase in a single flight, further comprises:
and calculating the number of parameters which are not in the attack angle threshold value interval in the attack angle detection data, and if the number of parameters which are not in the attack angle threshold value interval exceeds a threshold value, calculating the difference value between the attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage.
4. A method for health monitoring of angle of attack sensor blade sticking according to claim 3, characterized in that the probability density function is specifically as follows:
wherein x is a single attack angle detection value, f (x) is the total data amount of which the attack angle detection value is x, and u is the average value; sigma is variance.
5. A health monitoring system for angle of attack sensor blade jamming, comprising:
a threshold interval generation module: the method comprises the steps of acquiring attack angle detection data of historical flights, and acquiring an attack angle threshold interval according to the attack angle detection data of the historical flights in a cruising stage;
the attack angle detection data difference value calculation module: the method comprises the steps of acquiring attack angle detection data of a first attack angle sensor, a second attack angle sensor and a third attack angle sensor of an aircraft to be detected in a take-off stage, and calculating difference values between the attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage to obtain a 1-2 difference value group, a 1-3 difference value group and a 2-3 difference value group;
an attack angle detection data offset calculating module: the method comprises the steps of respectively carrying out probability density function fitting on the three difference value groups to obtain 1-2 offset, 1-3 offset and 2-3 offset;
the attack angle sensor health evaluation module: and the three offset values are used for carrying out one-to-one correspondence between the three offset values and 1-2 offset values, 1-3 offset values and 2-3 offset values of an attack angle sensor of a normal aircraft, and judging the health degree of the attack angle sensor according to the difference values.
6. The angle of attack sensor blade stuck health monitoring system of claim 5, further comprising:
and a data preprocessing module: the method is used for decoding and scale-transforming the acquired attack angle detection data in advance and unifying the recording time intervals of all the attack angle detection data.
7. The system for health monitoring of angle of attack sensor blade sticking in accordance with claim 6, wherein said angle of attack detection data difference calculation module further comprises:
fault pre-determination submodule: and the method is used for calculating the number of all parameters which are not in the attack angle threshold value interval in the attack angle detection data, and calculating the difference value between every two attack angle detection data recorded by the first attack angle sensor, the second attack angle sensor and the third attack angle sensor at the same moment in the take-off stage if the number of the parameters which are not in the attack angle threshold value interval exceeds a threshold value.
8. A computer device, comprising:
at least one memory and at least one processor;
the memory is used for storing one or more programs;
when said one or more programs are executed by said at least one processor, said at least one processor implements the steps of a method for health monitoring of angle of attack sensor blade sticking as claimed in any of claims 1 to 4.
9. A computer readable storage medium storing a computer program, characterized in that the computer program when executed by a processor implements the steps of a method for health monitoring of angle of attack sensor blade sticking according to any of claims 1 to 4.
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| CN202311144671.0A CN117308996A (en) | 2023-09-06 | 2023-09-06 | Health monitoring method and system for jamming of attack angle sensor blade |
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| CN202311144671.0A CN117308996A (en) | 2023-09-06 | 2023-09-06 | Health monitoring method and system for jamming of attack angle sensor blade |
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