CN115320886A - Real-time monitoring method and system for aircraft control surface fault - Google Patents
Real-time monitoring method and system for aircraft control surface fault Download PDFInfo
- Publication number
- CN115320886A CN115320886A CN202211058249.9A CN202211058249A CN115320886A CN 115320886 A CN115320886 A CN 115320886A CN 202211058249 A CN202211058249 A CN 202211058249A CN 115320886 A CN115320886 A CN 115320886A
- Authority
- CN
- China
- Prior art keywords
- fault
- control surface
- aircraft
- information
- control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing And Monitoring For Control Systems (AREA)
Abstract
The invention relates to the field of fault diagnosis, and discloses a real-time monitoring method and a system for aircraft control surface faults, wherein the method comprises the steps of classifying the mechanical energy of the aircraft control surface fault information, creating a flight model of the aircraft in a fault state, obtaining different aircraft control surface fault data through the flight model of the aircraft in the fault state, and detecting the different aircraft control surface fault data through a control surface fault detector, wherein a local steering engine fault comparator detects aircraft fault detection data of control surface blocking fault information and control surface floating fault information; the aircraft fault detection data of the control plane fault information is detected by part of the steering engine fault detectors, so that the fault information of the control plane is comprehensively detected, the detected data is judged through judgment logic in a flight control system, and the fault information of the control plane is rapidly detected and monitored.
Description
Technical Field
The invention relates to the field of fault diagnosis, in particular to a method and a system for monitoring faults of an aircraft control surface in real time.
Background
The control surface system is an important component of the aircraft, particularly an aileron, an elevator and a rudder which are used as main control surfaces, and once the aileron, the elevator and the rudder break down, the stability of a flight control system is reduced, false alarms and passengers are panic, and the aircraft is directly crashed if the aileron, the elevator and the rudder break down, so that great personnel and property losses and negative public opinions occur. At present, aircraft fault diagnosis technology is gradually and vigorously developed, and the aim is to predict and identify faults in advance, and feed back diagnosis results to drivers/ground service personnel so that the drivers/ground service personnel can adopt reasonable control strategies and maintenance strategies to avoid faults or reduce loss caused by faults as much as possible.
Part of response signals of the aircraft control surface system before and after the fault occurs can show different characteristics from the normal state, and the data difference contains rich information. And then, effective prediction diagnosis is carried out on unknown samples, and real-time monitoring is carried out on the airplane. From the research and application situation of intelligent fault diagnosis technology, the development prospect of the intelligent fault diagnosis technology in the aerospace field is promising and has great potential in the future.
The flight control system of the aircraft transmits flight data information to a flight control computer through measuring devices such as a sensor, and other automatic control units send control instructions according to flight attitude information to control the deflection of the control surface of the aircraft, so that the aircraft stably flies according to a preset track on the premise of keeping stable attitude. However, because the control surface system of the aircraft, which is affected by extreme weather and constantly changing stress, works in the atmosphere turbulence environment, the control surface system is inevitably interfered and affected by the external environment, and simultaneously, because the structure of the aircraft is complex and the flight environment condition is severe, the control surface component is easy to break down, so that the monitoring accuracy requirement of the aircraft on the fault information received by the control surface component in the flight process is also very high.
Disclosure of Invention
The invention provides a method and a system for monitoring the fault of an aircraft control surface in real time, aiming at the problems that the fault information of the aircraft control surface component in real time is low in monitoring accuracy and potential safety hazards exist in the prior art, so that the fault information of the control surface component is effectively monitored in real time, the monitoring information is effectively fed back, the detection accuracy is effectively improved, and the safety of the aircraft in the flight process is ensured.
The invention is realized by the following technical scheme:
a real-time monitoring method for aircraft control surface faults comprises the following steps:
classifying the fault information of the control surface of the aircraft;
creating a flight model of the aircraft under the control surface fault state, and inputting the classified fault information of the control surface of the aircraft into the flight model under the control surface fault state of the aircraft to obtain different fault data of the control surface of the aircraft;
correspondingly detecting the fault data of the control surfaces of different aircrafts to obtain fault detection data of different aircrafts;
and judging different flight detection data respectively to complete real-time monitoring of the faults of the control surface of the aircraft.
Preferably, the fault information of the control surface of the aircraft comprises the fault information of the dead locking of the control surface, the fault information of the floating of the control surface and the fault information of the defect of the control surface.
Further, the calculation formula of the flight model in the aircraft control surface fault state is as follows:
wherein X ∈ R n×1 Is a system state vector; y belongs to R m×1 Outputting a state vector for the system; u is formed by R m×1 Outputting a vector for system control; a is an element of R n×n ；C∈R m×n ；B＝[b 1 b 2 …b n ]∈R m×n 。
Preferably, different aircraft control surface fault data are respectively and correspondingly detected through a local steering engine fault comparator and a partial steering engine defect detector to obtain different aircraft fault detection data.
Further, a local steering engine fault comparator detects aircraft fault detection data of control surface blocking fault information and control surface floating fault information; and the partial steering engine defect detector detects aircraft fault detection data of the control surface defect fault information.
Furthermore, the method for detecting the aircraft fault detection data of the control surface stuck fault information and the control surface floating fault information by the local steering engine fault comparator comprises the following steps:
the local steering engine fault comparator receives control surface deflection angle information, control surface control quantity information and attack angle information in the control surface stuck fault information and the control surface floating fault information through a control surface sensor, sets tolerance according to the received control surface deflection angle information, control surface control quantity information and attack angle information, judges whether the control surface deflection angle information, the control surface control quantity information and the attack angle information are in the tolerance range, and if the control surface deflection angle information, the control surface control quantity information and the attack angle information are in the tolerance range, the control surface control quantity information and the attack angle information are in a normal state, otherwise, the control surface stuck fault or the control surface floating fault is detected.
Furthermore, the method for detecting the aircraft fault detection data of the control surface fault information through the partial steering engine fault detector comprises the following steps:
the method comprises the steps of establishing a flight model of the aircraft control surface in a normal state, identifying the defect condition of the control surface, comparing the defect condition of the control surface with the flight model of the aircraft control surface in the normal state to obtain residual error information, inputting the residual error information into a part of steering engine defect detectors, setting a tolerance according to the residual error information, judging whether the residual error information is in a tolerance range, if so, judging that the aircraft control surface is in a normal state, otherwise, judging that the aircraft control surface is in a defect fault.
Furthermore, the calculation formula of the flight model of the aircraft under the normal state of the control surface is as follows:
Y(t)＝CX(t)
wherein X ∈ R n×1 Is a system state vector; y belongs to R m×1 Outputting state vectors for a system；U∈R m×1 Outputting a vector for system control; a is an element of R n×n ；C∈R m×n ；B＝[b 1 b 2 …b n ]∈R m×n ；f i Indicating the type of the fault; a is i And (t) is an arbitrary time function and reflects the influence of the fault.
An aircraft control surface fault real-time monitoring system comprising:
the classification module is used for classifying the fault information of the control surface of the aircraft;
the processing module is used for creating a flight model of the aircraft under the control surface fault state, and inputting the classified aircraft control surface fault information into the flight model of the aircraft under the control surface fault state to obtain different aircraft control surface fault data;
the data monitoring module is used for correspondingly detecting the fault data of the control surfaces of different aircrafts to obtain fault detection data of different aircrafts;
and the data judgment module is used for respectively judging different flight detection data to complete real-time monitoring of the faults of the control surface of the aircraft.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a real-time monitoring method for aircraft control surface faults, which comprises the steps of classifying mechanical energy of aircraft control surface fault information, creating a flight model of the aircraft in a fault state of the control surface, obtaining different aircraft control surface fault data through the flight model of the aircraft in the fault state of the control surface, and detecting the different aircraft control surface fault data through a control surface fault detector, wherein a local steering engine fault comparator detects aircraft fault detection data of control surface jamming fault information and control surface floating fault information; and detecting aircraft fault detection data of control surface fault information by a part of steering engine fault detectors. The method identifies the fault of the control surface of the airplane according to the flight data generated in the actual flight process of the airplane, monitors the working state of the airplane steering engine in real time and effectively protects the health state of the control surface of the airplane.
Drawings
FIG. 1 is a flow chart of a real-time monitoring method for aircraft control surface faults in the invention;
FIG. 2 is a schematic diagram of a real-time monitoring system for aircraft control surface faults in the present invention;
FIG. 3 is a flow chart of the aircraft flight control system monitoring control surfaces of the present invention;
FIG. 4 is a schematic diagram of the aircraft flight control system for identifying and monitoring faults of the control surfaces of the aircraft.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein. Moreover, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The invention is described in further detail below with reference to the accompanying drawings:
the invention provides a method and a system for monitoring the fault of a control surface of an aircraft in real time, which can effectively monitor the fault information of a control surface component in real time, effectively feed back the monitoring information, effectively improve the detection accuracy and ensure the safety of the flight process of the aircraft.
Specifically, as shown in fig. 1, the method for monitoring the fault of the control surface of the aircraft in real time includes the following steps:
s1, classifying fault information of an aircraft control surface;
according to the physical model, as shown in fig. 3, the control surface control component of the aircraft is composed of a booster and a steering engine, the command signal of the control surface control component is given by the control law of the flight control system, the response signal is obtained by a line displacement sensor in the system, and the faults related to the control surface system in the basic composition structure of the aircraft mainly include: actuator faults, sensor faults, system state changes, and model biases. In actual flight, when organism itself or control surface system physical structure appear damaging the phenomenon such as, directly change the structural performance of object, promptly: system states and model parameters change.
1) Failure of the actuator:
the actuator plays a very important role in all components of the control surface system, and the fault behavior of the actuator not only can cause the characteristics of response signals of the control surface system to change, but also can cause the failure or breakdown of the flight control system, thereby seriously affecting the dynamic performance and the flight safety of the aircraft.
For the control surface system, the actuator is the most frequently used physical component, and therefore, the actuator is also the most frequently-failed part. Generally, the fault behavior of an actuator of a flight control system includes the following types: stuck faults, loose faults and defective faults.
1) Sensor failure:
sensor faults are also a representative class of faults in aircraft diagnostics. The device is used as a measurement component of flight data and state information, and provides various data information for a flight control computer in the whole loop. If the sensor fails, the fed back measurement signals are abnormal, and great threat is generated to flight safety. For a sensor in a flight control system, the fault types of the sensor mainly comprise a dead lock fault, a gain fault and a deviation failure.
Faults which can occur to the control surface of the airplane comprise dead locking faults, floating faults, defect faults, gain faults and sensor deviation faults of the control surface.
And (3) jamming failure: the actuator of the control surface system is fixed at a certain position, the output no longer responds to the input command, and the mathematical description is as follows:
d is a constant value and represents the position where the control surface is stuck when a fault occurs. In a practical system, the response output of the control surface has a certain physical range u omin And u omax Beyond this range the control surface output is unchanged, i.e.: u. of omin ≤d≤u omax 。
Loosening and floating faults: a failure mode accompanied by irregular deviation, in which the response signal of the actuator shows irregular random drift around the normal value, is described mathematically as follows:
u o (t)＝u i (t)+Δ(t)
Δ (t) is the irregular disturbance signal and the noise impact.
Defect and fault: the gain of the actuator does not achieve the desired effect, and the control signal deviates to a varying degree, resulting in a change in the performance, which is mathematically described as follows:
eta is a gain coefficient, 0 is greater than or equal to eta is less than or equal to 1, and eta can be a constant value or can be variable. When eta =0, the actuator is equivalently stuck at a zero offset position; when eta =1, the actuator works normally and no fault occurs.
And (4) gain failure: the signal actually measured by the sensor and the theoretical expected value are in a proportional relation, and the proportionality coefficient is a constant or variable, and the mathematical expression of the proportionality coefficient is as follows:
sensor deviation: there is a constant deviation between the signal actually measured by the sensor and the theoretically expected value. The mathematical expression is as follows:
s2, creating a flight model of the aircraft in the control surface fault state, and inputting the classified fault information of the control surface of the aircraft into the flight model of the aircraft in the control surface fault state to obtain different fault data of the control surface of the aircraft;
the calculation formula of the flight model under the aircraft control surface fault state is as follows:
wherein X ∈ R n×1 Is a system state vector; y belongs to R m×1 Outputting a state vector for the system; u is formed by R m×1 Outputting a vector for system control; a is an element of R n×n ；C∈R m×n ；B＝[b 1 b 2 …b n ]∈R m×n 。
S3, correspondingly detecting the fault data of the control surfaces of different aircrafts to obtain fault detection data of different aircrafts;
specifically, different aircraft control surface fault data are respectively and correspondingly detected through a local steering engine fault comparator and a partial steering engine defect detector to obtain different aircraft fault detection data; the local steering engine fault comparator detects aircraft fault detection data of control surface stuck fault information and control surface floating fault information; and detecting aircraft fault detection data of control surface fault information by a part of steering engine fault detectors.
As shown in fig. 4, the method for detecting the aircraft fault detection data of the control surface stuck fault information and the control surface floating fault information by using the local steering engine fault comparator comprises the following steps:
the local steering engine fault comparator receives control surface deflection angle information, control surface control quantity information and attack angle information in control surface stuck fault information and control surface floating fault information through a control surface sensor, sets tolerance according to the received control surface deflection angle information, control surface control quantity information and attack angle information, and judges whether the control surface deflection angle information, the control surface control quantity information and the attack angle information are in the tolerance range, if so, the local steering engine fault comparator is in a normal state, otherwise, the local steering engine fault comparator is in a control surface stuck fault or a control surface floating fault.
As shown in fig. 4, the method for detecting the aircraft fault detection data of the control surface defect fault information by the partial steering engine defect detector is as follows:
the method comprises the steps of establishing a flight model of the aircraft control surface in a normal state, identifying the defect condition of the control surface, comparing the defect condition of the control surface with the flight model of the aircraft control surface in the normal state to obtain residual error information, inputting the residual error information into a part of steering engine defect detectors, setting a tolerance according to the residual error information, judging whether the residual error information is in a tolerance range, if so, judging that the aircraft control surface is in a normal state, otherwise, judging that the aircraft control surface is in a defect fault.
The calculation formula of the flight model of the aircraft under the normal state of the control surface is as follows:
Y(t)＝CX(t)
wherein X ∈ R n×1 Is a system state vector; y is formed by the element R m×1 Outputting a state vector for the system; u is formed by R m×1 Outputting a vector for system control; a is an element of R n×n ；C∈R m×n ；B＝[b 1 b 2 …b n ]∈R m×n ；f i Indicating the type of the fault; a is i And (t) is an arbitrary time function and reflects the influence of the fault.
Modeling of the control surface system is:
where xi is the damping ratio of the system and ω is n Is the natural frequency of the system.
And S4, judging different flight detection data respectively to complete real-time monitoring of the faults of the control surface of the aircraft.
When the control surface is blocked, the deflection angle of the control surface is not equal to a control signal of deflection of the control surface, namely W is not equal to Wc. Whether the actual deflection angle of the control surface follows the control signal or not is judged through a comparator in the fault detection of the local steering engine, or whether the deflection angle of the control surface is kept unchanged or not is judged, and whether the control surface has a stuck fault or not can be known. The position of the control surface stuck can be obtained by measuring W.
When the control surface has floating fault, the control surface becomes a vane and deflects along with the change of the T angle. And comparing the change relation of W along with the T angle by a comparator to judge whether the control surface has a floating fault.
When the control surface has partial defect faults, the detection filter can judge whether the control surface has residual control surface or not and judge the residual efficiency of the control surface by comparing the output error residual error between the airplane state and the intact airplane model.
In summary, the invention provides a real-time monitoring method for aircraft control surface faults, which classifies the mechanical energy of aircraft control surface fault information, creates a flight model in the fault state of the aircraft control surface, obtains different aircraft control surface fault data through the flight model in the fault state of the aircraft control surface, and detects the different aircraft control surface fault data through a control surface fault detector, wherein a local steering engine fault comparator detects the aircraft fault detection data of the control surface stuck fault information and the control surface floating fault information; and detecting aircraft fault detection data of control surface fault information by a part of steering engine fault detectors. The method realizes comprehensive detection of fault information of the control surface, judges the detected data through judgment logic in the flight control system, and realizes quick detection and implementation monitoring of the fault information of the control surface.
According to fig. 2, the invention also provides an aircraft control surface fault real-time monitoring system, which comprises a classification module, a processing module, a data monitoring module and a data judging module;
the classification module is used for classifying the fault information of the control surface of the aircraft;
the processing module is used for creating a flight model of the aircraft under the control surface fault state, and inputting the classified aircraft control surface fault information into the flight model of the aircraft under the control surface fault state to obtain different aircraft control surface fault data;
the data monitoring module is used for correspondingly detecting fault data of different aircraft control surfaces to obtain fault detection data of different aircraft;
and the data judgment module is used for respectively judging different flight detection data to complete real-time monitoring of the faults of the control surface of the aircraft.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting the same, and although the present invention is described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications and equivalents may be made to the embodiments of the invention without departing from the spirit and scope of the invention, which is to be covered by the claims.
Claims (9)
1. A real-time monitoring method for aircraft control surface faults is characterized by comprising the following steps:
classifying the fault information of the control surface of the aircraft;
creating a flight model of the aircraft under the control surface fault state, and inputting the classified fault information of the control surface of the aircraft into the flight model under the control surface fault state of the aircraft to obtain different fault data of the control surface of the aircraft;
correspondingly detecting fault data of different aircraft control surfaces to obtain fault detection data of different aircraft;
and judging different flight detection data respectively to complete real-time monitoring of the faults of the control surface of the aircraft.
2. The real-time monitoring method for the faults of the control surfaces of the aircraft according to claim 1, wherein the fault information of the control surfaces of the aircraft comprises control surface stuck fault information, control surface floating fault information and control surface defect fault information.
3. The method for monitoring the fault of the control surface of the aircraft in real time according to claim 2, wherein a calculation formula of a flight model in the fault state of the control surface of the aircraft is as follows:
wherein X ∈ R n×1 Is a system state vector; y is formed by the element R m×1 Outputting a state vector for the system; u is formed by R m×1 Outputting a vector for system control; a is an element of R n×n ；C∈R m×n ；B＝[b 1 b 2 …b n ]∈R m×n 。
4. The method for monitoring the faults of the control surfaces of the aircraft in real time according to claim 1, wherein different fault detection data of the aircraft are obtained by respectively and correspondingly detecting different fault data of the control surfaces of the aircraft through a local steering engine fault comparator and a partial steering engine defect detector.
5. The real-time monitoring method for the faults of the control surfaces of the aircraft as claimed in claim 4, wherein the local steering engine fault comparator detects aircraft fault detection data of control surface stuck fault information and control surface floating fault information; and detecting aircraft fault detection data of control surface fault information by a part of steering engine fault detectors.
6. The method for monitoring the faults of the control surfaces of the aircraft in real time according to claim 5, wherein the method for detecting the aircraft fault detection data of the control surface stuck fault information and the control surface floating fault information through the local steering engine fault comparator comprises the following steps:
the local steering engine fault comparator receives control surface deflection angle information, control surface control quantity information and attack angle information in the control surface stuck fault information and the control surface floating fault information through a control surface sensor, sets tolerance according to the received control surface deflection angle information, control surface control quantity information and attack angle information, judges whether the control surface deflection angle information, the control surface control quantity information and the attack angle information are in the tolerance range, and if the control surface deflection angle information, the control surface control quantity information and the attack angle information are in the tolerance range, the control surface control quantity information and the attack angle information are in a normal state, otherwise, the control surface stuck fault or the control surface floating fault is detected.
7. The method for monitoring the fault of the control surface of the aircraft in real time according to claim 5, wherein the method for detecting the fault detection data of the aircraft of the fault information of the control surface through a part of steering engine fault detectors comprises the following steps:
the method comprises the steps of establishing a flight model of the aircraft control surface in a normal state, identifying the defect condition of the control surface, comparing the defect condition of the control surface with the flight model of the aircraft control surface in the normal state to obtain residual information, inputting the residual information into a part of steering engine defect detectors, setting a tolerance according to the residual information, judging whether the residual information is in the tolerance range, if so, judging the aircraft control surface is in the normal state, otherwise, judging the aircraft control surface defect fault.
8. The method for monitoring the faults of the control surfaces of the aircraft in real time according to claim 7, wherein a calculation formula of a flight model of the control surfaces of the aircraft in a normal state is as follows:
Y(t)＝CX(t)
wherein X ∈ R n×1 Is a system state vector; y is formed by the element R m×1 Outputting a state vector for the system; u is formed by R m×1 Outputting a vector for system control; a is an element of R n×n ；C∈R m×n ；B＝[b 1 b 2 …b n ]∈R m×n ；f i Indicating the type of the fault; a is a i And (t) is an arbitrary time function and reflects the influence of the fault.
9. An aircraft control surface fault real-time monitoring system, comprising:
the classification module is used for classifying the fault information of the control surface of the aircraft;
the processing module is used for creating a flight model of the aircraft under the control surface fault state, and inputting the classified aircraft control surface fault information into the flight model of the aircraft under the control surface fault state to obtain different aircraft control surface fault data;
the data monitoring module is used for correspondingly detecting fault data of different aircraft control surfaces to obtain fault detection data of different aircraft;
and the data judgment module is used for respectively judging different flight detection data to complete the real-time monitoring of the faults of the control surface of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211058249.9A CN115320886A (en) | 2022-08-31 | 2022-08-31 | Real-time monitoring method and system for aircraft control surface fault |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211058249.9A CN115320886A (en) | 2022-08-31 | 2022-08-31 | Real-time monitoring method and system for aircraft control surface fault |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115320886A true CN115320886A (en) | 2022-11-11 |
Family
ID=83928621
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211058249.9A Pending CN115320886A (en) | 2022-08-31 | 2022-08-31 | Real-time monitoring method and system for aircraft control surface fault |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115320886A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115993075A (en) * | 2022-11-14 | 2023-04-21 | 南京航空航天大学 | Missile control surface fault detection method based on SSLLE and self-adaptive threshold |
| CN117171681A (en) * | 2023-11-03 | 2023-12-05 | 贵州大学 | Unmanned plane control surface intelligent fault diagnosis method and device under unbalanced small sample |
-
2022
- 2022-08-31 CN CN202211058249.9A patent/CN115320886A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115993075A (en) * | 2022-11-14 | 2023-04-21 | 南京航空航天大学 | Missile control surface fault detection method based on SSLLE and self-adaptive threshold |
| CN117171681A (en) * | 2023-11-03 | 2023-12-05 | 贵州大学 | Unmanned plane control surface intelligent fault diagnosis method and device under unbalanced small sample |
| CN117171681B (en) * | 2023-11-03 | 2024-01-30 | 贵州大学 | Unmanned plane control surface intelligent fault diagnosis method and device under unbalanced small sample |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115320886A (en) | Real-time monitoring method and system for aircraft control surface fault | |
| CN107608335B (en) | Data driving method for fault detection and fault separation of unmanned aerial vehicle flight control system | |
| US6408259B1 (en) | Alert generation for trend performance analysis | |
| Fravolini et al. | Experimental interval models for the robust fault detection of aircraft air data sensors | |
| US11472568B2 (en) | Prognostic monitoring of complementary air data system sensors | |
| US8090485B2 (en) | Low-frequency flight control system oscillatory faults prevention via horizontal and vertical tail load monitors | |
| US7271741B2 (en) | Method and device for detecting an overstepping of design loads of the fin of an aircraft | |
| CN112884051B (en) | Data-driven multi-component online complex fault diagnosis method for lightweight unmanned aerial vehicle | |
| CN112947392B (en) | Flight control system actuator and sensor composite tiny fault estimation method based on robust observer | |
| CN111474919A (en) | Aeroengine control system sensor fault diagnosis method based on AANN network group | |
| CN107991552A (en) | A kind of Reusable Launch Vehicles life appraisal and forecasting system and method | |
| CN111506049A (en) | Multiple fault diagnosis method for aero-engine control system based on AANN network system | |
| CN102200776A (en) | Fault diagnosis method for actuator of flight control system | |
| CN111580498A (en) | Aircraft environmental control system air cooling equipment robust fault diagnosis method based on random forest | |
| Lu et al. | Fault detection, diagnosis, and performance assessment scheme for multiple redundancy aileron actuator | |
| Fravolini et al. | Model-based approaches for the airspeed estimation and fault monitoring of an Unmanned Aerial Vehicle | |
| CN116127842A (en) | Post-fault flight envelope online prediction method based on radial basis-counter propagation neural network | |
| Schuchard et al. | Detection and classification of aircraft icing using neural networks | |
| US7164366B2 (en) | Process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of said aircraft | |
| CN115981265B (en) | Ship-borne aircraft fault online detection method based on extended observer | |
| Garcia et al. | Nonlinear observer-based OFC detection for A380 aircraft | |
| Romanova | Applying intelligent data analysis technologies for detecting damages to UAVs | |
| Mack et al. | An adaptive detection scheme for aircraft aerodynamic system damage | |
| CN118210292A (en) | SR20 type airplane fault detection method and system based on visualization technology | |
| CN117390443A (en) | Unmanned aerial vehicle running state anomaly detection method based on time sequence prediction |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |