CN108945517A - Aircraft slat tilt detection device and its localization method - Google Patents
Aircraft slat tilt detection device and its localization method Download PDFInfo
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- CN108945517A CN108945517A CN201810841689.9A CN201810841689A CN108945517A CN 108945517 A CN108945517 A CN 108945517A CN 201810841689 A CN201810841689 A CN 201810841689A CN 108945517 A CN108945517 A CN 108945517A
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- slat
- tooth head
- small tooth
- rack
- circle
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- 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
Abstract
The present invention provides a kind of aircraft slat tilt detection device, comprising: slat inclined sensor device, including angular displacement sensor and the small tooth head being associated；Feedback rack, for installing to the inside groove of slat rail and being engaged with small tooth head.It additionally provides to above-mentioned detection device localization method, comprising the following steps: determine the pressure angle of feedback rack Yu small tooth head；Determine the small tooth head number of teeth；Determine transmission ratio；According to the number of teeth of determining gear ratio calculation feedback rack；Modulus is selected, and calculates the center radius of circle of feedback rack and small tooth head；Small tooth head is arranged in center circle, and is balanced with the distance of other component on partition to prevent interference or gap too small, and adjustment modulus modulus obtains the position of the small tooth head of sensor；By adjusting modulus and then center radius of circle is adjusted, the length that can guarantee rack gear is enabled to detect the angle of slat total travel.The present invention can arrange the detection device for capableing of accurately detecting slat tilt angle in the aircraft leading edge of space anxiety.
Description
Technical field
The present invention relates to the high-lift systems of aircraft, and more particularly to a kind of aircraft slat based on gear-rack drive incline
Oblique detection device and its localization method.
Background technique
Wing flap control system and slat control system have collectively constituted the promotion Force control system of civil aircraft.Slat is come
It says, slat actuator is mounted on the structural bulk in aircraft wing leading edge cabin, and slat actuator output shaft passes through spline and seam
The engagement of wing driving pinion, slat driving pinion are engaged with slat drive rack, and slat drive rack is mounted on slat rail
The end of inside groove, sliding rail connects slat rudder face.The sliding rail of slat circumferentially moves, whole since the radius of each sliding rail is different
A slat is in conical motion.
The research and development of the high-lift system of modern civil aircraft need to follow ARP4754A " R&D process of aircraft and system " text
It is required specified in part, and is the safety analysis for instructing carry out system with ARP4761 " security evaluation process guidance and method ".
Slat is tilted beyond a kind of failure limited as slat system, may cause the destruction or aircraft handling performance of slat rudder face
Be greatly reduced, thus be defined as disaster grade (catastrophic) failure state, it is necessary to enough design means be taken to make
Its probability occurred is lower than 1E-9, therefore becomes the essential of slat Control System Design for the lasting monitoring of the failure
A part.
General aircraft uses RVDT (Rotary Variable Differential Transformer) Rotary Variable
Differential transformer detects the inclination of each slat driving erect-position.Sensor is driven by mechanical rocker-arm link mechanism, and slat is normally received
When putting, connecting rod exports different voltage values and carrys out joint measurement wing erect-position with motion of rudder, corresponding different movement angle, sensor
Angle, the flap slat control computer judge by comparing the RVDT output valve of multiple erect-positions slat whether run-off the straight.But
Above scheme is there are sizable difficulty, a large amount of system of arrangement and pipeline, cable, arrangement space ten in aircraft wing leading edge cabin
Divide anxiety, rocker-arm link mechanism is often arranged without enough spaces, the wing ultra-thin for modern supercritical wing, this is asked
Topic is more prominent, and rocker-arm link mechanism can not be arranged in leading edge cabin.
Therefore, this field needs a kind of slat tilt detection device and the dress that can be installed in narrow space
The localization method with high duplication set.
Summary of the invention
The invention proposes a kind of novel civil aircraft slat tilt detection design based on gear-rack drive, the hairs
Slat sensor rack gear is arranged on sliding rail, utilizes sensor by the principle that the bright sliding rail for making full use of slat circumferentially moves
The rotation of the small tooth head of the movement driving slat sensor of rack gear, and then measure the angle of slat erect-position.
The method is suitable for the very nervous aircraft slat being particularly suitable for using supercritical wing of leading edge arrangement space and inclines
The design tiltedly detected has the characteristics that with strong points, repeatable high, at low cost, light-weight.
Specifically, the present invention provides a kind of aircraft slat tilt detection devices, comprising:
Slat inclined sensor device, the slat inclined sensor device include angular displacement sensor and have with it is described
The associated small tooth head of angular displacement sensor；
Feedback rack, the feedback rack is for installing to the inside groove of slat rail and engaging with the small tooth head.
In a preferred embodiment, the angular displacement sensor is Rotary Variable Differential transformer.
In a preferred embodiment, the feedback rack with a thickness of 2-4mm.It prevents from disengaging
In a preferred embodiment, the width of the feedback rack is 10-15mm.
It also provides a kind of to above-mentioned aircraft slat tilt detection device progress localization method, comprising the following steps:
Determine the pressure angle of the feedback rack Yu the small tooth head；
Determine the number of teeth of the small tooth head；
Determine the transmission ratio i of pinion gear, feedback rack；
Z2, i=Z2/Z1 are calculated according to the i determined, wherein Z2 is the number of teeth of the feedback rack, and Z1 is the small tooth
The number of teeth of head；
Modulus m is selected, and calculates the center radius of circle R=m (Z2-Z1) of the feedback rack and the small tooth head；
The small tooth head of the sensor is arranged in center circle, so that the small tooth head is located on the center radius of circle, and
The reference circle of the feedback rack is located on the center radius of circle, and balances the distance with other component on partition to prevent from doing
It relates to or gap is too small, adjustment modulus m obtains the position of the small tooth head of the sensor；
By adjusting determining modulus and then determining center radius of circle is adjusted, suitable cloth is selected on the radius of circle of center
Set the angle for a little enabling the length that can guarantee rack gear to detect slat total travel.
In a preferred embodiment, determine that the pressure angle is 20 °.
In a preferred embodiment, the number of teeth of the small tooth head of sensor is selected to be greater than 12.
In a preferred embodiment, the number of teeth of the small tooth head of sensor is less than 20.
In a preferred embodiment, determine that transmission ratio i includes determining described anti-according to the radius of gyration of the slat rail
The radius of gyration for presenting rack gear, in conjunction with the radius of the small tooth head of sensor, determine the radius of gyration of feedback rack described in transmission ratio i=/
The radius of the small tooth head.
In a preferred embodiment, determine that transmission ratio i includes the transmission ratio being determined as transmission ratio i equal to slat.
The additional features and advantage of aircraft slat tilt detection device and its localization method described herein will below
Detailed description in state, and by below with those skilled in the art obviously or from described herein by practicing
Embodiment and be recognized by those skilled in the art, these description include detailed description below, claim and attached drawing.
It should be appreciated that general description and detailed description below above illustrate various embodiments and be intended to provide understanding
The general introduction of the property and feature of claimed theme or frame.Various embodiments are further understood with providing including attached drawing
And attached drawing merges in this manual and constitutes the part of this specification.Attached drawing shows various implementations described herein
Example, and it is used to explain the principle and operation of claimed theme together with the description.
Detailed description of the invention
With reference to object above, technical characteristic of the invention is explicitly described in the following claims, and its advantage
It is clear that attached drawing has been illustrated by way of example the preferred embodiment of the present invention from detailed description referring to the drawings, and
It does not limit the scope of the inventive concept.
Fig. 1 shows the aircraft slat tilt detection device being mounted in aircraft wing leading edge according to the present invention.
Fig. 2 shows the schematic diagrames of the feedback rack of aircraft slat tilt detection device according to the present invention.
Fig. 3 shows the schematic diagram of the slat inclined sensor device of aircraft slat tilt detection device according to the present invention
Reference signs list
1 slat inclined sensor device
11 small tooth heads
12 transducer body portions
2 feedback racks
3 slat rails
4 structural bulks
5 longitudinal rollers
6 lateral rollers
Specific embodiment
It will be described in detail each embodiment of the invention now, the example of these embodiments is shown in the accompanying drawings
And it is described as follows.Although the present invention will be combined with an exemplary implementation and be described, it will be appreciated that this specification
It is not intended to limit the invention to those exemplary implementation schemes.On the contrary, the present invention is directed to not only cover these exemplary realities
Apply scheme, and covering can be included in it is within the spirit and scope of the present invention being defined by the appended claims various
Selection form, modification, equivalents and other embodiments.For the ease of explaining and accurately determining in the following claims
Justice, term " on ", "lower", "inner", "outside", " left side " and " right side " are used for the feature with reference to exemplary implementation scheme shown in the figure
Position these features are described.Exemplary implementation scheme of the invention is retouched in detail below with reference to the accompanying drawings
It states.
Present invention mainly solves civil aircraft supercritical wing slat tilt detection problems, are needing to carry out slat inclination
Each erect-position of detection makes full use of the space of slat rail 3 to install feedback rack, drives feedback tooth using the movement of sliding rail 3
Item 2 moves, and then drives the movement angle of the detection slat rudder face of inclined sensor device 1 with small 11 input terminal of tooth head, when
When the movement angle that the inclination sensor of two erect-positions is measured is more than preset threshold, system is alarmed and locks slat system.
The aircraft slat tilt detection device of the present invention being mounted in aircraft wing leading edge is shown in Fig. 1 comprising anti-
Present rack gear 2 and the inclined sensor device 1 with small 11 input terminal of tooth head.As shown, the setting of feedback rack 2 is sliding in slat
In the inside groove of 3 lower section of rail, and it is close to the upper surface installation of 3 inside groove of slat rail, so as to take full advantage of in slat rail 3
Slot space is arranged, and will not influence the aerodynamic configuration of wing.It is anti-to also be driven simultaneously when the drive slat inclination of slat rail 3
Rack gear 2 is presented to tilt.
Fig. 2 shows the schematic diagram of feedback rack 2, feedback rack 2 is for example, by passing through the bolt being arranged on feedback rack 2
The bolt in hole and be fixedly attached to slat rail 3.It should be understood that feedback rack 2 can also be fixedly attached to seam by other means
Wing slip rail 3.
Fig. 3 shows the schematic diagram of slat inclined sensor device 1.The slat inclined sensor device 1 is mounted on wing
On structural bulk 4 in leading edge cabin, and including transducer body portion 12 and small tooth head 11.It is accommodated in transducer body portion 12
There is angular displacement sensor (not shown).The angular displacement sensor is associated with small tooth head 11, so as to sense turning for small tooth head 11
Dynamic angle.The small tooth head 11 is engaged with feedback rack 2 again, so that the rotation of feedback rack 2 drives small tooth head 11 to rotate.As a result,
The angular displacement sensor of slat inclined sensor device 1 can detect inclining for slat rail 3 via feedback rack 2 and small tooth head 11
Thus rake angle detects the tilt angle of slat.
Preferably, above-mentioned angular displacement sensor is Rotary Variable Differential sensor RVDT.
The thickness of feedback rack 2 is preferably provided as 2~4mm, is thus making full use of the same of slot space in slat rail 3
When also can guarantee the engaging width of feedback rack 2 Yu small tooth head 11, prevent from causing to occur since thickness is too small effectively to engage
Failure.
The width of feedback rack 2 is preferably provided as 10~15mm, and the mounting hole of rack gear may be sized to national standard
4.8mm had not only guaranteed the robust that feedback rack 2 is installed, but also can effectively avoid the interference with pulley transverse direction roller 6, pivot pin.
Since aircraft leading edge inner part is numerous, and arrangement space is very nervous, it is therefore desirable to tilt to above-mentioned aircraft slat
Detection device is carefully positioned, to realize the purpose of detection slat tilt angle.Specifically, localization method includes following
Step:
Determine the pressure angle of feedback rack 2 Yu small tooth head 11,；
Determine the number of teeth of small tooth head；
Determine the transmission ratio i of pinion gear 11 Yu feedback rack 2；
Z2, i=Z2/Z1 are calculated according to the i determined, wherein Z2 is the number of teeth of the feedback rack, and Z1 is described small
The number of teeth of tooth head；
Pinion gear 11 and 2 modulus m of feedback rack are selected, and calculates the center radius of circle R=of feedback rack 2 and small tooth head 11
m(Z2-Z1)；
The small tooth head 11 of placement sensor in the center circle, so that the center circle of small tooth head 11 is located at the center radius of circle
On, and the reference circle of feedback rack 2 is located on the center radius of circle, and balance simultaneously and structural bulk 4 on other component away from
From to prevent interference or gap too small, when generating interference or gap is too small, modulus m is adjusted, so as to adjust center radius of circle R
To carry out radial adjustment to small tooth head 11 and feedback rack 2, to obtain the suitably-arranged position of the small tooth head of sensor；
By adjusting determining modulus and then adjust determining center radius of circle R, and select on the radius of circle of center not with
The suitably-arranged point that peripheral parts are interfered or gap is too small, enables the length that can guarantee rack gear 2 to detect slat total travel
Angle.
Specifically, above-mentioned pressure angle can be determined as 20 °, in order to process.
In addition, the number of teeth of small tooth head has to be larger than minimum number of teeth in order to avoid root is cut, that is, it is greater than 12.For the ease of processing,
The usual number of teeth is determined as 13 or 14, generally no greater than 20.It should be understood that the number of teeth is also greater than 20 without departing from of the invention
Range.
Wherein transmission ratio i may be determined as follows, and according to the radius of gyration of slat rail 3, determine the rotation half of feedback rack 2
Diameter determines the radius of gyration/small tooth head radius of transmission ratio i=feedback rack in conjunction with the radius of the small tooth head 11 of sensor.This
Outside, transmission ratio i is also intended to the transmission ratio equal to slat.
Advantages of the present invention is as follows:
1, feedback rack is mounted on slat driving sliding rail, is taken full advantage of space in sliding-rail groove and is arranged, Bu Huiying
Ring the aerodynamic configuration of wing.
A) feedback rack with a thickness of 2~4mm, make full use of and also can guarantee that the engagement of tooth is wide while sliding rail slot space
Degree prevents the failure for causing to occur effectively engaging since thickness is too small.
B) width of feedback rack is 10~15mm, and the installation pore size of rack gear takes national standard 4.8mm, has both guaranteed that rack gear is installed
Robust, and can effectively avoid the interference with pulley horizontal lateral roller, pivot pin.
2, slat inclination sensor is mounted on the structural bulk in leading edge of a wing cabin, also needs installation to stitch on corresponding partition
Horizontal lateral roller of wing actuator, bleed air line, EWIS cable, structure sliding rail etc..
A) slat inclination sensor takes the lead small tooth head input terminal, can be according to the reality of the structural bulk installation space of each erect-position
Modulus/radius of border situation, variable adjustment feedback rack and sensor gear determines optimal installation site；
B) layout points at slat inclination sensor tooth head center are in center circle, layout points can along center circular motion,
Guarantee effectively to complete mounting arrangements using the space of structural bulk and measures the movement of slat rudder face total travel.
Although combining preferred embodiment above structure and working principle of the invention is illustrated, this technology
Those of ordinary skill in field is it should be appreciated that above-mentioned example is intended merely to explanation, and cannot function as to limit of the invention
System.Therefore, it can modify in the spirit of claims to the present invention and modification, these modifications and variations
Within the scope of all falling in required by claims of the present invention.
Claims (10)
1. a kind of aircraft slat tilt detection device, comprising:
Slat inclined sensor device, the slat inclined sensor device include angular displacement sensor and have and the angle position
The associated small tooth head of displacement sensor；
Feedback rack, the feedback rack is for installing to the inside groove of slat rail and engaging with the small tooth head.
2. aircraft slat tilt detection device according to claim 1, which is characterized in that
The angular displacement sensor is Rotary Variable Differential transformer.
3. aircraft slat tilt detection device according to claim 1, which is characterized in that
The feedback rack with a thickness of 2-4mm, prevent from disengaging.
4. aircraft slat tilt detection device according to claim 1, which is characterized in that
The width of the feedback rack is 10-15mm.
5. a kind of carry out localization method, including following step to aircraft slat tilt detection device described according to claim 1-4
It is rapid:
Determine the pressure angle of the feedback rack Yu the small tooth head；
Determine the number of teeth of the small tooth head；
Determine the transmission ratio i of pinion gear, feedback rack；
The tooth number Z 2 of feedback rack is calculated according to the transmission i determined, wherein i=Z2/Z1, Z2 is the tooth of the feedback rack
Number, Z1 are the number of teeth of the small tooth head；
Modulus m is selected, and calculates the center radius of circle R=m (Z2-Z1) of the feedback rack and the small tooth head；
The small tooth head of the sensor is arranged in center circle, so that the center circle of the small tooth head is located at the center radius of circle
On, and the reference circle of feedback rack is located on the center radius of circle, and balances the distance with other component on partition to prevent
Interference or gap are too small, and adjustment modulus m obtains the position of the small tooth head of the sensor；
By adjusting determining modulus and then determining center radius of circle is adjusted, suitable arrangement is selected on the radius of circle of center
Point enables the length that can guarantee rack gear to detect the angle of slat total travel.
6. localization method according to claim 5, which is characterized in that
Determine that the pressure angle is 20 °.
7. localization method according to claim 5, which is characterized in that
The number of teeth of the small tooth head of sensor is selected to be greater than 12.
8. localization method according to claim 7, which is characterized in that
The number of teeth of the small tooth head of sensor is less than 20.
9. localization method according to claim 5, which is characterized in that
Determine that transmission ratio i includes determining the radius of gyration of the feedback rack according to the radius of gyration of the slat rail, in conjunction with
The radius of the small tooth head of sensor determines the radius of gyration/small tooth head radius of feedback rack described in transmission ratio i=.
10. localization method according to claim 5, which is characterized in that
Determine that transmission ratio i includes the transmission ratio being determined as transmission ratio i equal to slat.
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| CN201810841689.9A CN108945517A (en) | 2018-07-27 | 2018-07-27 | Aircraft slat tilt detection device and its localization method |
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| CN201810841689.9A CN108945517A (en) | 2018-07-27 | 2018-07-27 | Aircraft slat tilt detection device and its localization method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108945516A (en) * | 2018-07-27 | 2018-12-07 | 中国商用飞机有限责任公司 | Aircraft slat tilt detection device and its localization method |
| CN111977023A (en) * | 2020-07-06 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Test system of slat inclination detection mechanism |
| GB2585652A (en) * | 2019-07-09 | 2021-01-20 | Moog Wolverhampton Ltd | Skew and loss detection system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101988570A (en) * | 2009-07-31 | 2011-03-23 | 中国商用飞机有限责任公司 | Design method of gears and racks for airplane slat actuators |
| CN102806992A (en) * | 2011-06-01 | 2012-12-05 | 哈米尔顿森德斯特兰德公司 | Resolver type skew sensor with gimbal attachment |
| CN104048874A (en) * | 2014-06-24 | 2014-09-17 | 西北工业大学 | Load follow-up loading system for plane flap reliability test |
| US9102398B2 (en) * | 2011-11-23 | 2015-08-11 | Airbus Operations Limited | Deployment system |
| US20160297541A1 (en) * | 2015-04-09 | 2016-10-13 | The Boeing Company | Aircraft wing slat skew detection systems and methods |
| 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 |
| CN108945516A (en) * | 2018-07-27 | 2018-12-07 | 中国商用飞机有限责任公司 | Aircraft slat tilt detection device and its localization method |
-
2018
- 2018-07-27 CN CN201810841689.9A patent/CN108945517A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101988570A (en) * | 2009-07-31 | 2011-03-23 | 中国商用飞机有限责任公司 | Design method of gears and racks for airplane slat actuators |
| CN102806992A (en) * | 2011-06-01 | 2012-12-05 | 哈米尔顿森德斯特兰德公司 | Resolver type skew sensor with gimbal attachment |
| US9102398B2 (en) * | 2011-11-23 | 2015-08-11 | Airbus Operations Limited | Deployment system |
| CN104048874A (en) * | 2014-06-24 | 2014-09-17 | 西北工业大学 | Load follow-up loading system for plane flap reliability test |
| US20160297541A1 (en) * | 2015-04-09 | 2016-10-13 | The Boeing Company | Aircraft wing slat skew detection systems and methods |
| 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 |
| CN108945516A (en) * | 2018-07-27 | 2018-12-07 | 中国商用飞机有限责任公司 | Aircraft slat tilt detection device and its localization method |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108945516A (en) * | 2018-07-27 | 2018-12-07 | 中国商用飞机有限责任公司 | Aircraft slat tilt detection device and its localization method |
| GB2585652A (en) * | 2019-07-09 | 2021-01-20 | Moog Wolverhampton Ltd | Skew and loss detection system |
| GB2585652B (en) * | 2019-07-09 | 2021-07-14 | Moog Wolverhampton Ltd | Skew and loss detection system |
| CN111977023A (en) * | 2020-07-06 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Test system of slat inclination detection mechanism |
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