CN111071430B - Switching structure and rudder of composite material rudder of high-speed aircraft - Google Patents
Switching structure and rudder of composite material rudder of high-speed aircraft Download PDFInfo
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- CN111071430B CN111071430B CN201911372935.1A CN201911372935A CN111071430B CN 111071430 B CN111071430 B CN 111071430B CN 201911372935 A CN201911372935 A CN 201911372935A CN 111071430 B CN111071430 B CN 111071430B
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- rudder
- sleeve
- cavity
- metal adapter
- rudder shaft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention discloses a switching structure of a composite material rudder of a high-speed aircraft and the rudder, wherein the switching structure comprises a metal switching cylinder, a plug connector and a protective sleeve, the top end of the metal switching cylinder is provided with an accommodating cavity for accommodating a rudder shaft of the rudder, and the bottom end of the metal switching cylinder is matched with an installation groove at the rear part of a vertical stabilizing part of the aircraft and is assembled in the installation groove; the plug connector is inserted into the metal adapter cylinder and is used for fixing the rudder shaft in the accommodating cavity; the top of a metal switching section of thick bamboo is located to the lag cover to be used for protecting the rudder axle and the joint position of a metal switching section of thick bamboo, the joint position is the rudder axle and inserts the overall structure of holding the cavity. The rudder comprises a switching structure and a rudder body, a rudder shaft is arranged on one side of the rudder body, one end of the rudder shaft is accommodated in the accommodating cavity, and the plug connector is inserted in the metal switching cylinder and the rudder shaft; and the protective sleeve is sleeved on the joint part of the metal adapter sleeve and the rudder shaft.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a composite material rudder switching structure of a high-speed aircraft and a rudder.
Background
In order to improve range and reduce energy consumption, high-speed aircrafts are increasingly widely made of composite materials. The rudder is an important part for controlling the attitude of the high-speed aircraft, is arranged at the tail part of the aircraft, is vertical to the horizontal plane, and is used for regulating the left or right flight of the aircraft. Because the rudder bears larger load, higher heat flow and has smaller rotational inertia, the composite material rudder generally selects composite materials such as carbon/silicon carbide, carbon, quartz ceramic and the like with good mechanical property, low density, high temperature resistance and ablation resistance.
The existing composite rudder is installed at the tail of the airplane in the following way: the rudder shaft of the rudder is threaded, and then the rudder shaft is in threaded connection with the mounting groove at the rear part of the vertical stabilizing part of the aircraft. However, due to the limitation of machining performance, the rudder made of the composite material has low machining precision of threads on the surface of the rudder shaft and poor integrity of the threads, so that the composite material rudder is difficult to connect with the mounting groove in the rear part of the vertical stabilizing part of the aircraft, and the connection reliability is poor.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a composite material rudder switching structure of a high-speed aircraft and a rudder.
In order to achieve the above purposes, the technical scheme adopted by the invention is as follows:
a transition structure for a composite rudder of a high speed aircraft, comprising:
the top end of the metal adapter cylinder is provided with an accommodating cavity for accommodating a rudder shaft of the rudder, and the bottom end of the metal adapter cylinder is matched with the mounting groove at the rear part of the vertical stable part of the aircraft and is used for being assembled in the mounting groove;
the plug connector is inserted into the metal adapter cylinder and used for fixing the rudder shaft in the accommodating cavity;
and the protecting sleeve is sleeved at the top end of the metal switching cylinder and is used for protecting the joint part of the rudder shaft and the metal switching cylinder.
On the basis of the technical scheme, the vertical section of the inner cavity of the protective sleeve is in a convex shape, the inner cavity comprises a first sleeve cavity and a second sleeve cavity which are arranged from top to bottom and communicated with each other, the first sleeve cavity and the second sleeve cavity form a step, the inner diameter of the first sleeve cavity is equal to that of the accommodating cavity, the inner diameter of the second sleeve cavity is equal to that of the metal transfer cylinder, and the top end of the metal transfer cylinder is abutted to the step.
On the basis of the technical scheme, the outer surface of the metal adapter cylinder is outwards and convexly arranged along the circumferential direction to form a bearing table, and the bottom end of the second sleeve cavity is pressed on the bearing table.
On the basis of the technical scheme, a threaded hole penetrating through the metal adapter cylinder is formed in the metal adapter cylinder and is positioned above the bearing table; two sides of the bottom end of the protective sleeve are provided with operation ports corresponding to the threaded holes; the plug connector comprises at least one expansion bolt which is in threaded connection with the threaded hole.
On the basis of the technical scheme, the plug connector comprises two expansion bolts, and the two expansion bolts are respectively screwed at two ends of the threaded hole.
The invention also provides a composite rudder for a high-speed aircraft, comprising:
the above-mentioned switching structure;
a rudder shaft is arranged on one side of the rudder, one end of the rudder shaft is accommodated in the accommodating cavity, and the plug connector is inserted in the metal adapter cylinder and the rudder shaft; and the protective sleeve is sleeved on the joint part of the metal adapter sleeve and the rudder shaft.
On the basis of the technical scheme, the vertical cross section of the inner cavity of the protective sleeve is in a convex shape, the inner cavity comprises a first sleeve cavity and a second sleeve cavity which are arranged from top to bottom and communicated with each other, the first sleeve cavity and the second sleeve cavity form a step, the inner diameter of the first sleeve cavity is equal to that of the accommodating cavity, the inner diameter of the second sleeve cavity is equal to that of the metal transfer cylinder, the outer surface of the metal transfer cylinder is outwards convexly arranged along the circumferential direction to form a bearing table, and the bottom end of the second sleeve cavity is pressed on the bearing table.
On the basis of the technical scheme, a threaded hole penetrating through the metal adapter cylinder is formed in the metal adapter cylinder, a mounting hole matched with the threaded hole is formed in the rudder shaft, and the threaded hole is located above the bearing platform; two sides of the bottom end of the protective sleeve are provided with operation ports corresponding to the threaded holes; the plug connector comprises at least one expansion bolt which is in threaded connection with the threaded hole and the mounting hole.
On the basis of the technical scheme, the inner wall of the mounting hole is provided with an expansion sleeve; the plug connector comprises two expansion bolts, and one ends of the two expansion bolts extend into the expansion sleeve and are abutted to the expansion sleeve.
Compared with the prior art, the invention has the advantages that:
the metal adapter tube of the adapter structure of the composite material rudder of the high-speed aircraft adopts heat-resistant steel, can machine the surface of the metal adapter tube, has high precision of the machined thread, and realizes reliable connection with the mounting groove at the rear part of the vertical stable part of the aircraft. The plug connector fixes the rudder shaft in the holding cavity of a metal switching section of thick bamboo, realizes being connected of rudder shaft and a metal switching section of thick bamboo, and the lag is used for preventing the rudder shaft when receiving the impact force of high-pressure draught, and the looseness and the destruction of rudder shaft and the combination position of a metal switching section of thick bamboo. The stable and reliable connection between the rudder shaft of the rudder and the rear part of the vertical stabilizing part of the aircraft is realized.
Drawings
FIG. 1 is a schematic structural diagram of a metal adapter in an embodiment of the present invention;
FIG. 2 is a view taken along line A-A of FIG. 1;
FIG. 3 is a schematic structural diagram of a protective cover according to an embodiment of the present invention;
FIG. 4 is a view taken along line A-A of FIG. 3;
FIG. 5 is a schematic view of the construction of the connector;
FIG. 6 is a top view of FIG. 5;
FIG. 7 is a schematic structural view of a composite rudder for a high speed aircraft according to an embodiment of the present invention;
FIG. 8 is a view in the direction A-A of FIG. 7;
FIG. 9 is a view in the direction B-B of FIG. 7;
FIG. 10 is a schematic structural view of an expansion sleeve in an embodiment of the present invention;
fig. 11 is a view in the direction of a-a of fig. 10.
In the figure: the device comprises a metal adapter cylinder 1, a containing cavity 10, a bearing table 11, a threaded hole 12, a rudder 2, a rudder shaft 20, a mounting hole 21, a connector 3, a protective sleeve 4, a first sleeve cavity 40, a second sleeve cavity 41, an operation opening 42 and an expansion sleeve 5.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Referring to fig. 1 and 2, an embodiment of the present invention provides a transition structure of a composite rudder of a high-speed aircraft, including a metal transition cylinder 1, a plug connector 3, and a protective sleeve 4, wherein an accommodating cavity 10 for accommodating a rudder shaft 20 of the rudder 2 is disposed at a top end of the metal transition cylinder 1, and a bottom end of the metal transition cylinder is adapted to a mounting groove at a rear portion of a vertical stabilizing portion of the aircraft and is configured to be mounted in the mounting groove; the plug connector 3 is inserted into the metal adapter tube 1 and is used for fixing the rudder shaft 20 in the accommodating cavity 10; the protecting sleeve 4 is sleeved on the top end of the metal adapter tube 1 and used for protecting the joint of the rudder shaft 20 and the metal adapter tube 1, and the joint is a whole structure that the rudder shaft 20 is inserted into the accommodating cavity 10.
The metal adapter cylinder 1 is made of heat-resistant steel, the surface of the metal adapter cylinder 1 can be machined, the machined thread is high in precision, and reliable connection with a mounting groove in the rear portion of a vertical stabilizing portion of an aircraft is achieved. The plug connector 3 fixes the rudder shaft 20 in the accommodating cavity 10 of the metal adapter tube 1, so that the connection between the rudder shaft 20 and the metal adapter tube 1 is realized, and the protective sleeve 4 is used for preventing the looseness and damage of the joint part of the rudder shaft 20 and the metal adapter tube 1 when the rudder shaft 20 is impacted by high-pressure airflow. A stable and reliable connection of the rudder shaft 20 of the rudder 2 to the rear of the vertical stabilizer of the aircraft is achieved.
Referring to fig. 3 and 4, the vertical cross section of the inner cavity of the protective sleeve 4 is in a shape of a Chinese character 'tu', the inner cavity comprises a first sleeve cavity 40 and a second sleeve cavity 41 which are arranged up and down and communicated with each other, the first sleeve cavity 40 and the second sleeve cavity 41 form a step, the projection of the first sleeve cavity 40 on the horizontal plane is located in the projection range of the second sleeve cavity 41 on the horizontal plane, the inner diameter of the first sleeve cavity 40 is equal to the inner diameter of the accommodating cavity 10, the inner diameter of the second sleeve cavity 41 is equal to the outer diameter of the metal adapter sleeve 1, and the top end of the metal adapter sleeve 1 is abutted against the step, so that the protective sleeve 4 is fastened and connected with the metal adapter sleeve 1, and the protective sleeve 4 is prevented from moving left and right.
Preferably, as shown in fig. 2, the outer surface of the metal adapter 1 is protruded outward along the circumferential direction to form a receiving platform 11, and the bottom end of the second sleeve cavity 41 is pressed on the receiving platform 11. Prevent reciprocating of lag 4 to guarantee that lag 4 stable cover is established outside metal switching section of thick bamboo 1.
Referring to fig. 2, 4 and 10, a threaded hole 12 penetrating through the metal adapter tube 1 is formed in the metal adapter tube 1, the threaded hole 12 is located above the bearing platform 11, the bottom end of the rudder shaft 20 abuts against the bottom end of the accommodating cavity 10, and the rudder shaft 20 is prevented from loosening in the accommodating cavity 10, so that the connector clip 3 connecting the rudder shaft 20 and the metal adapter tube 1 is connected to a joint of the rudder shaft 20 and the metal adapter tube 1, and the connector clip 3 is located above the bearing platform 11. The protection sleeve 4 completely protects the joint of the rudder shaft 20 and the metal adapter sleeve 1 (i.e. the whole structure of the rudder shaft 20 inserted into the accommodating cavity 10), so that the bottom end of the protection sleeve 4 is flush with the bottom end of the accommodating cavity 10, and therefore, operation ports 42 corresponding to the threaded holes 12 need to be formed in two sides of the bottom end of the protection sleeve 4, and the insertion of the plug connectors 3 is realized through the operation ports 42; referring to fig. 5 and 6, the plug-in unit 3 includes at least one expansion bolt, which is screwed into the threaded hole 12. Therefore, the protection sleeve 4 is guaranteed to completely protect the joint of the rudder shaft 20 and the metal adapter tube 1, the bottom end of the rudder shaft 20 is also guaranteed to abut against the bottom end of the accommodating cavity 10, and the rudder shaft 20 is prevented from loosening in the accommodating cavity 10.
Preferably, the plug connector 3 comprises two expansion bolts, and the two expansion bolts are respectively screwed at two ends of the threaded hole 12. Because the length of one expansion bolt is not enough and can not penetrate through the whole threaded hole 12, two expansion bolts are arranged, and the stable connection of the rudder shaft 20 and the metal adapter cylinder 1 is realized.
Referring to fig. 7-9, embodiments of the present invention further provide a composite rudder for a high-speed aircraft, which includes the above-mentioned transfer structure and rudder 2; a rudder shaft 20 is arranged on one side of the rudder 2, one end of the rudder shaft 20 is accommodated in the accommodating cavity 10, and the plug connector 3 is inserted in the metal adapter 1 and the rudder shaft 20; and the protective sleeve 4 is sleeved on the joint part of the metal adapter tube 1 and the rudder shaft 20. The rudder shaft 20 is accommodated in the accommodating cavity 10, the rudder shaft 20 is connected with the metal adapter tube 1 through the plug connector 3, and then the bottom end of the metal adapter tube 1 is connected with the mounting groove at the rear part of the vertical stable part of the aircraft, so that the rudder shaft 20 is stably and reliably connected with the rear part of the vertical stable part of the aircraft.
Referring to fig. 8 and 9, the vertical cross section of the inner cavity of the protective sleeve 4 is in a shape of a Chinese character 'tu', the inner cavity comprises a first sleeve cavity 40 and a second sleeve cavity 41 which are arranged up and down and communicated with each other, the first sleeve cavity 40 and the second sleeve cavity 41 form a step, the projection of the first sleeve cavity 40 on the horizontal plane is located in the projection range of the second sleeve cavity 41 on the horizontal plane, the inner diameter of the first sleeve cavity 40 is equal to the inner diameter of the accommodating cavity 10, the inner diameter of the second sleeve cavity 41 is equal to the outer diameter of the metal adapter sleeve 1, and the top end of the metal adapter sleeve 1 is abutted against the step, so that the protective sleeve 4 is fastened and connected with the metal adapter sleeve 1, and the protective sleeve 4 is prevented from moving left and right.
Referring to fig. 9, the outer surface of the metal adapter tube 1 is protruded outward along the circumferential direction to form a receiving platform 11, and the bottom end of the second sleeve cavity 41 is pressed on the receiving platform 11. Prevent reciprocating of lag 4 to guarantee that lag 4 stable cover is established outside metal switching section of thick bamboo 1.
Referring to fig. 8 and 9, a threaded hole 12 penetrating through the metal adapter tube 1 is formed in the metal adapter tube 1, a mounting hole 21 adapted to the threaded hole 12 is formed in the rudder shaft 20, and the threaded hole 12 is located above the bearing table 11. The bottom end of the rudder shaft 20 abuts against the bottom end of the accommodating cavity 10, so that the rudder shaft 20 is prevented from loosening in the accommodating cavity 10, and the threaded hole 12 is located above the bearing platform 11; the two sides of the bottom end of the protective sleeve 4 are provided with operation ports 42 corresponding to the threaded holes 12, and since the protective sleeve 4 completely protects the joint part of the rudder shaft 20 and the metal adapter sleeve 1 (i.e. the whole structure of the rudder shaft 20 inserted into the accommodating cavity 10), the bottom end of the protective sleeve 4 is flush with the bottom end of the accommodating cavity 10, so the two sides of the bottom end of the protective sleeve 4 are provided with the operation ports 42 corresponding to the threaded holes 12, and the insertion of the plug connector 3 is realized through the operation ports 42; the plug connector 3 comprises at least one expansion bolt which is screwed in the threaded hole 12 and the mounting hole 21 to realize the connection of the rudder shaft 20 and the metal adapter cylinder 1.
Preferably, as shown in fig. 10 and 11, the inner wall of the mounting hole 21 is provided with an expansion sleeve 5, and the plug connector 3 includes two expansion bolts, and one end of each of the two expansion bolts extends into the expansion sleeve 5 and abuts against the expansion sleeve 5. The expansion sleeve 5 is used for realizing the stable connection of the two expansion bolts and preventing the loosening of the two expansion bolts.
The present invention is not limited to the above-described embodiments, and it will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements are also considered to be within the scope of the present invention. Those not described in detail in this specification are within the skill of the art.
Claims (5)
1. A transition structure for a composite rudder of a high-speed aircraft, comprising:
the top end of the metal adapter cylinder (1) is provided with an accommodating cavity (10) for accommodating a rudder shaft (20) of the rudder (2), and the bottom end of the metal adapter cylinder is matched with an installation groove at the rear part of the vertical stable part of the aircraft and is assembled in the installation groove;
the plug connector (3) is inserted into the metal adapter cylinder (1) and is used for fixing the rudder shaft (20) in the accommodating cavity (10);
the protecting sleeve (4) is sleeved at the top end of the metal adapter tube (1) and used for protecting the joint of the rudder shaft (20) and the metal adapter tube (1);
the rudder shaft (20) is cubic, and the accommodating cavity (10) is cubic;
the vertical section of the inner cavity of the protective sleeve (4) is in a convex shape, the inner cavity comprises a first sleeve cavity (40) and a second sleeve cavity (41) which are arranged up and down and communicated with each other, the first sleeve cavity (40) and the second sleeve cavity (41) form a step, the inner diameter of the first sleeve cavity (40) is equal to that of the accommodating cavity (10), the inner diameter of the second sleeve cavity (41) is equal to that of the metal adapter tube (1), and the top end of the metal adapter tube (1) is abutted against the step;
the outer surface of the metal adapter cylinder (1) is outwards and convexly arranged along the circumferential direction to form a bearing table (11), and the bottom end of the second sleeve cavity (41) is pressed on the bearing table (11);
a threaded hole (12) penetrating through the metal adapter cylinder (1) is formed in the metal adapter cylinder (1), and the threaded hole (12) is located above the bearing table (11); two sides of the bottom end of the protective sleeve (4) are provided with operation ports (42) corresponding to the threaded holes (12); the plug connector (3) comprises at least one expansion bolt which is screwed in the threaded hole (12).
2. A changeover structure according to claim 1, wherein said plug-in unit (3) comprises two expansion bolts which are screwed to both ends of said threaded hole (12), respectively.
3. A composite rudder for a high speed aircraft, comprising:
the transition structure of claim 1;
a rudder (2), one side of which is provided with a rudder shaft (20), one end of the rudder shaft (20) is accommodated in the accommodating cavity (10), and the plug connector (3) is inserted in the metal adapter cylinder (1) and the rudder shaft (20); and the protective sleeve (4) is sleeved on the joint of the metal adapter tube (1) and the rudder shaft (20).
4. The composite material rudder according to claim 3, wherein the rudder shaft (20) is provided with a mounting hole (21) adapted to the threaded hole (12), and the expansion bolt is screwed into the threaded hole (12) and the mounting hole (21).
5. A composite rudder according to claim 4 characterised in that the inner wall of the mounting hole (21) is provided with an expansion sleeve (5); the plug connector (3) comprises two expansion bolts, and one ends of the two expansion bolts extend into the expansion sleeve (5) and are abutted against the expansion sleeve (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911372935.1A CN111071430B (en) | 2019-12-26 | 2019-12-26 | Switching structure and rudder of composite material rudder of high-speed aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911372935.1A CN111071430B (en) | 2019-12-26 | 2019-12-26 | Switching structure and rudder of composite material rudder of high-speed aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111071430A CN111071430A (en) | 2020-04-28 |
| CN111071430B true CN111071430B (en) | 2021-11-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911372935.1A Active CN111071430B (en) | 2019-12-26 | 2019-12-26 | Switching structure and rudder of composite material rudder of high-speed aircraft |
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| CN (1) | CN111071430B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114030589B (en) * | 2021-10-19 | 2023-07-21 | 湖北航天技术研究院总体设计所 | Light high-efficiency thermal resistance air rudder |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105464164A (en) * | 2015-12-09 | 2016-04-06 | 荣昌精密机械(苏州)有限公司 | Lower steel chisel bushing for breaking hammer |
| CN108340067A (en) * | 2018-03-15 | 2018-07-31 | 吴谦 | It is a kind of that method is connected by the metal of metal-base composites and the bolt of composite material |
| CN108372936A (en) * | 2018-03-02 | 2018-08-07 | 北京星际荣耀空间科技有限公司 | A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely |
| CN108799315A (en) * | 2018-06-08 | 2018-11-13 | 武汉理工大学 | Composite material for vehicle transmission shaft and preparation method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7712993B2 (en) * | 2007-11-30 | 2010-05-11 | The Boeing Company | Double shear joint for bonding in structural applications |
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2019
- 2019-12-26 CN CN201911372935.1A patent/CN111071430B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105464164A (en) * | 2015-12-09 | 2016-04-06 | 荣昌精密机械(苏州)有限公司 | Lower steel chisel bushing for breaking hammer |
| CN108372936A (en) * | 2018-03-02 | 2018-08-07 | 北京星际荣耀空间科技有限公司 | A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely |
| CN108340067A (en) * | 2018-03-15 | 2018-07-31 | 吴谦 | It is a kind of that method is connected by the metal of metal-base composites and the bolt of composite material |
| CN108799315A (en) * | 2018-06-08 | 2018-11-13 | 武汉理工大学 | Composite material for vehicle transmission shaft and preparation method thereof |
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| Publication number | Publication date |
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| CN111071430A (en) | 2020-04-28 |
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