CN110550191B - Aircraft landing gear position indicating mechanism and indicating method - Google Patents
Aircraft landing gear position indicating mechanism and indicating method Download PDFInfo
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- CN110550191B CN110550191B CN201910761948.1A CN201910761948A CN110550191B CN 110550191 B CN110550191 B CN 110550191B CN 201910761948 A CN201910761948 A CN 201910761948A CN 110550191 B CN110550191 B CN 110550191B
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- stop block
- fan
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- 238000000034 method Methods 0.000 title claims abstract description 10
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 9
- 239000010959 steel Substances 0.000 claims abstract description 9
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
- B64C25/28—Control or locking systems therefor with indicating or warning devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Traffic Control Systems (AREA)
- Emergency Lowering Means (AREA)
Abstract
A position indicator for the landing gear of airplane is composed of a guide unit linked with the supporting post of landing gear, an indicator driven by said guide unit, a fan-shaped moving part coaxial with said supporting post, an eccentric axle linked with said moving part, a stop block hinged to the body of airplane, and a steel cable for connecting said moving part to said indicator. The method ensures that the correct information of the landing gear falling position can be provided for a pilot mechanically through the fan-shaped movable part and the indicating device under the condition that the landing gear position indicating system fails.
Description
Technical Field
The patent relates to an aircraft design technology, in particular to an aircraft landing gear position indicating mechanism and an indicating method.
Background
The landing gear is a take-off and landing device of the airplane, and has the functions of ensuring take-off running and landing sliding of the airplane and absorbing impact and jumping energy generated during landing and ground movement. When an airplane takes off and lands or flies, a pilot needs to timely and accurately acquire the position information of the undercarriage. The position indicating mechanism of the aircraft landing gear triggers the indicating mechanism to act to send out an in-place signal after the rotating angular displacement of the landing gear reaches a set value, and is suitable for indicating the position of the aircraft landing gear and indicating the in-place position of other angular displacements.
The aircraft landing gear position indicating mechanism is arranged in a landing gear cabin and extends to an outer skin of an aircraft, and a pilot observes whether an indicating rod extends out of the skin at a side window of the aircraft to judge whether the landing gear is put down in place. When the airplane is in a flying state, the landing gear indicator rod retracts into the airplane skin; when the aircraft lands, after the pilot carries out the operation of putting the landing gear in place, if the normal indication system of the aircraft landing gear fails, the pilot can carry out normal landing at the moment if the indication rod extends out of the skin of the aircraft to indicate that the landing gear is put down in place; if the indication rod does not extend out of the skin of the airplane, indicating that the landing gear is not put down in place, emergency measures should be taken for landing.
In general, a micro-electric door is arranged at the landing gear lowering position, when the landing gear is lowered in place, the electric door is connected, a landing gear lowering indicator lamp positioned in a cockpit is lighted, and a pilot receives the landing gear lowering in-place information. When the aircraft loses power supply or the micro-switch is in failure, the pilot can not judge whether the undercarriage is put down, and can only land according to the command of the airport tower at the moment, however, the tower can not judge whether the undercarriage is in place at the put-down position, and the undercarriage is pressed and retracted during the landing process possibly caused by the landing at the moment, so that flight accidents are caused. Therefore, a set of standby undercarriage down position mechanical indicating mechanism needs to be designed, and it is guaranteed that a pilot can effectively judge whether the undercarriage is down to the position or not by observing an indicating rod arranged on an outer skin of the airplane under the emergency condition.
Disclosure of Invention
The invention aims to provide an aircraft landing gear position indicating mechanism and an indicating method, which can realize standby indication of the landing gear down position under the condition that a landing gear normal position indicating system has a fault.
The position indicating mechanism for airplane landing gear includes a guide unit and an indicator unit, the guide unit includes a sector movable part coaxial with the landing gear support, the sector movable part has one arc chute with one notch, the landing gear support has one eccentric shaft corresponding to the arc chute, the eccentric shaft is embedded in the arc chute to link the sector movable part with the landing gear support, and one Y-shaped stop block with middle part hinged to the airplane body and two arms in the front end.
When the undercarriage is retracted, an eccentric shaft on an undercarriage strut is positioned at the left end of an arc-shaped sliding groove of the fan-shaped moving part and continues to move leftwards to drive the fan-shaped moving part to rotate, so that a second support arm of the stop block is clamped in a clamping groove at the right end of the arc-shaped sliding groove, and the steel cable traction spring actuating cylinder drives the indicating rod to retract into an outer skin of the airplane; when the undercarriage is in a down position, an eccentric shaft on an undercarriage support post moves towards the right end along an arc-shaped sliding groove on the fan-shaped moving part, when the eccentric shaft meets a first support arm of the stop block, the first support arm is lifted along the arc-shaped edge of the first support arm, then the second support arm is driven to be separated from the clamping groove, the stop block is relieved from limiting the fan-shaped moving part, the indicating rod is popped out of the airplane skin by the spring actuating cylinder to indicate that the undercarriage is down, and meanwhile, the spring actuating cylinder drives the steel cable to pull the fan-shaped moving part to reset.
The invention has the beneficial effects that: the mechanism and the method for indicating the landing gear position of the airplane are linked with a landing gear support column of the airplane, so that the correct information of the landing gear down position can be provided for a pilot through the fan-shaped moving part and the spring actuator cylinder machinery under the condition that the landing gear position indicating system is in failure.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of a position indicating mechanism when the landing gear is stowed.
FIG. 2 is a schematic view of the off-center shaft release stop during landing gear lowering.
FIG. 3 is a schematic view of the position indicating mechanism with the landing gear in place.
Figure 4 is a schematic view of a fan-shaped moving part structure.
FIG. 5 is a schematic view of a stopper structure
The numbering in the figures illustrates: 1. a landing gear strut; 2. an eccentric shaft; 3. a fan-shaped movable part; 4. a stopper block; 5. stretching the spring; 6. a steel cord; 7. a pulley; 8. a spring actuator cylinder; 9. aircraft skin; 10. an indication lever; 11. an arc-shaped chute; 12, a clamping groove; 13. a first support arm; 14. a second support arm; 15 arc-shaped sliding rails.
Detailed Description
Referring to the drawings, the aircraft landing gear position indicating mechanism of the present application, as shown in fig. 1 to 5, includes a guiding device and an indicating device which are linked with a landing gear strut 1, the guiding device includes a fan-shaped moving part 3 coaxial with the landing gear strut, an arc-shaped sliding groove 11 is provided on the fan-shaped moving part 3, a recessed slot 12 is provided at the right end of the arc-shaped sliding groove 11, an eccentric shaft 2 corresponding to the arc-shaped sliding groove 11 is fixed on the landing gear strut 1, the eccentric shaft 2 is embedded in the arc-shaped sliding groove 11 to link the fan-shaped moving part 3 with the landing gear strut 1, a Y-shaped stop block 4 is provided, the middle of the stop block 4 is hinged on the aircraft body, the front end of the stop block 4 is provided with two support arms, wherein the first support arm 13 has an arc-shaped edge, the end surface of the second support arm 14 is a plane, the other end of the stop block 4 is connected to the moving part by a tension spring 5, the first support arm 13 of the stop block 4 can be matched with the eccentric shaft 2 on the landing gear strut 1, the second support arm 14 on the stop block 4 is closely attached to the arc-shaped sliding groove 11 of the fan-shaped moving part 3, and a steel cable 6 connects the fan-shaped indicating device 3. The indicating device comprises a spring actuating cylinder 8 fixed on the airplane body and an indicating rod 10 coaxial with the spring actuating cylinder 8, wherein the lower end of the spring actuating cylinder 8 is connected with the steel cable 6, the lower end of the indicating rod 10 is connected with the actuating surface of the spring actuating cylinder 8, and the indicating rod 10 can move up and down under the driving of the spring actuating cylinder 8. The guide pulley 7 is fixed to the aircraft body and serves to guide the wire rope 6.
In the implementation, in order to better enable the stop block 4 to exert the stop effect on the fan-shaped moving part 3, an arc-shaped sliding rail 15 is arranged below the arc-shaped sliding groove 11 of the fan-shaped moving part 3, the stop block 4 is attached to the arc-shaped sliding rail 15, and a clamping groove 12 is formed at the right end head of the arc-shaped sliding rail.
When the landing gear is in the down position, the state of the indicating mechanism is shown in fig. 3, the indicating rod 10 extends out of the aircraft skin 9, the eccentric shaft 2 on the landing gear strut 1 is positioned at the leftmost end of the arc-shaped sliding groove of the fan-shaped movable part 3, and the stop block 4 is in a loose state relative to the fan-shaped movable part 3. When the landing gear is retracted, the landing gear strut 1 rotates clockwise, meanwhile, the eccentric shaft 2 drives the fan-shaped moving part 3 to rotate clockwise, the fan-shaped moving part 3 drives the steel cable 6 to compress the spring actuating cylinder 8 through the pulley 7, the indicating rod 10 is forced to move towards the spring actuating cylinder 8, and when the landing gear is completely retracted, the indicating rod 10 retracts into the aircraft skin 9; the arc chute 11 is provided with a concave clamping groove 12 at the extreme position, when the fan-shaped moving part 3 moves to the extreme position, the stop block 4 slides downwards into the clamping groove 12 along the arc slide rail 15 under the action of the tension of the extension spring 5, and the second support arm 14 of the stop block 4 is clamped, so that the fan-shaped moving part 3 is stopped, the indicating rod 10 is kept at the retracted position, and the state of the indicating mechanism is shown in fig. 1 at this time.
The state of the indicator mechanism when the landing gear is in the stowed position is shown in figure 1. When the landing gear needs to be put down, the landing gear support column 1 rotates anticlockwise, the eccentric shaft 2 fixed on the landing gear support column 1 moves anticlockwise along the arc-shaped sliding groove 11 of the fan-shaped movable piece 3, the fan-shaped movable piece 3 is still kept in a state of being clamped by the stop block 4 in the whole process, and the indicating rod 10 is also kept in a retracted position; when the eccentric shaft 2 continues to move to the position shown in fig. 2, the eccentric shaft 2 presses the arc-shaped edge of the first support arm of the stop block 4, the stop block 4 is lifted and is separated from the clamping groove 12 of the fan-shaped movable part 3, the stop block 4 is separated from the rear fan-shaped movable part 3, the fan-shaped movable part 3 rotates anticlockwise under the action of the spring actuating cylinder 8, the indicating rod 10 extends out of the aircraft skin 9 under the action of the spring actuating cylinder 8, and the state of the indicating mechanism is shown in fig. 3.
Claims (4)
1. The position indicating mechanism for airplane landing gear includes a guide unit linked to the landing gear support and an indicator driven by the guide unit, and features that the guide unit includes a sector moving part coaxial with the landing gear support, an arc chute with a notch, an eccentric shaft fixed to the landing gear support and embedded in the arc chute to link the sector moving part with the landing gear support, a Y-shaped stop block with middle part hinged to the airplane body and two support arms connected to the front end of the stop block, the first support arm with arc edge and the second end of the stop block being planar, and the stop block with the other end connected via a tension spring to the airplane body.
2. An aircraft landing gear position indicating mechanism according to claim 1, wherein an arc-shaped slide rail is arranged below the arc-shaped slide groove of the fan-shaped movable member, the stop block is attached to the arc-shaped slide rail, and a clamping groove is formed at the right end of the arc-shaped slide rail.
3. An aircraft landing gear position indicating method, characterized by comprising the following: 1) The lower end of the spring actuating cylinder is connected with the lower end of the indicating rod, the lower end of the indicating rod is connected with the spring actuating cylinder, and the indicating device can move up and down by the spring actuating cylinder which is connected with the spring actuating cylinder; 2) When the undercarriage is folded, an eccentric shaft on an undercarriage strut is located at the left end of the arc-shaped sliding groove of the fan-shaped moving part, a second support arm of the stop block is clamped in a clamping groove at the right end of the arc-shaped sliding groove, the steel cable traction spring actuating cylinder drives the indicating rod to retract into the outer skin of the airplane, when the undercarriage is put down, the eccentric shaft on the undercarriage strut moves towards the right end along the arc-shaped sliding groove of the fan-shaped moving part, when the eccentric shaft meets a first support arm of the stop block, the first support arm is lifted along the arc-shaped edge of the first support arm, the second support arm is further driven to be separated from the clamping groove, the limit of the stop block on the fan-shaped moving part is relieved, the spring actuating cylinder ejects the indicating rod out of the outer skin of the airplane to indicate that the undercarriage is put down, and meanwhile, the spring actuating cylinder drives the steel cable traction fan-shaped moving part to reset.
4. An aircraft landing gear position indicating method according to claim 3, wherein an arc-shaped slide rail is arranged below the arc-shaped slide groove of the fan-shaped movable part, the stop block is attached to the arc-shaped slide rail, and a clamping groove is formed at the right end of the arc-shaped slide rail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910761948.1A CN110550191B (en) | 2019-08-16 | 2019-08-16 | Aircraft landing gear position indicating mechanism and indicating method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910761948.1A CN110550191B (en) | 2019-08-16 | 2019-08-16 | Aircraft landing gear position indicating mechanism and indicating method |
Publications (2)
| Publication Number | Publication Date |
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| CN110550191A CN110550191A (en) | 2019-12-10 |
| CN110550191B true CN110550191B (en) | 2022-11-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910761948.1A Active CN110550191B (en) | 2019-08-16 | 2019-08-16 | Aircraft landing gear position indicating mechanism and indicating method |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112623204B (en) * | 2021-02-18 | 2023-03-10 | 江西洪都航空工业集团有限责任公司 | Undercarriage mechanism of going back to well |
| CN113562167B (en) * | 2021-08-07 | 2024-06-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Multi-position monitoring device for retraction of undercarriage |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB104050A (en) * | 1916-03-20 | 1917-02-22 | Douglas Tweedie Smith | Improved Automatic Safety Device and Indicator to Minimise Accidents to Flying Machines on Grounding. |
| DE645860C (en) * | 1935-05-25 | 1937-06-07 | Pioneer Instr Company Inc | Air speed indicator with a scale for displaying the air speed over the operating range of the display device for aircraft equipped with retractable landing gear |
| US7621481B2 (en) * | 2004-09-03 | 2009-11-24 | Lockheed-Martin Corporation | Decoupled steering/planing air vehicle nose landing gear |
| FR2887516B1 (en) * | 2005-06-27 | 2008-10-03 | Messier Bugatti Sa | DISTRIBUTED ARCHITECTURE OF AIRCRAFT AIRCRAFT MANAGEMENT SYSTEM |
| CN204587304U (en) * | 2015-04-23 | 2015-08-26 | 零度智控（北京）智能科技有限公司 | Unmanned vehicle can folding and unfolding take-off and landing device |
| CN205418077U (en) * | 2016-01-13 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Maintain the body that locks of undercarriage down lock |
| FR3064596A1 (en) * | 2017-03-31 | 2018-10-05 | Airbus Operations | FRONT LANDING TRAIN OF REDUCED HEIGHT AND AIRCRAFT, IN PARTICULAR FLYING WING, EQUIPPED WITH SUCH A FRONT TRAIN |
| CN107878734B (en) * | 2017-11-10 | 2020-10-09 | 中国航空工业集团公司西安飞机设计研究所 | Double-channel steel cable mechanism and aircraft landing gear cabin door with same |
| CN108839790B (en) * | 2018-06-19 | 2020-04-10 | 中航飞机起落架有限责任公司 | Folding type retractable structure of undercarriage and retractable method thereof |
| CN109319093B (en) * | 2018-11-06 | 2021-08-20 | 深圳市富裕泰贸易有限公司 | Unmanned aerial vehicle |
| CN109515697A (en) * | 2018-12-04 | 2019-03-26 | 四川凌峰航空液压机械有限公司 | The holder locking apparatus that rises and falls suitable for different motion track |
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| CN110550191A (en) | 2019-12-10 |
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