CN102219052A - Skew and/or damage detecting system of control surface element - Google Patents
Skew and/or damage detecting system of control surface element Download PDFInfo
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- CN102219052A CN102219052A CN2010101638115A CN201010163811A CN102219052A CN 102219052 A CN102219052 A CN 102219052A CN 2010101638115 A CN2010101638115 A CN 2010101638115A CN 201010163811 A CN201010163811 A CN 201010163811A CN 102219052 A CN102219052 A CN 102219052A
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Abstract
The invention provides a skew and/or damage detecting system of a control surface element, which is combined with a cable (168 and 178) system; the cable system is connected with a movement sensor (120) by mechanical connecting rods (114, 116); and the mechanical connecting rods can enable a fixed wing structure (102) to be connected with the control surface elements (106,112).
Description
Technical field
The present invention relates to the crooked and/or loss detection system of a kind of control surface element.More particularly, the present invention relates to the crooked and/or loss detection system of a kind of cable type, be used for the leading edge slat (slat) and the wing flap (flap) of aircraft wing.
Background technology
But aircraft wing generally includes a series of drive controlling surface elements.These control surface elements have been determined control surface (being also referred to as auxiliary surface), and this control surface can be with respect to the fixed wing structure motion, so that change the aerodynamic characteristics of wing.Such control surface element comprises for example leading edge slat and lagging dege device wing flap for example of front edge device.
Usually, the control surface element is driven at each spanwise end place by two independent actuators.It is contemplated that when any one actuator et out of order, relevant control surface will produce inconsistent driving and crooked or loss (loss).Importantly, when detecting crooked or lose, the related system shutdown, and inform the aviator of aircraft.
Having proposed several different methods in the prior art provides the crooked of control surface element and/or loss to detect.Proposing cable in this system of described in the US Patent 5680124 is connected with each control surface element.Cable is tightened up in the situation of crooked or loss.Motion detector with proximity sensor is connected with cable, like this, because any cable motion crooked and/or that loss causes can be detected.This detector is installed on the wing flap or leading edge slat of extreme end.It is connected with wing flap/leading edge slat electronic unit (FSEU) in the airframe by electric cable, and this electricity cable stretches into the fuselage by the fixed wing structure and reaches FSEU from movable control surface element.
It is crooked that the adjacently situated surfaces element of this system by being used to spur cable differential detects.First problem of this system is that because cable must be anchored on the control surface element of extreme end, so the crooked of these elements can not be detected at an easy rate by this system.For example, when extreme end surface drive mechanism can not move, not necessarily can cause differential between extreme end surface and next surface.
An also problem of this prior art systems is to connect up between movable control surface element (detector is installed on this movable control surface element) and fixed wing structure.It is inappropriate that circuit between movable structure and fixed sturcture is transformed, because may produce wearing and tearing and tired.And this circuit will be exposed in the infringement of outer member and be subjected to the infringement of outer member.
In addition, front edge control surface element (for example leading edge slat) needs anti-icing feature.These features produce the unfavorable temperature conditions of certain limit, and this may influence the Performance And Reliability of the cable pulling detector that is installed on these control surface elements.
An also problem of prior art systems is that movable control surface element is generally closure panel, thereby makes very difficult proximity transducer so that safeguard.
Summary of the invention
The objective of the invention is to overcome or alleviate one or more the problems referred to above at least.According to the present invention, provide a kind of aircraft control surface element crooked and/or loss detection system, it comprises: aircraft wing structure, this aircraft wing structure comprise fixed part, the first control surface element and the second control surface element, and these elements are arranged to and can be moved with respect to fixed part; Cable, this cable is connected with each of the first and second control surface elements, and like this, in crooked and/or when loss when one of them control surface element, tightening force is applied on the cable; Mechanical linkage, first end of this mechanical linkage is connected with the fixed wing structure, and second end is installed on the first control surface element movingly; Motion sensor, this motion sensor is arranged to detect the flexible connection campaign of mechanical linkage, wherein, first end of cable is connected with second end of mechanical linkage, like this, the crooked and/or loss of one of them control surface element will cause the flexible connection campaign of mechanical linkage by second end of connecting rod with respect to the motion of the first control surface element.
The meaning of " mechanical linkage " is the structure that can be flexibly connected (articulate), for example many bars connecting rod mechanism, expansion link, strut etc.Because mechanical linkage is installed between fixed wing structure and the control surface element (being generally one of them terminal control surface element), therefore, the accidental movement of this element can directly detect by connecting rod, and the control surface element can not exempted crooked and/or loss detects.
In addition, because between the first control surface element and fixed part, only need mechanical linkage, therefore do not need electronic component or wiring to come across control surface element and fixed wing structure.Therefore, can avoid the above-mentioned shortcoming of this wiring.
Because motion sensor is positioned on the fixed wing structure, so it can suitablely cover and/or cover.It can also be easy to approaching so that safeguard and/or repairing.Because motion sensor is positioned on the fixed wing structure, so it can be positioned to leave the anti-icing zone with associated temperature extremum.
Description of drawings
Introduce the crooked and/or loss detection system of example of the present invention below with reference to the accompanying drawings, in the accompanying drawing:
Fig. 1 is mounted in the schematic plan view of on the aircraft wing front edge, the of the present invention first crooked and/or loss detection system;
Fig. 2 is the diagrammatic side view of the system of Fig. 1 along direction II;
Fig. 3 is the amplification view of the part of the crooked and/or loss detection system shown in Fig. 1 and 2;
Fig. 4 is the part sectional view of the described part of the crooked and/or loss detection system shown in Fig. 3;
Fig. 5 is mounted in the diagrammatic side view of on the aircraft wing front edge, the of the present invention second crooked and/or loss detection system; And
Fig. 6 is the amplification view of the part of the of the present invention the 3rd crooked and/or loss detection system.
The specific embodiment
With reference to figure 1, schematically illustrated the crooked and/or loss detection system 100 of control surface element among the figure.This system representation is to be installed on the fixed wing structure 102 with front edge 104.But become first leading edge slat 106, second leading edge slat 108, the 3rd leading edge slat 110 and the 4th leading edge slat 112 forms the self-movement of a plurality of control surface element be installed on the fixed wing structure 102.The method of installing and drive leading edge slat 106,108,110,112 is known in this field, will no longer further introduce here.The overall positions of leading edge slat system is indicated by the system motion sensor, and this system motion sensor is usually located at the extreme end position of each wing.
Crooked and/or loss detection system 100 comprises first connecting rod assembly 114, second connecting rod assembly 116 and cable assembly 118.First connecting rod assembly 114 and second connecting rod assembly 116 are basic identical, and the inside part (close fuselage) of the outermost part (away from fuselage) of the leading edge slat 106 of winning and the 4th leading edge slat 112 is connected with the fixed wing structure respectively.Here only introduce second connecting rod assembly 116 in detail, but should be known in that first connecting rod assembly 114 operates in the same manner.
With reference to figure 2, represented second connecting rod assembly 116 among the figure in detail.The sensor 120 that rotatablely moves for example rotates variable differential transformer (RVDT) and is installed on the fixed wing structure 102.The rotation input shaft 122 that leads to sensor 120 is connected with first end 124 of first connecting rod arm 126.Like this, first connecting rod arm 126 can be around its first end, 124 rotations, and this first end 124 is on the input shaft 122 of sensor 120.Therefore, the sensor 120 that rotatablely moves can detect any of first connecting rod arm 126 and rotatablely moves.Second end 128 of first connecting rod arm 126 pivotally is connected with first end 130 of second connecting rod arm 132, and like this, second connecting rod arm 132 can rotate with respect to first connecting rod arm 126 around its first end 130.Second end 134 of second connecting rod arm 132 is pivotally mounted on the slider element, as hereinafter described.
Second connecting rod assembly 116 also comprises slider rails 138, and this slider rails 138 is installed on the 4th leading edge slat 112.With reference to figure 3 and 4, slider rails 138 is hollow and prism essentially rectangular, has determined hollow cavity and bottom slot 140, and its function will be introduced in the back.Slit 140 extends along the whole length of track 138 substantially, and its width W is fully less than the width of the cavity of track 138.The first side wall 142 of track 138 comprises along track 138 longitudinally-spaced first positioning groove 144 and second positioning groove 146.In the end of track 138, cable guide slit 148 is formed in the end wall.
Should be known in that second connecting rod assembly 116 will flexibly connect motion when the 4th leading edge slat 112 during with respect to fixed wing structure 102 motion, make pitman arm 126,132 rotate relative to one another and with respect to sensor 120 rotations that rotatablely move.Therefore, in the proper motion process of the 4th leading edge slat 112, will estimate in the motion detection at sensor 120 places that rotatablely move.Motion at system motion sensor place record can compare with the motion by the sensor that rotatablely moves.Any deviation (for example excessive movements) all will be represented crooked or loss, as hereinafter described.
For cable assembly 118, the first not extending substantially cable part 168 is provided, it is installed on the cable mounting structure 160 of slider element 136.The first cable part 168 is returned guiding piece 170 by the cable that cable slit 148 leads in the 4th leading edge slat 112.Therefore, the first cable part 168 turns to 90 degree, extends so that be parallel to front edge 104.Then, the first cable part 168 is led to second leading edge slat 108 by the 3rd leading edge slat 110.Should be known in that the first cable part 168 and leading edge slat connect into can be with respect to the leading edge slat axial motion, like this, it can by since the motion crooked or that loss causes of leading edge slat be tightened up.For example, the first cable part 168 can wrap in the guide sleeve by the leading edge slat structure.
When the first cable part 168 arrived second leading edge slat 108, it was connected with idle motion arrangement 172.This idle motion arrangement 172 comprises cylinder 174, and piston 176 can slide in this cylinder 174.The first cable part 168 is connected with cylinder 174.Piston 176 is connected with the second cable part 178, like this, allows relative motion between the first cable part 168 and the second cable part 178 by the slip of piston 176 in cylinder 174.Piston 176 is by compression spring 180 bias voltages, thereby the end of cable part 168,178 is pushed to together.Idle motion arrangement 172 has solved any acceptable motion that cable during normal use causes owing to known facts, for example expansion and the contraction that causes owing to variation of ambient temperature and in use normal wing deflection (deflection).The installation window is provided in idle motion arrangement, and like this, it can be set in fitting process at an easy rate.
The second cable part 178 continues by being installed in second cable guide 182 on first leading edge slat 106.Second cable guide 182 makes cable 178 turn to 90 degree, makes it perpendicular to front edge 104.The second portion of cable 178 ends at the cable mounting structure in the first connecting rod assembly 114, will introduce this first connecting rod assembly 114 no longer in detail here.
In use, system operation is as follows:
The normal variation of the cable length between first connecting rod assembly 114 and second connecting rod assembly 116 is solved by idle motion arrangement 172.Therefore, since any tension of the cable that normal heat effect and/or wing flexure effect cause all will solve by idle motion arrangement.
For more serious situation (for example wing flap crooked or loss), idle motion arrangement 172 will " (bottom out) reduces as far as possible ".Specifically, compression spring 180 will compress fully, and piston 176 will arrive the end of cylinder 174.When this thing happens, tensile force was applied on the cable mounting structure 160 of the slider element 136 in the connecting rod assembly 114,116.With reference to figure 3, such power makes ball-bearing casing 156 leave first positioning groove 144 by compression spring 158.Then, slider element 136 will be with respect to 112 free motions of the 4th leading edge slat.Should be known in the character according to crooked and/or damaed cordition, also possible at first connecting rod assembly 114 places this thing happens.
This makes pitman arm 126,132 rotate relative to one another, and such flexible connection campaign will detect at sensor 120 places that rotatablely move.Therefore, when that meet accident or the excessive motion of first connecting rod assembly 114 with when flexibly connecting motion, expectation output (for example from the leading edge slat drive system) and real output by the sensor 120 that relatively rotatablely moves can detect crooked arbitrarily or loss.
In case slider element 136 arrives the place, end of the close cable guide slit 148 of track 138, ball-bearing casing 156 will enter second positioning groove 146 under the resilient force of spring 158.This guarantees that slider element 136 will remain on crooked and/or lose the detection position, and can not return its normal position when crooked and/or loss are enough to disconnect cable 168,178.Therefore, crooked and/or loss will keep and can detect, and make system reset up to service personnel.
Should be known in and preferably in wing components, detect crooked and/or loss, particularly first leading edge slat in a plurality of leading edge slats and last leading edge slat two positions.Therefore, crooked and/or loss will be by reliable Detection repeatedly.
With reference to figure 5, represented the second crooked and/or loss detection system 200 among the figure.The reference number of same characteristic features is identical with system 100.
In system 200, the sensor 120 that rotatablely moves is replaced by linear-movement pickup (for example LVDT) 202.Linear-movement pickup is determined its length variations, and is arranged to report these variations to the aircraft control system (not shown).
The form of 202 one-tenth extending struts of sensor, it is pivotally mounted on the fixed wing structure 102 at first end, 204 places, and is pivotally mounted on the slider element 136 at second end, 206 places.When the 4th leading edge slat 112 in use during proper motion, the length variations of sensor 202.Length variations by sensor 202 reports compares with estimating length variations (this expectation length variations has provided the 4th wing flap 112 along with the expectation campaign that drives).Notable difference between report length variations and predicted value is represented crooked or damaed cordition.
With reference to figure 6, represented the part of the 3rd crooked and/or loss detection system 300 among the figure.The reference number of same characteristic features is identical with system 100.Particularly, represented the part second connecting rod assembly, that comprise slider element 136 and track 138 among the figure.
In crooked and/or loss detection system 300, idle motion arrangement 172 is included in the track 138 and between the first cable part 168 and slider element 136.Idle motion arrangement 172 substantially with system 100 in identical mode come work.
Multiple variation falls within the scope of the invention.
By aforementioned invention, can detect the crooked and/or loss on one of the surface of arbitrary number.
Idle motion arrangement can be arranged in arbitrary surfaces or (according to system 300) slider element/rail mechanism.
Can use optional slider and detent mechanism, as long as can carry out motion of translation to a certain degree between mechanical linkage, this motion begins under predetermined cable strain loads.
Idle motion arrangement can be included in the slide mechanism in the each end, i.e. one of system moving in midair can solving by two devices, and one at the track place of first connecting rod, the track place at second connecting rod.Cable will be simplified by the installation on surface, and it will be easier that the cross-check sum of system is verified.
Claims (10)
1. crooked and/or loss detection system of aircraft control surface element comprises:
Aircraft wing structure, this aircraft wing structure comprise fixed part, the first control surface element and the second control surface element, and these elements are arranged to and can be moved with respect to fixed part;
Cable, this cable is connected with the first control surface element each with the second control surface element, and like this, in crooked and/or when loss when one of them control surface element, tightening force is applied on the cable;
Mechanical linkage, first end of this mechanical linkage is connected with the fixed wing structure, and second end is installed on the first control surface element movingly;
Motion sensor, this motion sensor are arranged to detect the flexible connection campaign of mechanical linkage,
Wherein, first end of cable is connected with second end of mechanical linkage, and like this, the crooked and/or loss of one of them control surface element causes the flexible connection campaign of mechanical linkage with respect to the motion of the first control surface element by second end of connecting rod.
2. the crooked and/or loss detection system of aircraft control surface element according to claim 1, wherein: motion sensor is installed on the fixed part of wing.
3. the crooked and/or loss detection system of aircraft control surface element according to claim 1 and 2, wherein: motion sensor is and pitman arm bonded assembly linear transducer.
4. the crooked and/or loss detection system of aircraft control surface element according to claim 1 and 2, wherein: motion sensor is the first pivotable arm bonded assembly rotation sensor with connecting rod.
5. the crooked and/or loss detection system of aircraft control surface element according to claim 4, wherein: mechanical linkage comprises connecting rod mechanism, this connecting rod mechanism comprises the first pivotable arm and the second pivotable arm, this second pivotable arm pivotally is connected with the first pivotable arm, and pivotally is connected with the first control surface parts at the second end place of connecting rod.
6. according to the crooked and/or loss detection system of aforementioned any one claim described aircraft control surface element, wherein: second end of connecting rod is connected with the control surface element by cliding joint.
7. the crooked and/or loss detection system of aircraft control surface element according to claim 6, wherein: when being lower than predetermined tightening force in the cable, second end that cliding joint suppresses connecting rod carries out motion of translation with respect to the first control surface element.
8. the crooked and/or loss detection system of aircraft control surface element according to claim 7, wherein, this cliding joint comprises:
First parts, these first parts are connected with second end of connecting rod;
Second parts, these second parts are connected with the first control surface element;
Wherein, first parts can slide with respect to second parts,
Cliding joint also comprises elastic bias component, the protrusion of this elastic bias component from first parts and second parts, and with in first parts and second parts another on detent engagement.
9. the crooked and/or loss detection system of aircraft control surface element according to claim 8, comprise: the described excess of stroke positioning groove in another in first parts and second parts, this excess of stroke positioning groove are arranged in the situation of crooked and/or loss and engage with elastic bias component.
10. according to the crooked and/or loss detection system of aforementioned any one claim described aircraft control surface element, wherein:
The aircraft wing structure comprises the 3rd control surface, and the 3rd control surface is in a side of the first control surface element relative with the second control surface element;
Another mechanical linkage wherein is provided, and first end of this another mechanical linkage is connected with the fixed wing structure, and second end of this another mechanical linkage is installed on the 3rd control surface element movingly;
Another motion sensor is provided, and this another motion sensor is arranged to detect the flexible connection campaign of this another mechanical linkage;
Wherein, second end of second another mechanical linkage of end and this of cable is connected, like this, the crooked and/or loss of one of them control surface element causes the flexible connection campaign of this another mechanical linkage with respect to the motion of the 3rd control surface element by second end of this another connecting rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101638115A CN102219052A (en) | 2010-04-15 | 2010-04-15 | Skew and/or damage detecting system of control surface element |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101638115A CN102219052A (en) | 2010-04-15 | 2010-04-15 | Skew and/or damage detecting system of control surface element |
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| Publication Number | Publication Date |
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| CN102219052A true CN102219052A (en) | 2011-10-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2010101638115A Pending CN102219052A (en) | 2010-04-15 | 2010-04-15 | Skew and/or damage detecting system of control surface element |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112351937A (en) * | 2018-06-11 | 2021-02-09 | 穆格伍尔弗汉普顿有限公司 | Control surface element inclination and/or loss detection system |
| CN117775272A (en) * | 2024-01-30 | 2024-03-29 | 中国商用飞机有限责任公司 | Leading edge slat and wing for aircraft |
-
2010
- 2010-04-15 CN CN2010101638115A patent/CN102219052A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112351937A (en) * | 2018-06-11 | 2021-02-09 | 穆格伍尔弗汉普顿有限公司 | Control surface element inclination and/or loss detection system |
| CN117775272A (en) * | 2024-01-30 | 2024-03-29 | 中国商用飞机有限责任公司 | Leading edge slat and wing for aircraft |
| CN117775272B (en) * | 2024-01-30 | 2024-05-14 | 中国商用飞机有限责任公司 | Leading edge slat and wing for aircraft |
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Application publication date: 20111019 |