CN113291458B - Inner and outer flap crosslinking device for high lift system of airplane - Google Patents
Inner and outer flap crosslinking device for high lift system of airplane Download PDFInfo
- Publication number
- CN113291458B CN113291458B CN202110715671.6A CN202110715671A CN113291458B CN 113291458 B CN113291458 B CN 113291458B CN 202110715671 A CN202110715671 A CN 202110715671A CN 113291458 B CN113291458 B CN 113291458B
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- CN
- China
- Prior art keywords
- corrugated pipe
- sleeve
- rod
- block
- support rod
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Links
- 238000004132 cross linking Methods 0.000 title claims abstract description 22
- 230000006698 induction Effects 0.000 claims description 17
- 238000001514 detection method Methods 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 description 5
- 230000003139 buffering effect Effects 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
- Fluid-Damping Devices (AREA)
Abstract
The invention may relate to the technical field of high lift systems, control surface control components, actuating components and the like of an aircraft, in particular to an inner and outer flap crosslinking device for the high lift systems of the aircraft. The device is used for an aircraft high lift system, is connected with an inner flap and an outer flap, and is sleeved on a support rod (2) through a corrugated pipe (7), a left support block (6) and a right support block (8) and can move relatively along the axial direction of the support rod (2); two ends of the corrugated pipe (7) are respectively stopped in the shell through the left supporting block (6) and the right supporting block (8); on the support rod (2), the outer side of the left support block (6) and the outer side of the right support block (8) are provided with limiting structures; when the supporting rod (2) axially moves, the limiting structure is driven to compress the corrugated pipe (7). The technical problem that the prior art can only absorb impact load generated when extending is solved, meanwhile, the double redundancy design is carried out on the proximity switch, and the reliability of the device is improved.
Description
Technical Field
The invention may relate to the technical field of high lift systems, control surface control components, actuating components and the like of an aircraft, in particular to an inner and outer flap crosslinking device for the high lift systems of the aircraft.
Background
An inner and outer flap crosslinking apparatus is disclosed in the published patent document, which has been issued with publication number CN107161325B as the closest prior art to the present solution. As shown in FIG. 1, the device includes a piston rod assembly 1-1, a piston cylinder assembly 1-2, an arcuate wedge 1-3, and a concave ring 1-4. The piston rod assembly 1-1 is disposed within the piston tube assembly 1-2 and is radially fixed and axially movable relative to the piston tube assembly 1-2. An arcuate wedge 1-3 is secured to the outside of the piston-cylinder assembly 1-2, the arcuate wedge 1-3 comprising a first wedge-shaped compression surface. The concave ring 1-4 is fixed on the outer side of the piston rod assembly 1-1, the concave ring 1-4 comprising a second wedge-shaped pressing surface. When the first wedge-shaped pressing surface is contacted with the second wedge-shaped pressing surface, axial force is generated to realize forward buffering. The inner and outer flap cross-linking device can only absorb impact loads generated during extension.
Disclosure of Invention
The invention solves the technical problems that: the technical problem that the impact load generated when the prior art only can absorb the extension is solved by the crosslinking device, and meanwhile, the double redundancy design is carried out on the proximity switch, so that the reliability of the device is improved.
The technical scheme of the invention is as follows: a cross-linking device for use in an aircraft high lift system connecting inner and outer flaps, the device comprising a housing, a support rod, a bellows, a left support block and a right support block;
The corrugated pipe, the left support block and the right support block are sleeved on the support rod and can move relatively along the axial direction of the support rod;
Two ends of the corrugated pipe are respectively stopped in the shell through the left supporting block and the right supporting block;
On the support bar, the outer side of the left support block and the outer side of the right support block are provided with limiting structures;
when the supporting rod axially moves, the limiting structure is driven to compress the corrugated pipe. The technical scheme realizes the bidirectional buffer function.
Preferably, the device further comprises a sensor, the supporting rod is provided with a sensing surface capable of axially moving along with the supporting rod, the sensing surface is provided with a concave/convex structure, and the sensor gives different feedback signals by detecting the distance between the sensor and the sensing surface. The technical scheme realizes the monitoring of the travel and provides a basis for fault feedback.
Preferably, the number of the sensors is plural. The technical scheme realizes redundancy design and improves the reliability of the system.
Preferably, the support rod is sleeved with an induction sleeve, the outer circumferential surface of the induction sleeve is an induction surface, and the outer circumferential surface is provided with an annular groove. The technical scheme specifically discloses a technical means of stroke detection, simple structure, convenient use, reliability are high.
Preferably, the distance between the inner end surfaces of the two limiting structures is larger than the distance between the outer end surface of the left support block and the outer end surface of the right support block in the free state of the corrugated pipe; in the range of the distance difference, the corrugated pipe is kept in a free state, and the supporting rod can axially and freely move. That is, in this range, the support rod does not compress the bellows in the axial direction, and there is a lost motion design.
Preferably, the distance between the sensing surface and the sensor is constant within the range of axial free movement of the bellows holding free state support rod. The technical scheme discloses more technical means of the idle stroke design, and the compatibility of fault feedback and the idle stroke design is realized.
Preferably, the one-side limiting structure is a boss on the outer circumferential surface of the supporting rod.
Preferably, one end of the supporting rod is fixedly connected with a fixing rod through threads.
The invention has the beneficial effects that: compared with the prior art, the technical scheme realizes the absorption of impact loads in the extending and retracting directions by utilizing the compression and buffering of the corrugated pipe through the structural design, and feeds back fault signals to the control computer; meanwhile, through ingenious structural design, the inner and outer flap crosslinking device also has an idle stroke for extending and retracting so as to adapt to the stroke difference between the inner and outer flaps during extending and retracting; in addition, redundancy backup is realized through ingenious design of the sensor and the sensing surface, and the reliability of the device is improved.
Drawings
FIG. 1 is a schematic view of a prior art inner and outer flap cross-linking apparatus;
FIG. 2 is a perspective view of the device of the present invention;
FIG. 3 is a cross-sectional view A-A;
FIG. 4 is a schematic view of a bellows;
Fig. 5 is a schematic view of the structure of the support bar.
Wherein: 1. a fixed rod; 2. a support rod; 3. a left housing; 4. a screw; 5. a main housing; 6. a left support block; 7. a bellows; 8. a right support block; 9. a limit sleeve; 10. an induction sleeve; 11. a proximity switch; 12. a nut; 13. a transition plate; 14. a flap control computer; 15. a boss.
Detailed Description
The invention provides a technical scheme of an inner flap and outer flap crosslinking device. The basic composition of the inner and outer flap crosslinking device is as shown in fig. 2 and 3, and the inner and outer flap crosslinking device comprises a fixed rod 1, a supporting rod 2, a left shell 3, a screw 4, a main shell 5, a left supporting block 6, a corrugated pipe 7, a right supporting block 8, a limiting sleeve 9, an induction sleeve 10, a proximity switch 11, a nut 12 and a transition plate 13.
The fixed rod 1 is in threaded connection with the supporting rod 2, the left shell 3 and the main shell 5 are fixedly connected through screws 4 uniformly distributed in the circumferential direction, the left end face of the corrugated pipe 7 is supported by the left supporting block 6, the right end face of the corrugated pipe 7 is supported by the right supporting block 8, the left supporting block 6 and the right supporting block 8 are nested in the main shell 5, and the limiting sleeve 9 and the sensing sleeve 10 are fixed on the supporting rod 2 through nuts 12. One end of the supporting rod is provided with a boss 15, and the end surfaces of the boss 15 and the limiting sleeve 9 can be respectively stopped on the end surfaces of the supporting block 6 and the right supporting block 8. The two proximity switches 11 are fixed on the main housing in a vertically opposite manner through the transition plate 13, and the detection surface of the proximity switch 11 faces the outer circumferential surface of the induction sleeve 10 without contact between the two surfaces. When the proximity switch 11 changes by sensing the distance between the detection surface of the proximity switch 11 and the outer circumferential surface of the sleeve 10 beyond a certain range, the proximity switch 11 feeds back a signal to the flap control computer 14.
The distance from the inner end surface of the boss 15 to the inner end surface of the limit sleeve 9 is a. In the free state of the bellows 7, the distance from the left (outer) end face of the left support block 6 to the right (outer) end face of the right support block 8 is b. In this embodiment, a is greater than b by about 36mm. In the range of the distance difference, the corrugated pipe is kept in a free state, and the supporting rod can axially and freely move. In addition, the diameter of the outer circumferential surface of the sensing sleeve 10 does not change in the free movement range of the support rod.
The operation process of the device under different working states is as follows:
Extension and retraction idle travel state: because the inner and outer flaps of the high lift system adopt a centralized driving mode, the inner and outer flaps synchronously move when the flaps of the high lift system extend or retract, and at the moment, an inner and outer flap crosslinking device connected between the inner and outer flaps synchronously moves along with the inner and outer flaps, and auxiliary constraint is not provided for the wing surfaces of the inner and outer flaps. At this time, because a gap is reserved between the left end face of the limit sleeve 9 and the right end face of the right support block 8, the fixed rod 1 can freely extend until the left end face of the limit sleeve 9 contacts with the right end face of the right support block 8, the distance between the outer circular face of the induction sleeve 10 and the induction face of the proximity switch 11 is unchanged in the whole extending process, and the proximity switch 11 does not feed back a fault signal to the flap control computer 14; because a gap exists between the right end face of the boss 15 and the left end face of the left support block 6, the left fixing rod 1 can be freely retracted until the right end face of the boss 15 is contacted with the left end face of the left support block 6, the distance between the outer circular face of the sensing sleeve 10 and the sensing face of the proximity switch 11 is unchanged in the whole retraction process, and the proximity switch 11 does not feed back fault signals to the flap control computer 14.
Extended and retracted buffer state: when the high lift system drives the flap to extend or retract, if a certain actuator for driving the flap breaks away, the airfoil surface can incline to a large extent (the flap inclines to a fault), thereby preventing the flight safety. The inner and outer flap cross-linking means, which is now disposed between the inner and outer flaps, may act to reduce excessive lean of the failed airfoil and provide additional constraint to the failed airfoil. After the left end face of the limiting sleeve 9 of the inner and outer flap crosslinking device is contacted with the right end face of the right supporting block 8, the extension load is transmitted to the corrugated pipe 7 through the limiting sleeve 9 and the right supporting block 8, the corrugated pipe 7 is compressed to play a buffering role, the distance between the outer circular face of the sensing sleeve 10 and the sensing face of the proximity switch 11 is increased in the whole buffering process, and the proximity switch 11 feeds back a fault signal to the control computer 14; when an inner flap crosslinking device and an outer flap crosslinking device are needed to achieve the retraction buffer function, after the right end face of the boss 15 is contacted with the left end face of the left supporting block 6, retraction load is transmitted to the corrugated pipe 7 through the supporting rod 2 and the left supporting block 6, the corrugated pipe 7 is compressed to play a role in buffer, the distance between the outer circular face of the sensing sleeve 10 and the sensing face of the proximity switch 11 is increased in the whole buffer process, and the proximity switch 11 feeds back fault signals to the flap control computer 14.
Claims (4)
1. A cross-linking device for connecting inner and outer flaps of an aircraft high lift system, characterized in that the device comprises a support rod (2), a left shell (3), a main shell (5), a corrugated pipe (7), a left support block (6), a right support block (8), a limit sleeve (9), an induction sleeve (10), a proximity switch (11), a nut (12) and a transition plate (13);
The left shell (3) and the main shell (5) are fixedly connected through screws (4) uniformly distributed in the circumferential direction, and the corrugated pipe (7), the left supporting block (6) and the right supporting block (8) are sleeved on the supporting rod (2) and can move relatively along the axial direction of the supporting rod (2);
Two ends of the corrugated pipe (7) are respectively stopped in the main shell through a left supporting block (6) and a right supporting block (8);
the limit sleeve (9) and the induction sleeve (10) are fixed on the support rod (2) through nuts,
On the support rod (2), the outer side of the left support block (6) and the outer side of the right support block (8) are provided with limiting structures; one end of the supporting rod is provided with a boss (15), and the end surfaces of the boss (15) and the limiting sleeve (9) are respectively stopped on the end surfaces of the left supporting block (6) and the right supporting block (8); the two proximity switches (11) are fixed on the main shell in an up-down opposite mode through the transition plates (13), the detection surface of each proximity switch (11) faces the outer circumferential surface of the corresponding induction sleeve (10), and the two surfaces are not contacted; when the proximity switch (11) senses the change of the distance between the detection surface of the proximity switch (11) and the outer circumferential surface of the induction sleeve (10) through the induction detection head and exceeds a certain range, the proximity switch (11) feeds back a signal to the flap control computer (14); the distance from the inner side end surface of the boss (15) to the inner side end surface of the limit sleeve (9) is a; in the free state of the corrugated pipe (7), the distance from the left end face of the left support block (6) to the right end face of the right support block (8) is b, a is larger than b, and in the range of the distance difference, the corrugated pipe is kept in the free state, and the support rod can axially and freely move; in addition, the diameter of the outer circumferential surface of the induction sleeve 10 does not change in the free movement range of the support rod; outside the range of the distance difference, the support rod (2) drives the limiting structure to compress the corrugated pipe (7) when moving axially.
2. A cross-linking apparatus as claimed in claim 1, wherein the support bar (2) is provided with a sensing surface which is axially movable with the support bar, and the sensing surface is provided with a concave/convex structure.
3. A cross-linking apparatus as claimed in claim 2, wherein said support rod (2) is provided with an induction sleeve (10), an outer circumferential surface of said induction sleeve (10) being an induction surface, and said outer circumferential surface being provided with an annular groove.
4. A cross-linking apparatus as claimed in any one of claims 1 to 3, wherein one end of the support rod (2) is fixedly connected to the fixing rod (1) by means of a screw thread.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110715671.6A CN113291458B (en) | 2021-06-25 | 2021-06-25 | Inner and outer flap crosslinking device for high lift system of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110715671.6A CN113291458B (en) | 2021-06-25 | 2021-06-25 | Inner and outer flap crosslinking device for high lift system of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113291458A CN113291458A (en) | 2021-08-24 |
| CN113291458B true CN113291458B (en) | 2024-07-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110715671.6A Active CN113291458B (en) | 2021-06-25 | 2021-06-25 | Inner and outer flap crosslinking device for high lift system of airplane |
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| Country | Link |
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| CN (1) | CN113291458B (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112678151A (en) * | 2021-01-13 | 2021-04-20 | 中国商用飞机有限责任公司 | Device for cross-linking between flaps |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB542944A (en) * | 1940-08-02 | 1942-02-03 | Dehavilland Aircraft | Improvements in or relating to actuating mechanism for aircraft controls |
| FR1546878A (en) * | 1966-11-29 | 1968-11-22 | Saab Ab | Device for adjusting the lift of an aircraft during approach and for reversing jet thrust during taxiing |
| DE3505839A1 (en) * | 1985-02-20 | 1986-08-21 | Messerschmitt-Bölkow-Blohm GmbH, 2800 Bremen | Failure protection device for flap systems on aircraft mainplanes |
| CN1184056A (en) * | 1996-11-29 | 1998-06-10 | 三星航空产业株式会社 | Airfoil of aircraft |
| US6598834B2 (en) * | 2000-02-14 | 2003-07-29 | Aerotech Services Inc. | Method for reducing fuel consumption in aircraft |
| DE102009060326A1 (en) * | 2009-12-23 | 2011-06-30 | Airbus Operations GmbH, 21129 | High-lift system for an aircraft |
| WO2014153518A1 (en) * | 2013-03-22 | 2014-09-25 | Moog Inc. | High sensitivity, load alleviating load sensor for strut application |
| EP3324072B1 (en) * | 2016-11-21 | 2020-04-15 | Ratier-Figeac SAS | Damping assembly |
| CN107161325B (en) * | 2017-07-31 | 2018-09-11 | 中国商用飞机有限责任公司 | Inner and outer flap cross-linking device |
| JP6929761B2 (en) * | 2017-11-16 | 2021-09-01 | 三菱重工業株式会社 | Electric actuator device |
| CN108100235B (en) * | 2017-11-22 | 2021-01-08 | 中国航空工业集团公司西安飞机设计研究所 | Flap position control mechanism |
| US10882604B2 (en) * | 2018-01-18 | 2021-01-05 | The Boeing Company | Distributed trailing edge wing flap systems |
| CN109443314A (en) * | 2018-10-24 | 2019-03-08 | 庆安集团有限公司 | A kind of high-lift system slant detection method |
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2021
- 2021-06-25 CN CN202110715671.6A patent/CN113291458B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112678151A (en) * | 2021-01-13 | 2021-04-20 | 中国商用飞机有限责任公司 | Device for cross-linking between flaps |
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| CN113291458A (en) | 2021-08-24 |
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