CN113932770A - Flap inclination monitoring method based on stay-supported sensor - Google Patents
Flap inclination monitoring method based on stay-supported sensor Download PDFInfo
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- CN113932770A CN113932770A CN202111359509.1A CN202111359509A CN113932770A CN 113932770 A CN113932770 A CN 113932770A CN 202111359509 A CN202111359509 A CN 202111359509A CN 113932770 A CN113932770 A CN 113932770A
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 24
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- 238000001514 detection method Methods 0.000 abstract description 31
- 230000007246 mechanism Effects 0.000 description 11
- 239000012530 fluid Substances 0.000 description 9
- 238000009434 installation Methods 0.000 description 8
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- 238000006073 displacement reaction Methods 0.000 description 5
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
- G01C9/005—Measuring inclination, e.g. by clinometers, by levels specially adapted for use in aircraft
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/02—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring length, width, or thickness
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/32—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring the deformation in a solid
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/0002—Arrangements for supporting, fixing or guiding the measuring instrument or the object to be measured
- G01B5/0004—Supports
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention belongs to the field of airplane fault detection, and particularly relates to a flap inclination monitoring method. The monitoring method comprises the following steps: mounting a plurality of sensor cable support devices on two adjacent flaps and on adjacent sides of the two flaps; the sensor steel cable sequentially penetrates through the plurality of sensor steel cable supporting devices, one end of the sensor steel cable is connected with the fixed end of the sensor, and the other end of the sensor steel cable is connected with the sensor body; the sensor body is in signal connection with a flap controller (13).
Description
Technical Field
The invention belongs to the field of airplane fault detection, and particularly relates to a flap inclination monitoring method.
Background
Currently, there are two main types of flap tilt detection methods adopted by mainstream aircraft manufacturers in the world, namely, an RVDT (angular displacement sensor) detection method and an LVDT (linear displacement sensor) detection method.
The RVDT detection method has the characteristics of high precision, capability of realizing 360-degree rotation measurement, long service life and the like, and has a wide application range. RVDT detection, i.e. the sensor is mounted near the two actuators of each flap wing surface, and by comparing two RVDT measurements on the same wing surface it is determined whether the flap is tilted. A tilt fault is determined for the flap when the difference between the two RVDT measurements exceeds a maximum flap tilt threshold. At the moment, the pilot can effectively control the control surface to land nearby to remove faults, and the requirement of safety is met. The architecture of a high lift system using RVDT detection is shown in fig. 1. The method needs more sensors, so that the flap inclination monitoring method has higher failure probability and lower reliability.
LVDT is a linear displacement transducer. The working principle is simply that the iron core movable transformer is composed of a primary coil, two secondary coils, an iron core, a coil framework, a shell and the like. The LVDT detection method judges whether the flap is inclined or not by comparing the measured values of the two LVDTs at the left side and the right side of the wing. A tilt fault is determined for the flap when the difference between the two LVDT measurements exceeds a maximum flap tilt threshold. The high lift system architecture using LVDT sensing is shown in fig. 2. The method has the problem that the airfoil tilting fault caused by the disconnection of a part of the actuator cannot be effectively monitored.
In the prior art, CN107985553A proposes a flap tilt detection system and method configured to detect flap tilt of one or more flaps movably fixed to one or more wings of an aircraft. The flap tilt detection system includes a flap support assembly that couples the flap to the wing. The flap support assembly includes: a fixed portion configured to be fixed to a wing; a movable portion movably coupled to the fixed portion and configured to securely support the wing; and a connecting device movably coupled to the fixed portion and the movable portion. The connecting device includes: a cylinder defining an inner chamber comprising a hydraulic fluid chamber; a piston having a piston head within an inner chamber; and a liquid fluid held within the hydraulic fluid chamber. The pressure detector is fluidly coupled to the hydraulic fluid chamber. The pressure sensor is configured to detect a fluid pressure of the hydraulic fluid within the hydraulic fluid chamber. The presence of flap lean is determined using the fluid pressure detected by the pressure detector. However, this method involves hydraulic fluid, which adds weight to the detection system.
CN106043672A proposes a static flight control surface inclination detection system for an aircraft and which comprises a flight control surface of an aircraft wing, two drive mechanisms for operating the flight control surface, a first load sensor and a second load sensor for each of the two drive mechanisms, and a control module. Each of the two drive mechanisms is located on opposite sides of the flight control surface and each of the two drive mechanisms includes at least a first link comprising a first outer surface and a second link comprising a second outer surface. A first load sensor is disposed along a first outer surface of the first link and a second load sensor is disposed along a second outer surface of the second link. The control module is in signal communication with the first load sensor and the second load sensor of each drive mechanism. However, this patent is directed to a tilt detection system for a stationary flight control surface and the system is relatively complex.
US9656764B2 proposes a tilt detection system for an aircraft high lift system, in which a sensor with onboard data processing capability feeds back the relative tilt of each pair of sensor supports to determine whether the high lift system flaps are tilted. However, this solution requires two sensors per airfoil, the number of sensors being high (8).
US20150197347a1 proposes a monitoring method for an aircraft high lift system, which monitors a first current consumption of a first operating point and a second current consumption of a second operating point, compares whether a difference between the first current consumption and the second current consumption exceeds a threshold value, and determines that a tilt fault occurs when the difference exceeds the threshold value. However, this method requires two sensors per airfoil, with a large number (8).
US6382566B1 proposes a method and a device for detecting the tilt of flaps, which method stops the flap movement before an unacceptable aerodynamic or structural situation of the flap drive system occurs by measuring the position of the inner and outer sides of each flap. In an embodiment, the difference in the number of revolutions of the ball screw actuator is taken as a measure of the flap tilt.
CN110092005A provides a tilt fault detection mechanism suitable for large-stroke flap motion, this mechanism installs the lead screw in flap slide rail frame downside, it has the flap support to articulate on the lead screw nut, this flap support drives the flap and follows flap slide rail frame motion after being connected with the flap, this flap support constitutes hinge four-bar linkage with lead screw, connecting rod one and connecting rod two, angle displacement sensor fixes on the lead screw nut, thereby its sense terminal is connected with connecting rod two and is rotated in step. The mechanism improves the stroke of the flap tilt detection and also reduces the weight of the flap tilt fault detection mechanism. However, the mechanism is only suitable for large-stroke flap motion and cannot be applied to tilt monitoring of small-stroke flap motion, and meanwhile, the detection mechanism is arranged at each flap action point, so that the weight of the flap tilt detection device is increased.
CN103969035A proposes a flap distortion test system, which adopts LVDT/RVDT-based tilt detection devices symmetrically installed on flaps, for a pair of tilt detection devices on each flap, the excitation end is connected with a flap control computer, the feedback end is directly connected, during detection, the flap control computer simultaneously sends excitation signals to the symmetric tilt detection devices, the feedback voltage of the symmetric tilt detection devices is subjected to consistency difference calculation, if the difference is greater than a threshold value, the flap distortion test system is judged to be a tilt fault, otherwise, the flap distortion test system is normal and performs cyclic detection. Although the method reduces the complexity of electronic hardware, saves the system development cost, reduces the weight of the system cross-linked cable and improves the reliability of inclination detection, the number of the sensors is more (4), and the logic judgment of a computer is relatively complex.
Disclosure of Invention
The purpose of the invention is as follows: the flap inclination monitoring method is provided, the number of sensors is reduced compared with the RVDT detection method, and the reliability of flap inclination monitoring is improved; compared with different sensor layout modes of an LVDT detection method, the method has the advantages that the flap tilt fault caused by the disconnection of all the actuators can be monitored, the fault positioning capability is improved, and the requirement on installation space is reduced.
The technical scheme is as follows: providing a flap tilt monitoring method, wherein the monitoring method comprises the following steps:
the method comprises the following steps that a stay wire type sensor is adopted, and the stay wire type sensor comprises a plurality of sensor steel cable supporting devices, a sensor steel cable, a fixed end and a sensor body;
mounting a plurality of sensor cable support devices on two adjacent flaps and on adjacent sides of the two flaps; the sensor steel cable sequentially penetrates through the plurality of sensor steel cable supporting devices, one end of the sensor steel cable is connected with the fixed end of the sensor, and the other end of the sensor steel cable is connected with the sensor body; the sensor body is in signal connection with the slat controller;
when the flap actuator is disconnected or a transmission shaft between the actuators is disconnected to cause the flap to incline, the length of the sensor steel cable is lengthened, the sensor body monitors the deformation of the sensor steel cable and feeds the deformation back to the slat controller 13, and the slat controller 13 judges the flap inclining fault according to the deformation.
Optionally, the sensor cables are threaded through the plurality of sensor cable support devices in sequence without crossing between the sensor cables.
Alternatively, the sensor cables are sequentially passed through the plurality of sensor cable supporting devices, and the sensor cables are arranged to cross but not to contact each other.
Optionally, when a plurality of flaps are arranged on the left side and the right side of the airplane, the stay wire type sensor is arranged between each two adjacent flaps.
Optionally, a threshold is set on the flap controller 13, and when the deformation of the sensor cable exceeds the threshold, a flap tilt fault corresponding to the sensor body that feeds back the deformation of the sensor cable is determined.
Alternatively, the slat controller 13 receives the deformation amount of the sensor cable fed back by the plurality of sensor bodies,
and when the difference value of the deformation of the steel cable of the sensor fed back by the sensor bodies at the symmetrical positions on the left side and the right side of the airplane is larger than a set value, judging the tilt fault of the flap.
Alternatively, the pull-wire sensor employs single redundancy or redundancy.
Optionally, the sensor body is mounted inside the flap for protecting the sensor.
The technical effects are as follows: compared with the RVDT detection method, the number of sensors is reduced by half; the cost of the stay wire type sensor is lower than that of the LVDT; only the steel cable in the stay wire type sensor is positioned between the inner flap and the outer flap, so that the requirement on the installation space between the inner flap and the outer flap is lower compared with the LVDT. The sensor body of the stay wire sensor is mounted inside the flap, and therefore has lower environmental requirements than an LVDT.
According to the invention, the inclination of the flap is judged through the stay wire sensor, and whether the flap of the left wing is inclined or the flap of the right wing is inclined can be judged according to the triggering of the stay wire sensor body, so that the fault positioning capability is improved relative to the LVDT.
Drawings
FIG. 1 is a layout diagram of a conventional RVDT detection method;
FIG. 2 is a layout of a conventional LVDT probing method;
FIG. 3 is a schematic layout of a stay-based flap tilt monitoring scheme according to the present invention;
FIG. 4 is a schematic illustration of a left outboard actuator shown in an off tilt configuration in accordance with the present invention;
FIG. 5 is a schematic layout of a stay-based flap tilt monitoring arrangement according to the present invention;
in the figure, 1-left inner flap, 2-right inner flap, 3-left outer flap, 4-right inner flap, 5-left sensor body, 6-right sensor body, 7-left sensor fixed end, 8-right sensor fixed end, 9-left sensor cable, 10-right sensor cable, 11-left sensor cable support, 12-right sensor cable support, 13-flap controller slat
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In this embodiment, referring to fig. 3, a flap tilt monitoring method based on a stay-supported sensor is provided, which includes 1 flap controller and 2 stay-supported sensors.
During installation, the specific arrangement method comprises the following steps: for a left side stay-supported sensor, a left side sensor steel cable supporting device 11 is firstly installed at the outer side of a left side inner flap 1 and the inner side of a left side outer flap 3, then a left side sensor steel cable 9 is connected with a sensor fixed end 7 and then fixed on the left side inner flap 1, then the left side sensor steel cable 9 sequentially penetrates through the steel cable supporting device 11, finally the left side sensor steel cable 9 is connected with a left side sensor body 5 and then installed on the left side inner flap 1, the length of the left side sensor steel cable 9 is adjusted after installation is finished, and then a cable of the sensor is connected to a slat controller 13.
For a right side stay-supported sensor, a right side sensor steel cable supporting device 12 is firstly installed on the outer side of a right side inner flap 2 and the inner side of a right side outer flap 4, a right side sensor steel cable 10 is connected with a sensor fixing end 8 and then fixed on the right side inner flap 2, then the right side sensor steel cable 10 sequentially penetrates through the steel cable supporting device 12, finally the right side sensor steel cable 10 is connected with a right side sensor body 6 and then installed on the right side inner flap 2, the length of the right side sensor steel cable 10 is adjusted after installation, and then a cable of the sensor is connected to a slat controller 13.
In the embodiment, a stay-supported sensor is arranged between the inner flap and the outer flap, the stay-supported sensor consists of a stay-supported sensor body, a sensor fixed end, a sensor steel cable and a steel cable supporting device, the stay-supported sensor body and the sensor fixed end are both arranged on the inner flap, and the steel cable penetrates through the inner flap and the outer flap through the four steel cable supporting devices. The sensor body and the fixed end of the stay wire type sensor can be arranged on the inner flap and also can be arranged on the outer flap, but the stay wire type sensor is more beneficial to being arranged on the inner flap, so that the center of gravity is closer to the fuselage; the sensor body can be arranged in front of the fixed end and opposite to the handpiece direction, or the sensor body can be arranged behind the fixed end and selected according to the distance between the sensor and the FSECU, and the closer the sensor is to the FSECU, the shorter the length of the communication cable is.
In this embodiment, the sensors of the stay-type sensors are proximity sensors, and the proximity sensors are triggered when the tilt amounts of the inner and outer flaps exceed a set threshold value, so that the target is set to be "target away" as shown in fig. 4, the FSECU13 is triggered, the slat controller monitor is triggered, and finally the wing surface is held at the fault position by the WTB wing tip brake. The FSECU can judge whether the left side flap or the right side flap has the inclination fault according to the triggering of the left and right side stay wire type sensors. Further, the pull sensor may be a linear displacement sensor.
In the embodiment, the length of the steel cable is pre-tightened and adjusted after installation, the sensor is electrically zeroed, and installation errors caused in the installation process of the stay wire type sensor can be eliminated well. The threshold value of the flap tilt fault is set to be larger than the deformation of the steel cable caused by aerodynamic interference, flap shake and the like, and the influence of aerodynamic resistance can be overcome due to the installation position of the steel cable and the strength of the steel cable.
The wire rope layout of the stay wire sensors can be in parallel arrangement, as shown in fig. 3; a crossed arrangement is also possible, as shown in fig. 5.
The scheme is suitable for the airplane with at least 2 wing flaps on the single-side wing, and the arrangement of the stay wire type sensors is the same for the airplane with a plurality of wing flaps. Furthermore, the solution is not only applicable to aircraft with flaps only, but also to aircraft with flap slats.
In the embodiment, the flap tilt fault can be judged by the fact that the feedback value of the single-side stay wire type sensor exceeds the threshold value, or by the fact that the feedback value difference of the two-side stay wire type sensors exceeds the threshold value, but the flap tilt fault can be more conveniently determined on which side of the flap tilt fault occurs.
Claims (8)
1. A flap tilt monitoring method, characterized in that the monitoring method is:
the method comprises the following steps that a stay wire type sensor is adopted, and the stay wire type sensor comprises a plurality of sensor steel cable supporting devices, a sensor steel cable, a fixed end and a sensor body;
mounting a plurality of sensor cable support devices on two adjacent flaps and on adjacent sides of the two flaps; the sensor steel cable sequentially penetrates through the plurality of sensor steel cable supporting devices, one end of the sensor steel cable is connected with the fixed end of the sensor, and the other end of the sensor steel cable is connected with the sensor body; the sensor body is in signal connection with a flap controller (13);
when the flap actuator is disconnected or a transmission shaft between the actuators is disconnected to cause the flap to incline, the length of the sensor steel cable is lengthened, the sensor body monitors the deformation of the sensor steel cable and feeds the deformation back to the slat controller (13), and the slat controller (13) judges the flap inclining fault according to the deformation.
2. The flap tilt monitoring method of claim 1 wherein the sensor cables are threaded through the plurality of sensor cable support devices in sequence without crossing between the sensor cables.
3. The flap tilt monitoring method of claim 1 wherein the sensor cables are threaded through the plurality of sensor cable support devices in sequence, with the sensor cables being arranged crosswise but without contact.
4. The flap tilt monitoring method according to claim 1, wherein, when a plurality of flaps are present on the left and right sides of the aircraft, a stay-supported sensor is installed between each adjacent two flaps.
5. The flap tilt monitoring method according to claim 1 or 4, characterized in that a threshold value is set on the flap controller (13), and when the deformation of the sensor cable exceeds the threshold value, the flap tilt fault corresponding to the sensor body feeding back the deformation of the sensor cable is determined.
6. The flap tilt monitoring method according to claim 4, characterized in that the flap controller (13) receives the deformation amount of the sensor cable fed back by the plurality of sensor bodies,
and when the difference value of the deformation of the steel cable of the sensor fed back by the sensor bodies at the symmetrical positions on the left side and the right side of the airplane is larger than a set value, judging the tilt fault of the flap.
7. The flap tilt monitoring method of claim 1 wherein the stay-supported sensor employs single or redundant redundancy.
8. The flap tilt monitoring method of claim 1, wherein the sensor body is mounted inside the flap for protecting the sensor.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111359509.1A CN113932770A (en) | 2021-11-18 | 2021-11-18 | Flap inclination monitoring method based on stay-supported sensor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111359509.1A CN113932770A (en) | 2021-11-18 | 2021-11-18 | Flap inclination monitoring method based on stay-supported sensor |
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| CN113932770A true CN113932770A (en) | 2022-01-14 |
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|---|---|---|---|---|
| US5628477A (en) * | 1995-02-13 | 1997-05-13 | The Boeing Company | Auxiliary airfoil lost motion detector and actuator |
| CN101321666A (en) * | 2005-12-06 | 2008-12-10 | 空中客车德国有限公司 | Device for error detection of adjustable flaps |
| US20090223791A1 (en) * | 2008-03-10 | 2009-09-10 | Conner Patrick D | Disconnect sensor |
| US20100100355A1 (en) * | 2008-10-17 | 2010-04-22 | Marx Alan D | In-flight detection of wing flap free wheeling skew |
| US20100277346A1 (en) * | 2009-04-30 | 2010-11-04 | The Boeing Company | Slat Skew Detection System |
| CN102458994A (en) * | 2009-04-16 | 2012-05-16 | 空中客车运营有限公司 | High lift system for an aircraft and method for detecting faults in a high lift system for an aircraft |
| CN103328332A (en) * | 2010-09-08 | 2013-09-25 | 空中客车运作有限责任公司 | Monitoring device for an actuation system of an aircraft, actuation system and method for reconfiguring the actuation system |
| US20140336865A1 (en) * | 2013-05-13 | 2014-11-13 | GE Avivation Systems Limited | Method for diagnosing a trailing edge flap fault |
| CN106275503A (en) * | 2016-08-31 | 2017-01-04 | 中航电测仪器股份有限公司 | A kind of aircraft high-lift system slat tilt detecting device |
| CN113650796A (en) * | 2021-09-10 | 2021-11-16 | 庆安集团有限公司 | Slat inclination monitoring method and device |
-
2021
- 2021-11-18 CN CN202111359509.1A patent/CN113932770A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5628477A (en) * | 1995-02-13 | 1997-05-13 | The Boeing Company | Auxiliary airfoil lost motion detector and actuator |
| CN101321666A (en) * | 2005-12-06 | 2008-12-10 | 空中客车德国有限公司 | Device for error detection of adjustable flaps |
| US20090223791A1 (en) * | 2008-03-10 | 2009-09-10 | Conner Patrick D | Disconnect sensor |
| US20100100355A1 (en) * | 2008-10-17 | 2010-04-22 | Marx Alan D | In-flight detection of wing flap free wheeling skew |
| CN102458994A (en) * | 2009-04-16 | 2012-05-16 | 空中客车运营有限公司 | High lift system for an aircraft and method for detecting faults in a high lift system for an aircraft |
| US20100277346A1 (en) * | 2009-04-30 | 2010-11-04 | The Boeing Company | Slat Skew Detection System |
| CN103328332A (en) * | 2010-09-08 | 2013-09-25 | 空中客车运作有限责任公司 | Monitoring device for an actuation system of an aircraft, actuation system and method for reconfiguring the actuation system |
| US20140336865A1 (en) * | 2013-05-13 | 2014-11-13 | GE Avivation Systems Limited | Method for diagnosing a trailing edge flap fault |
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| CN113650796A (en) * | 2021-09-10 | 2021-11-16 | 庆安集团有限公司 | Slat inclination monitoring method and device |
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