CN110949688B - Inner circle positioner for aircraft inlet channel - Google Patents
Inner circle positioner for aircraft inlet channel Download PDFInfo
- Publication number
- CN110949688B CN110949688B CN201911244405.9A CN201911244405A CN110949688B CN 110949688 B CN110949688 B CN 110949688B CN 201911244405 A CN201911244405 A CN 201911244405A CN 110949688 B CN110949688 B CN 110949688B
- Authority
- CN
- China
- Prior art keywords
- guide
- guide rod
- positioning block
- inner circle
- frame
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to an inner circle positioner for an aircraft air inlet channel, and belongs to the field of structural design. An aircraft inlet inner circle positioner comprises a rotating shaft structure, a guide rod structure and a positioning block structure, wherein the rotating shaft structure is arranged in the center of the guide structure and can rotate around the central shaft of the guide structure; the guide structure provides frame support for the guide rod structure; the guide rod structure is arranged on the guide structure and can move along the length direction of the guide rod structure under the action of the rotating shaft structure; the positioning block structure is arranged at the end part of the guide rod structure, moves along with the movement of the guide rod structure, and the end surface of the positioning block structure, which is far away from the guide rod structure, is close to the inner circular surface of the air inlet of the airplane. The invention has the following advantages: the positioning quality of the inner circle of the air inlet channel can be improved, the working efficiency is improved, and the positioner is simple and convenient to use and good in operation effect.
Description
Technical Field
The invention relates to an inner circle positioner for an aircraft air inlet channel, and belongs to the field of structural design.
Background
The air inlet channel is used as an independent component of the airplane, and in the process of an assembly process, the accurate positioning of the air inlet channel is one of important factors for judging the performance of the airplane. Because the manufacturing process of the air inlet is complex, parts often have larger manufacturing tolerance, and the traditional air inlet inner circle positioner generally is a fixed size positioner taking the theoretical diameter of an air inlet inner circle as the benchmark, when the parts have larger tolerance, the problem is solved by adopting a mode of uniformly adding pads around the positioner, and because the manufacturing tolerances generated by different parts are different, the operability of the method and the positioning accuracy are reduced.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides an aircraft inlet inner circle positioner which can accurately position the inner circle of an inlet under the condition that different manufacturing deviations exist in the aircraft inlet.
In order to achieve the purpose, the invention adopts the following technical scheme: an aircraft inlet inner circle positioner comprises a rotating shaft structure, a guide rod structure and a positioning block structure, wherein the rotating shaft structure is arranged in the center of the guide structure and can rotate around the central shaft of the guide structure; the guide structure provides frame support for the guide rod structure; the guide rod structure is arranged on the guide structure and can move along the length direction of the guide rod structure under the action of the rotating shaft structure; the positioning block structure is arranged at the end part of the guide rod structure, moves along with the movement of the guide rod structure, and the end surface of the positioning block structure, which is far away from the guide rod structure, is close to the inner circular surface of the air inlet of the airplane.
Preferably, the rotating shaft structure comprises a main shaft, and a gear is arranged on the circumference of the main shaft; the guide structure comprises a fixed frame and a guide sleeve, the fixed frame comprises an inner frame and an outer frame which are connected together and are concentric, and the guide sleeve is symmetrically arranged on the inner frame and the outer frame; the guide rod structure comprises a guide rod, a polished rod part on the guide rod is arranged in the guide sleeve, and a rack on the guide rod is meshed with a gear on the main shaft; the positioning block structure comprises a positioning block arranged at the end part of the polished rod part, and the positioning block is used for contacting with the inner circular surface of the air inlet channel of the airplane.
Preferably, the fixed frame is a circular frame.
Preferably, the guide sleeves comprise double guide sleeves and single guide sleeves, the double guide sleeves are symmetrically arranged on the inner frame, and the single guide sleeves are symmetrically arranged on the outer frame and are opposite to the double guide sleeves; the rack part on the guide rod is limited between the opposite double guide sleeves, the polished rod part is arranged in the single guide sleeve, and the end part of the polished rod part is connected with the fixed positioning block.
Preferably, the number of the double guide sleeves and the number of the single guide sleeves are four, and the double guide sleeves and the single guide sleeves are uniformly distributed on the inner frame and the outer frame respectively.
Preferably, the side surface of the positioning block, which is in contact with the inner circular surface of the aircraft inlet, is arc-shaped.
Preferably, a rubber protective layer is arranged on the side face, in contact with the inner circular surface of the airplane air inlet, of the positioning block.
Preferably, a handle is provided at an end of the main shaft for rotating the main shaft.
The working principle is as follows: when using this locator location aircraft intake duct, at first twist grip rotates the main shaft to drive four guide arms along guide structure simultaneous movement, remove four quadrant positions to the circle in the intake duct with four locating pieces, and have the same amount of movement, the location demand when can not only satisfying the circle different diameters in the intake duct also can guarantee the central point of the circle in the intake duct and put.
Compared with the prior art, the invention has the following advantages: the positioning quality of the inner circle of the air inlet channel can be improved, the working efficiency is improved, and the positioner is simple and convenient to use and good in operation effect.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a side view of an embodiment of the present invention;
FIG. 3 is a schematic view of the structure of the rotating shaft in FIG. 1;
FIG. 4 is a schematic view of the guide structure of FIG. 1;
FIG. 5 is a schematic view of the guide bar of FIG. 1;
FIG. 6 is a schematic view of the positioning block of FIG. 1;
in the figure, 1, a rotating shaft structure; 2. a guide structure; 3. a guide bar structure; 4. a positioning block structure; 5. an aircraft inlet; 1-1, a handle; 1-2, a main shaft; 1-3, gear part; 1-4, gear part; 2-1, fixing the frame; 2-2, double guide sleeves; 2-3, a single guide sleeve; 3-1, gear part; 3-2, a polish rod part; 4-1 and a rubber protective layer.
Detailed Description
The invention is described in further detail below with reference to the accompanying figures 1-6: an inner circle positioner of an aircraft inlet is shown in figures 1-2 and comprises a rotating shaft structure 1, a guide structure 2, a guide rod structure 3 and a positioning block structure 4, and the inner circle positioner is used for positioning an inner circle of an aircraft inlet 5. The rotating shaft structure 1 is arranged in the center of the guide structure 2 and can rotate around the central shaft thereof; the guide structure 2 provides a frame support for the guide bar structure 3; the guide rod structure 3 is arranged on the guide structure 2 and can move along the length direction of the guide rod structure under the action of the rotating shaft structure 1; the positioning block structure 4 is mounted at the end of the guide rod structure 3, and moves along with the movement of the guide rod structure 3, and the end surface of the positioning block structure, which is far away from the guide rod structure 3, abuts against the inner circular surface of the aircraft air inlet 5.
As shown in fig. 3, the rotating shaft structure 1 comprises a handle 1-1, a main shaft 1-2, a gear part 1-3 and a gear part 1-4; the handle 1-1 is fixedly arranged at the end part of the main shaft 1-2 and is used as a handle for a worker to rotate the main shaft 1-2; the main shaft 1-2 is arranged in the center of the guide structure 2 and can rotate around the central shaft thereof; gear parts 1-3 and 1-4 are arranged around the circumference of the main shaft 1-2.
As shown in fig. 4, the guide structure 2 includes a fixed frame 2-1, a double guide bush 2-2 and a single guide bush 2-3; the fixed frame 2-1 is a cylindrical frame and comprises an external large circular outer frame and an internal small circular inner frame, the outer frame and the inner frame are fixedly connected through a connecting rod, 4 single guide sleeves 2-3 are uniformly arranged on the circumference of one end of the outer frame, 4 double guide sleeves 2-2 are uniformly arranged on the circumference of one end of the inner frame, and the positions of the single guide sleeves 2-3 and the double guide sleeves 2-2 are opposite; the main shaft 1-2 is installed at the center of the inner frame.
As shown in fig. 5, the guide rod structures 3 are four, and include a gear portion 3-1 and a polish rod portion 3-2; the gear part 3-1 is respectively meshed with the gear part 1-3 or the gear part 1-4 and is limited between the double guide sleeves 2-2 which are oppositely arranged, and the end part of the polished rod part 3-2 passes through the single guide sleeve 2-3 to be connected with the positioning block structure 4; the guide rod structures 3 are arranged on two sides of the main shaft 1-2 relatively, namely the guide rod structures are positioned at the upper, lower, left and right positions of the frame structure.
As shown in fig. 6, the positioning block structure 4 includes a positioning block, and a rubber protective layer 4-1 is disposed on an end surface of the positioning block close to the inner circular surface of the aircraft inlet 5 to prevent the inner circular surface of the aircraft inlet from being damaged; for better positioning of the aircraft air inlet 5, the surface of the positioning block structure in contact with it is designed as an arc.
The principle is as follows: the gear parts 1-3 and 1-4 in the rotating shaft structure 1 and the gear parts 3-1 in the guide rod structure 3 (four in all) form transmission; a fixed frame 2-1 in the guide structure 2 connects and fixes double guide sleeves 2-2 (four in all) and single guide sleeves 2-3 (four in all) through a circular frame and a connecting rod; a light rod part 3-2 in the guide rod structure 3 is connected with a double guide sleeve 2-2 and a single guide sleeve 2-3 through a hole shaft; the rubber protective layer 4-1 can prevent the positioning block structure 4 from damaging the inner circular surface of the air inlet channel 5. In the actual operation process, when the positioner is used for positioning the aircraft inlet 5, the main shaft 1-2 is rotated by rotating the handle 1-1 at first, so that the four guide rod structures 3 are driven to move simultaneously along the guide structure 2, the four positioning block structures 4 are moved to the four quadrant positions of the circle in the aircraft inlet, and the four quadrant positions have the same movement amount, so that the positioning requirements of the circle in the aircraft inlet when the circle is different in diameter can be met, and the central position of the circle in the inlet can be ensured. Thus, the positioning work of the inner circle of the air inlet channel of the airplane is completed.
The above embodiments are merely further descriptions of the present invention and are not to be construed as limiting the present invention. The guide structure, the guide rod structure and the positioning block structure can be set according to actual needs. Any extensions or modifications of the present invention that can be made by one of ordinary skill in the art without departing from the principle of the present invention are within the scope of the present invention.
Claims (7)
1. The utility model provides an interior round locator of aircraft intake duct which characterized in that: the guide device comprises a rotating shaft structure, a guide rod structure and a positioning block structure, wherein the rotating shaft structure is arranged in the center of the guide structure and rotates around the central shaft of the guide structure; the guide structure provides frame support for the guide rod structure; the guide rod structure is arranged on the guide structure and moves along the length direction of the guide rod structure under the action of the rotating shaft structure; the positioning block structure is arranged at the end part of the guide rod structure, moves along with the movement of the guide rod structure, and the end surface of the positioning block structure, which is far away from the guide rod structure, is close to the inner circle surface of the air inlet of the airplane; the rotating shaft structure comprises a main shaft, and a gear is arranged on the circumference of the main shaft; the guide structure comprises a fixed frame and a guide sleeve, the fixed frame comprises an inner frame and an outer frame which are connected together and are concentric, and the guide sleeve is symmetrically arranged on the inner frame and the outer frame; the guide rod structure comprises a guide rod, a polished rod part on the guide rod is arranged in the guide sleeve, and a rack on the guide rod is meshed with a gear on the main shaft; the guide sleeves comprise double guide sleeves and single guide sleeves, the double guide sleeves are symmetrically arranged on the inner frame, and the single guide sleeves are symmetrically arranged on the outer frame and are opposite to the double guide sleeves; the rack part on the guide rod is limited between the opposite double guide sleeves, the polished rod part is arranged in the single guide sleeve, and the end part of the polished rod part is connected with the fixed positioning block.
2. The aircraft inlet duct inner circle positioner of claim 1, wherein: the positioning block structure comprises a positioning block arranged at the end part of the polished rod part, and the positioning block is used for contacting with the inner circular surface of the air inlet channel of the airplane.
3. The aircraft inlet duct inner circle positioner of claim 2, wherein: the fixed frame is a circular frame.
4. The aircraft inlet duct inner circle positioner of claim 1, wherein: the number of the double guide sleeves and the number of the single guide sleeves are four, and the double guide sleeves and the single guide sleeves are uniformly distributed on the inner frame and the outer frame respectively.
5. The aircraft inlet duct inner circle positioner of claim 2, wherein: the side surface of the positioning block, which is contacted with the inner circle surface of the air inlet channel of the airplane, is arc-shaped.
6. The aircraft inlet inner circle positioner of claim 2 or 5, wherein: and a rubber protective layer is arranged on the side surface of the positioning block, which is in contact with the inner circle surface of the aircraft inlet.
7. The aircraft inlet duct inner circle positioner of claim 2, wherein: a handle is arranged at the end part of the main shaft and used for rotating the main shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911244405.9A CN110949688B (en) | 2019-12-06 | 2019-12-06 | Inner circle positioner for aircraft inlet channel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911244405.9A CN110949688B (en) | 2019-12-06 | 2019-12-06 | Inner circle positioner for aircraft inlet channel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110949688A CN110949688A (en) | 2020-04-03 |
| CN110949688B true CN110949688B (en) | 2022-03-18 |
Family
ID=69980156
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911244405.9A Active CN110949688B (en) | 2019-12-06 | 2019-12-06 | Inner circle positioner for aircraft inlet channel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110949688B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111412809B (en) * | 2020-04-22 | 2021-11-26 | 芜湖职业技术学院 | Auto-parts examines utensil |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102320027A (en) * | 2011-09-21 | 2012-01-18 | 浙江工业大学 | Circle automatic polishing machine in the long pipeline |
| CN205593454U (en) * | 2016-04-29 | 2016-09-21 | 于江伟 | Circle center positioner |
| CN206797775U (en) * | 2017-04-18 | 2017-12-26 | 成都飞机工业（集团）有限责任公司 | A kind of device for airplane intake inspection |
| CN207516032U (en) * | 2017-11-30 | 2018-06-19 | 成都飞机工业（集团）有限责任公司 | A kind of detection device for airplane intake and engine |
| CN209176936U (en) * | 2018-10-14 | 2019-07-30 | 天津宜捷海特通用航空服务有限公司 | A kind of device for airplane intake inspection |
| EP3561388A1 (en) * | 2018-04-23 | 2019-10-30 | Honeywell International Inc. | System and method for monitoring for sand plugging in gas turbine engines |
-
2019
- 2019-12-06 CN CN201911244405.9A patent/CN110949688B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102320027A (en) * | 2011-09-21 | 2012-01-18 | 浙江工业大学 | Circle automatic polishing machine in the long pipeline |
| CN205593454U (en) * | 2016-04-29 | 2016-09-21 | 于江伟 | Circle center positioner |
| CN206797775U (en) * | 2017-04-18 | 2017-12-26 | 成都飞机工业（集团）有限责任公司 | A kind of device for airplane intake inspection |
| CN207516032U (en) * | 2017-11-30 | 2018-06-19 | 成都飞机工业（集团）有限责任公司 | A kind of detection device for airplane intake and engine |
| EP3561388A1 (en) * | 2018-04-23 | 2019-10-30 | Honeywell International Inc. | System and method for monitoring for sand plugging in gas turbine engines |
| CN209176936U (en) * | 2018-10-14 | 2019-07-30 | 天津宜捷海特通用航空服务有限公司 | A kind of device for airplane intake inspection |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110949688A (en) | 2020-04-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2021109602A1 (en) | Variable-diameter bearing clamp | |
| CN109129177B (en) | A kind of wheeled end burnishing device of public affairs rotation | |
| CN203076872U (en) | Lining press-mounting machine | |
| CN110949688B (en) | Inner circle positioner for aircraft inlet channel | |
| CN204397579U (en) | A kind of centrifugal rust removing device for steel tube | |
| CN201350582Y (en) | Chamfering hob processing device of round glass sheets | |
| CN209407466U (en) | It is a kind of for producing the internal expanding fixture of motor housing | |
| CN102689193B (en) | Automatically determine crank shaft angle to universal positioning device | |
| CN213576081U (en) | Petrochemical industry pipeline flange structure of quick directional connection | |
| CN206206531U (en) | A kind of drive lacking transmission device based on flange transmission | |
| CN215147463U (en) | Nitrogen spring concentricity device | |
| CN210074982U (en) | Thrust limit structure of transmission shaft of mechanical press | |
| CN220029789U (en) | Product clamping device | |
| CN220508002U (en) | Roundness measuring device for water pump shaft connecting bearing | |
| CN109592314A (en) | A kind of precision indexing disk-transporting device | |
| CN211121903U (en) | Agricultural machinery roller durability test positioning device | |
| CN219284676U (en) | Automobile side protection detection device | |
| CN216246459U (en) | Portable probe installation tool | |
| CN207386894U (en) | Clamping device for automatic single-end wire tube row welding machine | |
| CN208945611U (en) | A kind of pump housing surrounding station clamp | |
| CN221038498U (en) | Bearing bolt torque performance detection device | |
| CN221185800U (en) | Grinding clamp for deep groove ball bearing ring | |
| CN215172080U (en) | Convenient driving shaft assembling structure who dismantles | |
| CN219520257U (en) | Bending tool for manufacturing bent pipe | |
| CN216730497U (en) | A gear rapid Assembly device for machining |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |