CN112373687B - Large-scale seaplane rudder face suspension structure - Google Patents
Large-scale seaplane rudder face suspension structure Download PDFInfo
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- CN112373687B CN112373687B CN202011289849.7A CN202011289849A CN112373687B CN 112373687 B CN112373687 B CN 112373687B CN 202011289849 A CN202011289849 A CN 202011289849A CN 112373687 B CN112373687 B CN 112373687B
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- joint
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- control surface
- seaplane
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/007—Specific control surfaces therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a seaplane control surface suspension structure, comprising: the device comprises a fixed suspension joint (3), a suspension support arm (4), a transition joint (5), a control surface butt joint (6) and a joint bearing (7); each control surface butt joint (6) is fixedly arranged on a control surface (1) of the seaplane; the fixed suspension joint (3) is fixedly connected to a stabilizing surface (2) of the large-scale seaplane and is rotationally connected with the control surface (1) through a control surface butt joint (6); the first end of the suspension support arm (4) is fixedly connected to the stabilizing surface (2) of the large-scale seaplane, the second end of the suspension support arm (4) is connected with the first end of the transition joint (5) through the joint bearing (7), and the second end of the transition joint (5) is connected with a control surface butt joint (6) through the joint bearing (7). The movement allowance between the control surface suspension structures is increased, and the problems of connector interference and blockage caused by inconsistent deformation between the metal stabilizing surface and the composite control surface are avoided.
Description
Technical Field
The invention relates to a large-scale seaplane control surface suspension structure, in particular to a large-scale seaplane control surface aerodynamic load and hinge line load bearing structure.
Background
The large seaplane rudder surface suspension structure must be able to bear the maximum 36Wg inertial load of the rudder surface along the hinge line in addition to the aerodynamic load of the rudder surface.
The conventional integrated control surface suspension structure is easy to deform greatly under the action of hinge line load, and in addition, the situation that thermal expansion deformation coordination is inconsistent exists between the metal stabilizing surface and the composite control surface, the joint and the peripheral structure are interfered or even blocked, so that the flight safety is seriously influenced.
Disclosure of Invention
The purpose of the invention is: the utility model provides a seaplane rudder face suspension structure, solve and have thermal expansion deformation coordination inconsistent between metal stabilizer and the combined material rudder face, lead to the dead problem of card.
The invention provides a seaplane control surface suspension structure, comprising: the device comprises a fixed suspension joint 3, a suspension support arm 4, a transition joint 5, a control surface butt joint 6 and a joint bearing 7; each control surface butt joint 6 is fixedly arranged on a control surface 1 of the seaplane; wherein the content of the first and second substances,
the fixed suspension joint 3 is fixedly connected to a stabilizing surface 2 of the large seaplane and is rotationally connected with the control surface 1 through the control surface butt joint 6;
the first end of the suspension support arm 4 is fixedly connected to the stabilizing surface 2 of the large-scale seaplane, the second end of the suspension support arm 4 is connected with the first end of the transition joint 5 through a joint bearing 7, and the second end of the transition joint 5 is connected with the control surface butt joint 6 through the joint bearing 7.
Optionally, the transition joint 5 is triangular, two vertex angles of the triangle are connected with the second end of the suspension arm 4, and the remaining vertex angle is connected with the control surface butt joint 6.
Optionally, the method further includes: a first wear-resistant shoulder bushing 8, a second wear-resistant shoulder bushing 9 and a sliding bushing 10;
the second end of the suspension support arm 4 is provided with two double lugs which are respectively connected with two vertex angles of the triangle;
the vertex angle of the triangle is a single lug, the knuckle bearing 7 is sleeved in the single lug, a first wear-resistant shoulder bush 8 and a second wear-resistant shoulder bush 9 are respectively sleeved in two through holes of the two lugs, and a sliding bush 10 is sleeved in the first wear-resistant shoulder bush 8;
the second wear-resistant shoulder bush 9 and the sliding bush 10 are respectively pressed on two sides of the inner ring of the joint bearing 7;
a gap exists between the monaural and the binaural.
Optionally, the second wear-resistant shoulder bushing 9, the knuckle bearing 7 and the sliding bushing 10 are connected by bolts;
the shoulders of the first 8 and second 9 wear-resistant shoulder bushes face the bolt head side of the bolt.
Optionally, the length of the sliding bushing 10 is greater than the length of the first wear shoulder bushing 8.
Optionally, a plurality of suspension arms 4 are respectively disposed on two sides of the fixed suspension joint 3.
Optionally, one end of the fixed suspension joint 3 connected to the control surface butt joint 6 is connected to a first end of a support rod, and a second end of the support rod is fixedly connected to the stabilizing surface 2.
Alternatively, the rotation axes of the joint bearings 7 are parallel.
The invention provides a seaplane control surface suspension structure, which has large structure adjustment movement allowance and can effectively avoid the problems of structure interference and locking caused by the incoordination of thermal expansion deformation between a metal stabilizing surface and a composite material control surface; the sufficient adjustment movement allowance can effectively reduce the assembly difficulty of the butt joint of the sections; the pneumatic load bearing structure and the hinge line load bearing structure are relatively independent, and the pneumatic load bearing structure and the hinge line load bearing structure have definite functions and reliable work.
Drawings
FIG. 1 is a schematic structural view of a seaplane rudder surface suspension structure according to the present invention;
FIG. 2 is an enlarged view of region I of FIG. 1;
FIG. 3 is a top view of FIG. 2;
FIG. 4 is an enlarged sectional view taken along line A-A of FIG. 3;
description of reference numerals:
1-control surface; 2-a stabilizing surface;
3-fixing the suspension joint; 4, hanging a support arm;
5-a transition joint; 6-control surface butt joint;
7-knuckle bearing; 8-a first wear-resistant shoulder bushing;
9-a second wear-resistant shoulder bushing; 10-sliding bush.
Detailed Description
The present invention provides a seaplane control surface suspension structure, which can be used for controlling the sea plane.
Fig. 1 is a schematic structural view of a seaplane control surface suspension structure of the present invention, please refer to fig. 1, the present invention provides a seaplane control surface suspension structure for connection between a control surface 1 and a stabilizer 2; the fixed suspension joint 3 is connected with the control surface 1 through a control surface butt joint 6 and used for bearing the inertial load of the control surface along a hinge line, and the suspension support arm 4 and the transition joint 5 are connected with the control surface butt joint 6 and used for bearing the aerodynamic load of the control surface.
Illustratively, as shown in fig. 2-4, a joint bearing 7 is pressed in the transition joint 5, so that the transition joint 5 and the control surface butt joint 6 can rotate relatively around the joint bearing 7.
Illustratively, a first wear-resistant shoulder bush 8 and a second wear-resistant shoulder bush 9 are sleeved in through holes of two lugs of the control surface butt joint 6, so that lug holes of the control surface butt joint 6 can be protected and repair allowance can be provided.
Illustratively, the first wear-resistant shoulder bushing 8 is internally sleeved with a sliding bushing 10, and the length of the sliding bushing 10 is greater than that of the first wear-resistant shoulder bushing 8. The inner diameters of the second wear-resistant shoulder bush 9 and the sliding bush 10 are consistent, and two end faces of an inner ring of the knuckle bearing 7 are respectively pressed, so that the transition joint 5 and the control surface butt joint 6 are convenient to install when connected.
The bolts pass through the sliding bush 10, the knuckle bearing 7 and the second wear-resistant shoulder bush 9 in this order.
The shoulders of the first 8 and second 9 wear-resistant shoulder bushes face the bolt head side of the bolt.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention.
Claims (6)
1. A seaplane control surface suspension structure comprising: the device comprises a fixed suspension joint (3), a suspension support arm (4), a transition joint (5), a control surface butt joint (6) and a joint bearing (7); each control surface butt joint (6) is fixedly arranged on a control surface (1) of the seaplane; wherein, the first and the second end of the pipe are connected with each other,
the fixed suspension joint (3) is fixedly connected to a stabilizing surface (2) of the large-scale seaplane and is rotatably connected with the control surface (1) through the control surface butt joint (6);
the first end of the suspension support arm (4) is fixedly connected to a stabilizing surface (2) of the large-scale seaplane, the second end of the suspension support arm (4) is connected with the first end of the transition joint (5) through a joint bearing (7), and the second end of the transition joint (5) is connected with one control surface butt joint (6) through the joint bearing (7);
the number of the fixed suspension joints (3) is 1, and a plurality of suspension support arms (4) are respectively arranged on two sides of each fixed suspension joint (3);
one end of the fixed suspension joint (3) connected with the control surface butt joint (6) is connected with a first end of a supporting rod, and a second end of the supporting rod is fixedly connected with the stabilizing surface (2).
2. Rudder surface suspension arrangement for seaplanes according to claim 1, characterised in that the transition joint (5) is triangular, two apex angles of which are connected to the second end of the suspension arm (4) and the remaining one apex angle is connected to the rudder surface butt joint (6).
3. The seaplane control surface suspension structure of claim 2, further comprising: a first wear-resistant shoulder bush (8), a second wear-resistant shoulder bush (9) and a sliding bush (10);
the second end of the suspension support arm (4) is provided with two double lugs which are respectively connected with two vertex angles of the triangle;
the vertex angle of the triangle is a single lug, the knuckle bearing (7) is sleeved in the single lug, a first wear-resistant shoulder bush (8) and a second wear-resistant shoulder bush (9) are respectively sleeved in two through holes of the two lugs, and a sliding bush (10) is sleeved in the first wear-resistant shoulder bush (8);
the second wear-resistant shoulder bush (9) and the sliding bush (10) are respectively pressed on two sides of an inner ring of the joint bearing (7);
a gap exists between the monaural and the binaural.
4. Seaplane rudder surface suspension structure according to claim 3, characterised in that the second wear-resistant shoulder bushing (9), the knuckle bearing (7) and the sliding bushing (10) are connected by means of bolts;
the shoulders of the first wear-resistant shoulder bush (8) and the second wear-resistant shoulder bush (9) face the bolt head side of the bolt.
5. Seaplane rudder surface suspension arrangement according to claim 4, characterised in that the length of the sliding bushing (10) is greater than the length of the first wear-resistant shoulder bushing (8).
6. Seaplane rudder surface suspension according to claim 1, characterised in that the axes of rotation of the joint bearings (7) are parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011289849.7A CN112373687B (en) | 2020-11-17 | 2020-11-17 | Large-scale seaplane rudder face suspension structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011289849.7A CN112373687B (en) | 2020-11-17 | 2020-11-17 | Large-scale seaplane rudder face suspension structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112373687A CN112373687A (en) | 2021-02-19 |
| CN112373687B true CN112373687B (en) | 2022-11-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011289849.7A Active CN112373687B (en) | 2020-11-17 | 2020-11-17 | Large-scale seaplane rudder face suspension structure |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102312930A (en) * | 2010-07-07 | 2012-01-11 | 空中客车西班牙运营有限责任公司 | The elasticity sliding motion joint |
| CN106995051A (en) * | 2015-10-23 | 2017-08-01 | 空中客车运营简化股份公司 | For aircraft suspension type rudder connecting rod and include the aircraft of such rudder connecting rod |
| WO2021062229A1 (en) * | 2019-09-26 | 2021-04-01 | Joby Aero, Inc. | Three-dimensional extension linkage |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9016623B2 (en) * | 2011-11-30 | 2015-04-28 | The Boeing Company | Jam protection and alleviation for control surface linkage mechanisms |
| GB2528231A (en) * | 2014-04-24 | 2016-01-20 | Airbus Operations Ltd | An aircraft with a foldable wing tip device |
| US9840320B2 (en) * | 2014-12-19 | 2017-12-12 | The Boeing Company | Trailing edge device with bell crank mechanism |
| CN207242014U (en) * | 2017-08-19 | 2018-04-17 | 精功（绍兴）复合材料有限公司 | A kind of device connected for unmanned plane rudder face with stabilization |
| CN108082449B (en) * | 2018-03-06 | 2022-06-10 | 中航通飞华南飞机工业有限公司 | Large aircraft control surface suspension structure |
| CN110789708B (en) * | 2019-10-12 | 2023-06-23 | 哈尔滨飞机工业集团有限责任公司 | Rear horizontal tail structure of helicopter with stay bar |
| CN211711048U (en) * | 2019-12-19 | 2020-10-20 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft suspension support arm structure |
-
2020
- 2020-11-17 CN CN202011289849.7A patent/CN112373687B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102312930A (en) * | 2010-07-07 | 2012-01-11 | 空中客车西班牙运营有限责任公司 | The elasticity sliding motion joint |
| CN106995051A (en) * | 2015-10-23 | 2017-08-01 | 空中客车运营简化股份公司 | For aircraft suspension type rudder connecting rod and include the aircraft of such rudder connecting rod |
| WO2021062229A1 (en) * | 2019-09-26 | 2021-04-01 | Joby Aero, Inc. | Three-dimensional extension linkage |
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| Publication number | Publication date |
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| CN112373687A (en) | 2021-02-19 |
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