CN111846200A - Aviation dual-redundancy flap retraction device - Google Patents
Aviation dual-redundancy flap retraction device Download PDFInfo
- Publication number
- CN111846200A CN111846200A CN202010520813.9A CN202010520813A CN111846200A CN 111846200 A CN111846200 A CN 111846200A CN 202010520813 A CN202010520813 A CN 202010520813A CN 111846200 A CN111846200 A CN 111846200A
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- Prior art keywords
- gear
- flap
- electric actuating
- actuating mechanism
- connecting rod
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- 230000007246 mechanism Effects 0.000 claims abstract description 28
- 230000009977 dual effect Effects 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to a dual-redundancy wing flap retracting device for aviation, belonging to the field of wing flaps of fixed-wing airplanes; the device comprises a first electric actuating mechanism, a second electric actuating mechanism, a gear and a connecting rod, wherein the first electric actuating mechanism and the second electric actuating mechanism are arranged in parallel and oppositely, output shafts of the first electric actuating mechanism and the second electric actuating mechanism are two racks which are arranged in parallel and oppositely, and the two racks can do reciprocating linear motion along the output axial direction of the electric actuating mechanism; one end of the connecting rod is hinged with the gear through a shaft, and the other end of the connecting rod is hinged with the flap through a shaft. The invention adopts the transmission form that two electric actuating mechanisms with output shafts as racks are simultaneously meshed with the gears to control the retraction and the release of the airplane flap, realizes the dual-redundancy flap retraction and release of the two electric actuating mechanisms which are mutually backups, has simple structure and improves the reliability and the safety of the flap retraction and release.
Description
Technical Field
The invention belongs to the field of flaps of fixed-wing airplanes, and particularly relates to a dual-redundancy flap retracting device for aviation.
Background
At present, with the development and progress of the market of general-purpose airplanes, the requirements for the retraction and the release of the flap are higher and higher, and the flap retraction and release device can ensure the safety and the reliability of the retraction and the release of the flap.
At present, the small and medium-sized general airplanes mainly adopt the retraction and the release of an output shaft of an electric actuating cylinder to control the retraction and the release of a flap. The electric actuating cylinder directly drives the control surface through the output shaft, the operation mode is a single redundancy operation mode, when the output shaft of the electric actuating cylinder cannot be released or retracted due to faults, the flap cannot be normally retracted or released, the airplane cannot normally take off and land, and personal safety of each driver and each passenger brings danger. In order to improve the safety and reliability of the flap retraction, a dual-redundancy flap retraction device is needed. The scheme provides a wing flap folding and unfolding device which is composed of two electric actuating mechanisms with output shafts in a rack structure, gears meshed with the racks of the two output shafts and the like, and double-redundancy wing flap folding and unfolding of the two electric actuating mechanisms which are backups of each other is realized.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides a dual-redundancy flap retracting and releasing device, which solves the problem that the flap of an airplane cannot be normally retracted or released when an extension shaft of the conventional electric actuating cylinder cannot be released or retracted.
The technical scheme of the invention is as follows: the utility model provides a wing flap retractable device of aviation with dual redundancy which characterized in that: the device comprises a first electric actuating mechanism, a second electric actuating mechanism, a gear and a connecting rod, wherein the first electric actuating mechanism and the second electric actuating mechanism are arranged in parallel and oppositely, output shafts of the first electric actuating mechanism and the second electric actuating mechanism are two racks which are arranged in parallel and oppositely, and the two racks can do reciprocating linear motion along the output axial direction of the electric actuating mechanism;
One end of the connecting rod is hinged with the gear through a shaft, and the other end of the connecting rod is hinged with the flap through a shaft; the axial direction of the gear is perpendicular to the axial direction of the connecting rod, and the gear is arranged between the two racks and meshed with the racks; the electric actuator drives the rack to further drive the gear to rotate and perform reciprocating linear motion along the axial direction of the rack, so that the connecting rod drives the flap to be retracted.
The further technical scheme of the invention is as follows: the gear is a cylindrical gear, and the tooth form of the gear is an involute type.
The further technical scheme of the invention is as follows: the module of the two racks is equal to the module of the gear in size, and the pressure angle is equal to the pressure angle of the gear.
Advantageous effects
The invention has the beneficial effects that: when the output shafts of the two electric actuating mechanisms are simultaneously released or retracted, the retraction and release of the flap are realized by pushing or pulling the gear; when one electric actuator does not work, the output shaft of the other electric actuator is released or retracted, and the retraction and release of the flap are realized by the meshing motion of the rack and the gear. The invention adopts the transmission form that two electric actuating mechanisms with output shafts as racks are simultaneously meshed with the gears to control the retraction and the release of the airplane flap, realizes the dual-redundancy flap retraction and release of the two electric actuating mechanisms which are mutually backups, has simple structure and improves the reliability and the safety of the flap retraction and release.
Drawings
Fig. 1 is a schematic view of the first electric actuator and the second electric actuator of the present invention both operating normally to drive flap retraction.
Fig. 2 is a schematic view of the first electric actuator and the second electric actuator of the present invention both operating normally with the drive flap lowered.
FIG. 3 is a schematic view of the present invention with a second electric actuator driving flap retraction when the first electric actuator is inoperable.
FIG. 4 is a schematic view of the present invention with the first electric actuator driving flap retraction when the second electric actuator is inoperable.
Fig. 5 is a schematic view of the invention with the flap being driven down by the second electric actuator when the first electric actuator is inoperative.
Fig. 6 is a schematic view of the invention with the flap being driven down by the first electric actuator when the second electric actuator is inoperative.
Description of reference numerals: 1-a first electric actuator, 2-a second electric actuator, 3-a gear, 4-a first shaft, 5-a second shaft, 6-a connecting rod.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
As shown in figure 1, the aviation dual-redundancy flap retraction device comprises a first electric actuator 1, a second electric actuator 2, a gear 3 and a connecting rod 6, wherein output parts of the first electric actuator 1 and the second electric actuator 2 are both in a rack structure and are parallelly installed on two sides of the gear 3 to be meshed with the gear 3, two ends of the connecting rod 6 are respectively an A end and a B end, the center of the gear 3 is hinged and connected with the A end of the connecting rod 6 through a first shaft 4 so that the gear 3 can rotate around the A end of the connecting rod 6, and the B end of the connecting rod 6 is hinged and connected with a flap through a second shaft 5. When the first electric actuator 1 and the second electric actuator 2 work normally and both release the racks, the gear 3 is pushed to move due to the meshing relationship between the racks and the gear 3, and then the flap is driven to retract through the connecting rod 6.
As shown in fig. 2, when the first electric actuator 1 and the second electric actuator 2 both work normally and retract the racks, the gear 3 is pulled to move, and then the flap is driven to be put down through the connecting rod 6.
As shown in fig. 3, the first electric actuator 1 is disabled, the second electric actuator 2 releases the rack, and since the first electric actuator 1 is self-locked at the position, the gear 3 is rotated and moved in the rack release direction of the second electric actuator 2 by the meshing relationship between the rack of the second electric actuator 2 and the gear 3 and the meshing relationship between the rack of the first electric actuator 1 and the gear 3, thereby driving the flap retraction by the link 6.
As shown in fig. 4, the second electric actuator 2 is disabled, the first electric actuator 1 releases the rack, and since the second electric actuator 2 is self-locked at the position, the gear 3 is rotated and moved in the rack release direction of the first electric actuator 1 by the meshing relationship between the rack of the first electric actuator 1 and the gear 3 and the meshing relationship between the rack of the second electric actuator 2 and the gear 3, and the flap retraction is driven by the link 6.
As shown in fig. 5, the first electric actuator 1 cannot work, the second electric actuator 2 retracts the rack, and since the first electric actuator 1 is self-locked at the position, the meshing relationship between the rack of the second electric actuator 2 and the gear 3 and the meshing relationship between the rack of the first electric actuator 1 and the gear 3 cause the gear 3 to rotate and move in the rack retracting direction of the second electric actuator 2, so that the flap is driven to be lowered through the link 6.
As shown in fig. 6, the second electric actuator 2 cannot work, the first electric actuator 1 retracts the rack, and since the second electric actuator 2 is self-locked at the position, the meshing relationship between the rack of the first electric actuator 1 and the gear 3 and the meshing relationship between the rack of the second electric actuator 2 and the gear 3 cause the gear 3 to rotate and move in the rack retracting direction of the first electric actuator 1, so that the flap is driven to be lowered through the link 6.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (3)
1. The utility model provides a wing flap retractable device of aviation with dual redundancy which characterized in that: the device comprises a first electric actuating mechanism, a second electric actuating mechanism, a gear and a connecting rod, wherein the first electric actuating mechanism and the second electric actuating mechanism are arranged in parallel and oppositely, output shafts of the first electric actuating mechanism and the second electric actuating mechanism are two racks which are arranged in parallel and oppositely, and the two racks can do reciprocating linear motion along the output axial direction of the electric actuating mechanism;
One end of the connecting rod is hinged with the gear through a shaft, and the other end of the connecting rod is hinged with the flap through a shaft; the axial direction of the gear is perpendicular to the axial direction of the connecting rod, and the gear is arranged between the two racks and meshed with the racks; the electric actuator drives the rack to further drive the gear to rotate and perform reciprocating linear motion along the axial direction of the rack, so that the connecting rod drives the flap to be retracted.
2. The dual-redundancy flap retraction device for aeronautics according to claim 1, wherein: the gear is a cylindrical gear, and the tooth form of the gear is an involute type.
3. The dual-redundancy flap retraction device for aeronautics according to claim 1, wherein: the module of the two racks is equal to the module of the gear in size, and the pressure angle is equal to the pressure angle of the gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010520813.9A CN111846200A (en) | 2020-06-10 | 2020-06-10 | Aviation dual-redundancy flap retraction device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010520813.9A CN111846200A (en) | 2020-06-10 | 2020-06-10 | Aviation dual-redundancy flap retraction device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111846200A true CN111846200A (en) | 2020-10-30 |
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ID=72987324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010520813.9A Pending CN111846200A (en) | 2020-06-10 | 2020-06-10 | Aviation dual-redundancy flap retraction device |
Country Status (1)
| Country | Link |
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| CN (1) | CN111846200A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115384758A (en) * | 2021-05-14 | 2022-11-25 | 陕西飞机工业有限责任公司 | Airplane flap redundancy control system and method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE747146C (en) * | 1941-03-01 | 1945-01-08 | Control gear for an aileron that can be extended on extension arms from the wing of an aircraft | |
| CN101595029A (en) * | 2006-10-18 | 2009-12-02 | 穆格公司 | Jam-tolerant redundant differential-type actuators |
| CN206940090U (en) * | 2017-05-15 | 2018-01-30 | 天津东方浩瑞光电科技有限公司 | A kind of cable machine |
| CN107719639A (en) * | 2017-09-12 | 2018-02-23 | 陕西飞机工业（集团）有限公司 | A kind of double remaining wing flap automatic control systems |
| CN109895995A (en) * | 2019-04-10 | 2019-06-18 | 珠海市海卫科技有限公司 | A kind of wing flap control mechanism of light-duty sport plane |
-
2020
- 2020-06-10 CN CN202010520813.9A patent/CN111846200A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE747146C (en) * | 1941-03-01 | 1945-01-08 | Control gear for an aileron that can be extended on extension arms from the wing of an aircraft | |
| CN101595029A (en) * | 2006-10-18 | 2009-12-02 | 穆格公司 | Jam-tolerant redundant differential-type actuators |
| CN206940090U (en) * | 2017-05-15 | 2018-01-30 | 天津东方浩瑞光电科技有限公司 | A kind of cable machine |
| CN107719639A (en) * | 2017-09-12 | 2018-02-23 | 陕西飞机工业（集团）有限公司 | A kind of double remaining wing flap automatic control systems |
| CN109895995A (en) * | 2019-04-10 | 2019-06-18 | 珠海市海卫科技有限公司 | A kind of wing flap control mechanism of light-duty sport plane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115384758A (en) * | 2021-05-14 | 2022-11-25 | 陕西飞机工业有限责任公司 | Airplane flap redundancy control system and method |
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