CN110949677B - Indicating device for airplane heavy landing - Google Patents
Indicating device for airplane heavy landing Download PDFInfo
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- CN110949677B CN110949677B CN201911239712.8A CN201911239712A CN110949677B CN 110949677 B CN110949677 B CN 110949677B CN 201911239712 A CN201911239712 A CN 201911239712A CN 110949677 B CN110949677 B CN 110949677B
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 5
- 238000009434 installation Methods 0.000 claims abstract description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Classifications
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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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- 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
- B64D2045/008—Devices for detecting or indicating hard landing
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Displays For Variable Information Using Movable Means (AREA)
- Mechanical Control Devices (AREA)
Abstract
The invention provides an indicating device for airplane heavy landing, which mainly comprises a rotary disc (3), a pointer (4) and a conversion device, wherein the situation of the impact force of the ground when an airplane lands is measured and displayed by converting the movement distance of a piston rod (8) of an airplane undercarriage into the range of the rotation angle of the pointer (4) on the rotary disc (3). The device simple structure, low in manufacturing cost because of installing on the aircraft undercarriage, installation and operation convenient to use, outfield field crew member rapidly reading device's instruction condition after the aircraft lands to maintain or maintain the operation, guaranteed the attendance rate of aircraft.
Description
Technical Field
The invention belongs to the field of mechanical structure design, and particularly relates to an airplane heavy landing indicating device.
Background
At present, the judgment of the heavy landing of the airplane is mostly based on the calculation and the judgment of flight parameter data, professional theoretical knowledge and experience accumulation are needed, and workers under the outfield condition are difficult to master and apply. Meanwhile, some existing destructive mechanical heavy landing indicating devices need to replace the indicating wires if heavy landing occurs, so that the workload of field ground service is increased, and the heavy landing degree cannot be acquired and judged.
Disclosure of Invention
In order to solve the defects in the prior art, the invention provides the indicating device for the heavy landing of the airplane, which is arranged on the landing gear of the airplane, can record the landing degree of the airplane each time, can meet the requirement that field ground service personnel quickly recover the original state through simple operation and put into reuse, and ensures the attendance rate of the airplane.
In order to solve the technical problem, the indicating device for indicating the heavy landing of the airplane provided by the invention measures and displays the size of the impact force on the ground when the airplane lands by converting the movement distance of the piston rod of the undercarriage of the airplane into the rotation angle range of the pointer on the rotary disc. The device mainly comprises a dial and a pointer, wherein the dial is semicircular and is fixedly connected to a buffering support column of the undercarriage, one end of the pointer is rotatably connected to the circle center of the dial, the other end of the pointer is driven by a piston rod of the undercarriage through a conversion device to rotate on the dial, the corresponding angle range of the dial is indicated and maintained, and manual operation is needed when the original position is recovered.
The dial of the airplane heavy landing indicating device is connected to the landing gear buffer support column through the clamp, and the installation and the position adjustment are facilitated.
The scales of the dial are marked on the semicircular circumferential ring, the dial is divided into two scales along the circumferential direction, namely a normal parking zero position, a normal landing area and a heavy landing area, and the scales are respectively marked after the relation between the compression amount of the piston rod of the aircraft landing frame and the deflection angle of the pointer in the landing process is calculated, so that the scales correspond to the positions and the range of the scales.
The conversion device for connecting the pointer and the piston rod of the landing gear mainly comprises a follow-up block, a stop block and a torsion arm. The dial circle ring is hollowed with a smooth arc sliding groove according to the requirement of an indication range; the follow-up block is assembled in the circular arc sliding groove of the dial, and slides in the circular arc sliding groove to drive the pointer to rotate and point to the corresponding scale; the stop block is assembled in the arc-shaped sliding groove and is rotationally connected with the torque arm, the torque arm rotates to drive the stop block to slide in the sliding groove, the stop block slides to push the follow-up block to slide in the sliding groove, so that the pointer is driven to rotate, and the follow-up block and the pointer have certain retention force after rotating to a certain position (the retention force meets the requirement of manual operation for overcoming the size, and after the airplane finishes rising and falling, a worker reads and records the pointer indication scale range, and then the worker manually restores the original position of the normal parking zero position); the other end of the torque arm is connected with a piston rod of the undercarriage.
In order to solve the problem that the follow-up block and the stop block move smoothly in the arc-shaped sliding groove, the follow-up block and the stop block are assembled in the arc-shaped sliding groove in a clamping mode.
The torque arm adopts two arm structures, adopts the pivot to connect between two arms, fastens after adjusting two arm angles during the installation.
Furthermore, the two arms are respectively connected with the stop block and the piston rod of the aircraft landing gear in a pin shaft connection mode.
The torque arm can adopt a single-arm structure, and the two ends of the single arm are rotatably connected with the stop block and a piston rod of the aircraft landing gear.
Furthermore, the rotating connection mode between the two ends of the single arm of the torsion arm and the check block and the piston rod of the aircraft landing gear is a pin shaft connection mode.
According to the technical scheme, the designed airplane heavy landing indicating device is simple in structure and low in manufacturing cost, is installed on an airplane undercarriage, is convenient to install, operate and use, and can be used for rapidly reading the indicating condition of the device after the airplane lands, and performing maintenance or repair operation after judgment is made according to the indicating condition, and meanwhile, the pointer is manually returned to the original position and then put into use again, so that the attendance rate of the airplane is guaranteed.
Drawings
FIG. 1 is an assembly view of the indicating device for indicating heavy landing of an airplane according to the present invention.
Fig. 2 is a schematic diagram of the dial of the present invention.
In FIGS. 1-2: 1. landing gear buffer strut, 2, clamp, 3, dial, 4, pointer, 5, follow-up block, 6, stop dog, 7, torsion arm, 8, piston rod, 31, heavy landing indication area, 32, normal landing area, 33, normal parking zero position.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to fig. 1 and fig. 2, and it is obvious that the described embodiment is only a specific embodiment of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 and 2, the indicating device for indicating the heavy landing of the airplane comprises a dial 3, a pointer 4, a follow-up block 5, a stop 6, a torsion arm 7 and the like, wherein a heavy landing indicating area 31, a normal landing area 32 and a normal zero parking position 33 are marked on the dial 3.
Wherein, the dial 3 is semicircular, and scales are marked on a semicircular circumferential ring; the circumferential ring of the dial 3 is hollowed with a smooth arc-shaped sliding groove according to the requirement of an indicating range. One end of a pointer 4 is rotatably connected to the circle center of the dial 3, the other end of the pointer is fixed on the follow-up block 5, and the pointer is driven to rotate through external force (the external force can be adjusted through a rotating connecting device, and the pointer generally meets the requirement that manual driving is not difficult). The follow-up block 5 is clamped in the arc-shaped sliding groove, and the follow-up block 5 slides in the sliding groove to drive the pointer 3 to rotate and point to the corresponding scale. The stop block 6 is clamped in the sliding groove and is connected with the torque arm 7 through a pin shaft, the torque arm 7 rotates to drive the stop block 6 to slide in the sliding groove, and the follow-up block 5 is pushed by the sliding of the stop block 6 to slide in the sliding groove together, so that the pointer 3 is driven to rotate.
The torque arm 7 adopts a double-arm structure, the double arms are connected by a rotating shaft, and the torque arm is fixed after the angle is adjusted during installation. The upper end of the dial 3 is connected with a hoop 2 through a bolt, and the airplane heavy landing indicating device and the undercarriage buffer bracket 1 are arranged on the hoop 2. The lower end of the torque arm 7 is connected with a piston rod 8 of the landing gear through a pin shaft.
When the airplane is normally parked, the pointer 4 and the follow-up block 5 are stopped at the normal parking zero position 33 of the dial 3, when the airplane lands, the landing gear is driven by the ground impact force to move the piston rod 8 upwards, the torsion arm 7 is driven to move, linear motion is converted into curvilinear motion through the torsion arm 7, the torsion arm 7 drives the stop block 6 to slide along the sliding groove, the stop block 6 drives the follow-up block 5 to slide along the sliding groove, and the pointer 4 is driven to rotate through the follow-up block 5. When the dial 3 normally lands, the piston rod 8 moves upwards for a distance within a normal range, and the driving stop 6 moves within a sliding groove within a range falling on a normal landing area 32 of the dial 3; when heavy landing, the upward movement distance of the piston rod 8 exceeds the normal range, and the movement range of the driven stop 6 in the sliding groove falls on the heavy landing area 31 of the dial 3. After the follow-up block 5 moves in place and stops, the driving pointer 4 cannot be automatically restored, and the normal parking zero position 33 of the dial 3 needs to be restored in a manual mode, so that the readability of field ground personnel outside the airplane is ensured. And the field ground service personnel judge the landing condition of the airplane through the scale positions of the pointer 4 and the follow-up block 5 and carry out corresponding airplane maintenance and repair work.
Claims (8)
1. An indicating device for indicating heavy landing of an airplane, which displays and obtains heavy landing data by measuring the movement distance of a piston rod of an undercarriage of the airplane under the action of ground impact force, and is characterized in that: the heavy landing indicating device mainly comprises a dial (3) and a pointer (4), wherein the dial (3) is semicircular, the dial (3) is fixedly connected to a landing gear buffer support column (1), one end of the pointer (4) is fixed at the circle center of the dial (3), the other end of the pointer (4) is driven by a piston rod (8) of the landing gear through a conversion device to rotate on the dial (3), the corresponding angle range of the dial (3) is indicated and maintained, and the original position is recovered by manual operation; the conversion device comprises a follow-up block (5), a stop block (6) and a torsion arm (7); the circumference ring of the dial (3) is hollowed with a smooth arc-shaped sliding groove according to the requirement of an indication range; the follow-up block (5) is assembled in the circular arc sliding groove of the dial (3), and the follow-up block (5) slides in the circular arc sliding groove to drive the pointer (4) to rotate and point to the corresponding scale; the stop block (6) is assembled in the arc-shaped sliding groove and is rotationally connected with the torque arm (7), the torque arm (7) rotates to drive the stop block (6) to slide in the sliding groove, and the sliding of the stop block (6) pushes the follow-up block (5) to slide in the sliding groove together, so that the pointer (4) is driven to rotate; the other end of the torque arm (7) is connected with a piston rod (8) of the undercarriage.
2. An indicator device for indicating heavy landing of an aircraft according to claim 1, wherein said dial (3) is fixed to the landing gear strut (1) by means of a clip.
3. An aircraft heavy landing indication device as claimed in claim 1, wherein: the scale of the dial (3) is marked on the semicircular circumferencial circle, the dial (3) is divided into two scales along the circumferencial direction, the two scales are respectively a heavy landing area (31), a normal landing area (32) and a normal parking zero position (33), and after the relationship between the movement distance of a piston rod (8) of the landing gear of the aircraft landing gear and the deflection angle of a pointer is calculated, the scales are respectively marked and correspond to the position and the range of the interval.
4. An aircraft heavy landing indication device as claimed in claim 1, wherein: the follow-up block (5) and the stop block (6) are assembled in the arc-shaped sliding groove in a clamping mode, and the follow-up block (5) and the stop block (6) can smoothly slide in the arc-shaped sliding groove.
5. An aircraft heavy landing indication device as claimed in claim 1, wherein: the torque arm (7) adopts a two-arm structure, the two arms are connected through a rotating shaft, and the two arms are fastened after the angles of the two arms are adjusted during installation.
6. An aircraft heavy landing indication device as claimed in claim 1, wherein: the torque arm (7) adopts a single-arm structure, and two ends of the single arm are rotatably connected with the stop block (6) and a piston rod (8) of the aircraft landing gear.
7. An aircraft heavy landing indicating device as claimed in claim 5, wherein: the rotary connection mode between the two arms of the torque arm (7) and the stop block (6) and the piston rod (8) of the aircraft landing gear is a pin shaft connection mode.
8. An aircraft heavy landing indication device as claimed in claim 6, wherein: the two ends of the torque arm (7) are rotatably connected with the stop block (6) and a piston rod (8) of the aircraft landing gear in a pin shaft connection mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911239712.8A CN110949677B (en) | 2019-12-06 | 2019-12-06 | Indicating device for airplane heavy landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911239712.8A CN110949677B (en) | 2019-12-06 | 2019-12-06 | Indicating device for airplane heavy landing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110949677A CN110949677A (en) | 2020-04-03 |
| CN110949677B true CN110949677B (en) | 2022-12-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911239712.8A Active CN110949677B (en) | 2019-12-06 | 2019-12-06 | Indicating device for airplane heavy landing |
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| CN (1) | CN110949677B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112429253B (en) * | 2020-12-14 | 2022-10-11 | 江西洪都航空工业集团有限责任公司 | Acceleration heavy landing indicator |
| CN114455814B (en) * | 2021-12-31 | 2023-06-09 | 浙江美晶新材料股份有限公司 | Quartz crucible melting device and preparation method |
| CA3197610A1 (en) * | 2022-05-06 | 2023-11-06 | Goodrich Corporation | Temperature compensated shock strut visual health indicator systems and methods |
| US11892052B2 (en) | 2022-05-06 | 2024-02-06 | Goodrich Corporation | Temperature compensated shock strut visual health indicator systems and methods |
| CN115367128A (en) * | 2022-09-15 | 2022-11-22 | 中国科学院工程热物理研究所 | Air-ground signal device for aircraft and using method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2700546A1 (en) * | 2008-10-13 | 2009-04-16 | Messier-Dowty Limited | Load detection in an aircraft landing gear |
| CN105644797A (en) * | 2014-11-14 | 2016-06-08 | 通用电气航空系统有限公司 | Aircraft assembly with load and position indicator |
| CN109606713A (en) * | 2018-12-03 | 2019-04-12 | 江西洪都航空工业集团有限责任公司 | A kind of Purely mechanical lands instruction structure again |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6676075B2 (en) * | 2001-08-30 | 2004-01-13 | The Boeing Company | Airplane hard landing indication system |
| US7274309B2 (en) * | 2005-03-29 | 2007-09-25 | Nance C Kirk | Aircraft landing gear initial touch-down velocity monitor |
| GB201209502D0 (en) * | 2012-05-29 | 2012-07-11 | Airbus Operations Ltd | System, kit and method for indicating the pressure in an aircraft landing gear shock absorber |
-
2019
- 2019-12-06 CN CN201911239712.8A patent/CN110949677B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2700546A1 (en) * | 2008-10-13 | 2009-04-16 | Messier-Dowty Limited | Load detection in an aircraft landing gear |
| CN105644797A (en) * | 2014-11-14 | 2016-06-08 | 通用电气航空系统有限公司 | Aircraft assembly with load and position indicator |
| CN109606713A (en) * | 2018-12-03 | 2019-04-12 | 江西洪都航空工业集团有限责任公司 | A kind of Purely mechanical lands instruction structure again |
Non-Patent Citations (1)
| Title |
|---|
| 民用飞机重着陆响应及诊断研究;舒平等;《中国制造业信息化》;20090831;第38卷(第15期);第68-70,72页 * |
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| CN110949677A (en) | 2020-04-03 |
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