CN112339976A - Aircraft linkage connecting hole blanking cover structure - Google Patents
Aircraft linkage connecting hole blanking cover structure Download PDFInfo
- Publication number
- CN112339976A CN112339976A CN202011060908.3A CN202011060908A CN112339976A CN 112339976 A CN112339976 A CN 112339976A CN 202011060908 A CN202011060908 A CN 202011060908A CN 112339976 A CN112339976 A CN 112339976A
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- CN
- China
- Prior art keywords
- pin
- plug
- blanking
- connecting pin
- cover
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- 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.)
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Classifications
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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
- B64C1/0009—Aerodynamic aspects
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
Abstract
The utility model provides an aircraft linkage connecting hole blanking cover structure, includes blanking cover and blanking cover connecting pin, its characterized in that: the plug cover is adaptive to the pneumatic outer surface of the airplane, a groove is formed in the surface of the plug cover, the head of the plug cover connecting pin is adaptive to the groove in the surface of the plug cover, the plug cover connecting pin penetrates into the suspension device from the groove, and a small groove is formed in the end part of the plug cover connecting pin; the plug structure further comprises a plug pin, a spring and a stop pin, the plug pin, the spring and the stop pin are arranged in the mounting hole of the suspension device, the plug pin is fixed on a support of the suspension device, the head of the stop pin is adapted to a small groove at the end of a plug connecting pin, and the tail of the stop pin is connected to the plug pin through the spring. The stop pin passes through the elasticity of spring, with the blanking cover connecting pin chucking, and then the chucking blanking cover, fixes the blanking cover at the surface of aircraft for circular blanking cover can not rotate easily, can adapt to the pneumatic profile of aircraft well. The plug cover can be stably fixed on the outer surface of the airplane.
Description
Technical Field
The invention relates to the field of wings, in particular to a connecting hole plugging structure of an aircraft suspension device.
Background
An aircraft (aircraft) is an aircraft with a power plant with one or more engines to generate forward thrust or pull, a fixed wing of the fuselage to generate lift, and heavier than air to fly in the atmosphere. The airplane is one of the most important inventions at the beginning of the 20 th century and is known to be invented by Later brother of Americans. It can be divided into two categories, military and civil, according to its application. The invention of the airplane profoundly changes and affects the life of people, and increasingly becomes an indispensable vehicle for modern civilization.
Due to the special structural design of the airplane, the outer surface of the airplane is a curved surface adaptive to airflow, and due to the fact that hole sites of the suspension device need to be reserved at a plurality of positions of the airplane, the existence of the hole sites can affect the aerodynamic surface of the airplane, affect the airflow of the surface of the airplane and further affect the flight of the airplane.
At present aircraft linkage and aircraft interface roughly can be divided into overhanging fork ear formula and evagination platform formula, when linkage does not install, there is certain unsmooth volume in the pneumatic appearance of connecting hole blanking cover structure on the aircraft and aircraft, because of the connecting hole is different in the position of aircraft surface distribution, the size of its unsmooth volume is also inconsistent, this surface quality that will influence the aircraft, increase the flight resistance of aircraft, be unfavorable for the improvement of aircraft tactics index, in addition, how to fix the blanking cover of the connecting hole on the aircraft, make the blanking cover can not drop easily also be a big difficult problem, research and develop the aircraft linkage connecting hole blanking cover structure that can overcome above-mentioned defect and become the technological problem that technical staff in the field awaited attention to solution.
Disclosure of Invention
The invention aims to: the utility model provides an aircraft linkage connecting hole blanking cover structure is provided with blanking pin, spring and stop pin in the aircraft profile of the blanking cover structure of needs installation, and the stop pin passes through the elasticity of spring, with blanking cover connecting pin chucking, and then chucking blanking cover, fixes the blanking cover at the surface of aircraft, has solved above-mentioned problem.
The technical scheme adopted by the invention is as follows:
the utility model provides an aircraft linkage connecting hole blanking cover structure, includes blanking cover and blanking cover connecting pin, its characterized in that: the plug cover is adaptive to the pneumatic outer surface of the airplane, a groove is formed in the surface of the plug cover, the head of the plug cover connecting pin is adaptive to the groove in the surface of the plug cover, the plug cover connecting pin penetrates into the suspension device from the groove, and a small groove is formed in the end part of the plug cover connecting pin;
the plug structure further comprises a plug pin, a spring and a stop pin, the plug pin, the spring and the stop pin are arranged in the mounting hole of the suspension device, the plug pin is fixed on a support of the suspension device, the head of the stop pin is adapted to a small groove at the end of a plug connecting pin, and the tail of the stop pin is connected to the plug pin through the spring.
In order to better realize the scheme, further, the plug connecting pin is in the form of a countersunk bolt, the outer surface of the plug connecting pin is adapted to the pneumatic outer surface of the airplane, and the inner surface of the plug connecting pin is provided with a stop block for limiting the rotation of the plug connecting pin.
In order to better implement the solution, further, the plug pin is fixed on the support by a rivet.
In order to better realize the scheme, the end part of the plug connecting pin is further provided with two symmetrical small grooves.
In order to better implement the scheme, two symmetrical groups of blocking pins, springs and stopping pins are further arranged in the blocking cover structure.
Because general blanking cap is circular, and circular blanking cap can 360 rotations, in order to guarantee that the surface of circular blanking cap is unanimous with the pneumatic profile of aircraft, design the recess on the support, and circular blanking cap internal surface design boss, circular blanking cap is located the recess of support during the installation, guarantees the mounted position requirement of circular blanking cap, and internal surface design recess simultaneously to control blanking cap connecting pin rotary motion, guarantees the mounted position requirement of blanking cap connecting pin head.
When the plugging cover connecting pin is installed, the installation position of the plugging cover connecting pin is controlled by the stop block on the inner surface of the head of the plugging cover connecting pin, the cylindrical surface at the tail of the plugging cover connecting pin pushes the stop pin to move linearly in the support installation hole, and the spring is in a compressed state. The plug cover connecting pin rotates by about 90 degrees after being installed, one side of a stop block of the plug cover connecting pin is in contact with a groove surface of the inner surface of the circular plug cover, and the tail part of the stop pin enters a hemispherical small groove of the cylindrical pin surface of the plug cover connecting pin due to the rebound of a spring to achieve a locking state of the plug cover connecting pin. During disassembly, the plug cover connecting pin rotates by about 90 degrees, the tail part of the stop pin moves out of the hemispherical groove, and the plug cover connecting pin and the circular plug cover automatically fall off.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. according to the connecting hole plugging structure for the aircraft suspension device, the plugging pin, the spring and the stop pin are arranged in the aircraft profile of the aircraft needing to be provided with the plugging structure, the stop pin clamps the plugging connecting pin through the elasticity of the spring so as to clamp the plugging cover, and the plugging cover is fixed on the outer surface of the aircraft, so that the plugging cover can be stably fixed on the outer surface of the aircraft.
2. According to the connecting hole plugging structure for the aircraft suspension device, the plugging pin, the spring and the stop pin are arranged in the aircraft profile of the aircraft needing to be provided with the plugging structure, the stop pin clamps the plugging connecting pin through the elasticity of the spring so as to clamp the plugging cover, and the plugging cover is fixed on the outer surface of the aircraft, so that the circular plugging cover cannot easily rotate, and the pneumatic profile of the aircraft can be well adapted.
Drawings
In order to more clearly illustrate the technical solution, the drawings needed to be used in the embodiments are briefly described below, and it should be understood that, for those skilled in the art, other related drawings can be obtained according to the drawings without creative efforts, wherein:
FIG. 1 is a schematic structural view of the present invention;
3 FIG. 3 2 3 is 3 a 3 schematic 3 view 3 of 3 the 3 invention 3 taken 3 along 3 the 3 line 3 A 3- 3 A 3 of 3 FIG. 3 1 3; 3
In the figure, 1-support, 2-plug pin, 3-spring, 4-stop pin, 5-plug connecting pin, 6-plug cover, 7-stop block.
Detailed Description
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
It is noted that relational terms such as "first" and "second," and the like, may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The present invention will be described in detail with reference to fig. 1 to 2.
Example 1:
a kind of plane suspension attachment hole blanking cover structure, as shown in fig. 1, 2, including blanking cover 6 and blanking cover connecting pin 5, characterized by that: the plug cover 6 is adaptive to the aerodynamic profile of the airplane, a groove is formed in the surface of the plug cover 6, the head of the plug cover connecting pin 5 is adaptive to the groove in the surface of the plug cover 6, the plug cover connecting pin 5 penetrates into the suspension device from the groove, and a small groove is formed in the end part of the plug cover connecting pin 5;
the blanking cover structure further comprises a blanking pin 2, a spring 3 and a stop pin 4, wherein the blanking pin 2, the spring 3 and the stop pin 4 are arranged in a mounting hole of the suspension device, the blanking pin 2 is fixed on a support 1 of the suspension device, the head of the stop pin 4 is adapted to a small groove at the end part of a blanking cover connecting pin 5, and the tail part of the stop pin 4 is connected to the blanking pin 2 through the spring 3.
The working principle is as follows: because general blanking cap 6 is circular, and circular blanking cap 6 can 360 rotatory, in order to guarantee that the surface of circular blanking cap 6 is unanimous with the pneumatic profile of aircraft, design the recess on support 1, and circular blanking cap 6 internal surface design boss, circular blanking cap 6 is located the recess of support 1 during the installation, guarantee circular blanking cap 6's mounted position requirement, the little recess of 5 tip designs of blanking cap connecting pin simultaneously, with the control blanking cap connecting pin 5 rotary motion, guarantee the mounted position requirement of 5 heads of blanking cap connecting pin.
When the plugging cover connecting pin 5 is installed, the installation position of the plugging cover connecting pin is controlled by the stop block 7 on the inner surface of the head of the plugging cover connecting pin 5, the cylindrical surface at the tail part of the plugging cover connecting pin 5 pushes the stop pin 4 to move linearly in the installation hole of the support 1, and the spring 3 is in a compressed state. The plug cover connecting pin 5 rotates by about 90 degrees after being installed in place, one side of a stop block 7 of the plug cover connecting pin 5 is in contact with a groove surface on the inner surface of the circular plug cover 6, and the spring 3 rebounds to enable the tail part of the stop pin 4 to enter a small hemispherical groove on the cylindrical pin surface of the plug cover connecting pin 5 to achieve the locking state of the plug cover connecting pin 5. During disassembly, the plug cover connecting pin 5 rotates by about 90 degrees, the tail part of the stop pin 4 moves out of the hemispherical groove, and the plug cover connecting pin 5 and the circular plug cover 6 automatically fall off.
Example 2:
on the basis of the embodiment 1, the invention provides a connecting hole plugging structure of an aircraft suspension device, as shown in fig. 1 and fig. 2, the plugging connecting pin 5 is in the form of a countersunk head bolt, the outer surface of the plugging connecting pin 5 is adapted to the aerodynamic profile of the aircraft, and the inner surface of the plugging connecting pin 5 is provided with a stop block 7 for limiting the rotation of the plugging connecting pin 5.
Further, the plug pin 2 is fixed to the support 1 by means of rivets.
Further, the end of the blanking cover connecting pin 5 is provided with two symmetrical small grooves.
Furthermore, two symmetrical groups of blocking pins 2, springs 3 and stop pins 4 are arranged in the blocking cover structure.
The working principle is as follows: because general blanking cap 6 is circular, and circular blanking cap 6 can 360 rotatory, in order to guarantee that the surface of circular blanking cap 6 is unanimous with the pneumatic profile of aircraft, design the recess on support 1, and circular blanking cap 6 internal surface design boss, circular blanking cap 6 is located the recess of support 1 during the installation, guarantee the mounted position requirement of circular blanking cap 6, two symmetrical little recesses are designed to 5 tip of blanking cap connecting pin simultaneously, cooperate spring 3 control blanking cap connecting pin 5 rotary motion with two sets of symmetrical stop pins 4, guarantee the mounted position requirement of 5 heads of blanking cap connecting pin.
When the plugging cover connecting pin 5 is installed, the installation position of the plugging cover connecting pin is controlled by the stop block 7 on the inner surface of the head of the plugging cover connecting pin 5, the cylindrical surface at the tail part of the plugging cover connecting pin 5 pushes the stop pin 4 to move linearly in the installation hole of the support 1, and the spring 3 is in a compressed state. The plug cover connecting pin 5 rotates by about 90 degrees after being installed in place, one side of a stop block 7 of the plug cover connecting pin 5 is in contact with a groove surface on the inner surface of the circular plug cover 6, and the spring 3 rebounds to enable the tail part of the stop pin 4 to enter a small hemispherical groove on the cylindrical pin surface of the plug cover connecting pin 5 to achieve the locking state of the plug cover connecting pin 5. During disassembly, the plug cover connecting pin 5 rotates by about 90 degrees, the tail part of the stop pin 4 moves out of the hemispherical groove, and the plug cover connecting pin 5 and the circular plug cover 6 automatically fall off.
Other parts of this embodiment are the same as those of embodiment 1, and thus are not described again.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (5)
1. The utility model provides an aircraft linkage connecting hole blanking cover structure, includes blanking cover (6) and blanking cover connecting pin (5), its characterized in that: the plug cover (6) is adaptive to the aerodynamic profile of an airplane, a groove is formed in the surface of the plug cover (6), the head of the plug cover connecting pin (5) is adaptive to the groove in the surface of the plug cover (6), the plug cover connecting pin (5) penetrates through the groove and extends into the suspension device, and a small groove is formed in the end of the plug cover connecting pin (5);
the blanking cover structure further comprises a blanking pin (2), a spring (3) and a stop pin (4), wherein the blanking pin (2), the spring (3) and the stop pin (4) are arranged in a mounting hole of the suspension device, the blanking pin (2) is fixed on a support (1) of the suspension device, the head of the stop pin (4) is adapted to a small groove at the end part of a blanking cover connecting pin (5), and the tail part of the stop pin (4) is connected to the blanking pin (2) through the spring (3).
2. The aircraft suspension attachment hole blanking cover structure of claim 1, wherein: the form of countersunk bolt is used to blanking cover connecting pin (5), the surface adaptation aircraft pneumatics profile of blanking cover connecting pin (5), and the internal surface of blanking cover connecting pin (5) is provided with stop block (7), the rotation of restriction blanking cover connecting pin (5).
3. The aircraft suspension attachment hole blanking cover structure of claim 1, wherein: the blocking pin (2) is fixed on the support (1) through a rivet.
4. The aircraft suspension attachment hole blanking cover structure of claim 1, wherein: the end part of the plug cover connecting pin (5) is provided with two symmetrical small grooves.
5. An aircraft suspension attachment hole blanking cap structure according to claim 4, wherein: two symmetrical groups of blocking pins (2), springs (3) and stop pins (4) are arranged in the blocking cover structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011060908.3A CN112339976A (en) | 2020-09-30 | 2020-09-30 | Aircraft linkage connecting hole blanking cover structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011060908.3A CN112339976A (en) | 2020-09-30 | 2020-09-30 | Aircraft linkage connecting hole blanking cover structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112339976A true CN112339976A (en) | 2021-02-09 |
Family
ID=74361426
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011060908.3A Pending CN112339976A (en) | 2020-09-30 | 2020-09-30 | Aircraft linkage connecting hole blanking cover structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112339976A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030213095A1 (en) * | 2002-05-03 | 2003-11-20 | Jackson Frank T. | Flush handle assembly |
| CN101519119A (en) * | 2009-03-13 | 2009-09-02 | 贵州航天精工制造有限公司 | Fast-disassembly method of aeroplane access cover and bearing lock |
| US20100243809A1 (en) * | 2009-03-30 | 2010-09-30 | The Boeing Company | Opening plug and method of installing the same |
| US20100303542A1 (en) * | 2007-12-21 | 2010-12-02 | Sfs Intec Holding Ag | Plug mounting |
| CN105217014A (en) * | 2015-10-15 | 2016-01-06 | 中国航天科技集团公司第四研究院第四十一研究所 | A kind of quick-release opening cover device |
| WO2017003671A1 (en) * | 2015-07-02 | 2017-01-05 | Northrop Grumman Systems Corporation | Rotary ball lock latching mechanism |
| CN108609190A (en) * | 2016-12-12 | 2018-10-02 | 中国航空工业集团公司成都飞机设计研究所 | Rotary stealthy multi-functional lid |
| US20190162225A1 (en) * | 2017-11-27 | 2019-05-30 | The Boeing Company | Seal system and method |
| CN209290660U (en) * | 2018-12-01 | 2019-08-23 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of quick release aircraft wing hanging point lid |
-
2020
- 2020-09-30 CN CN202011060908.3A patent/CN112339976A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030213095A1 (en) * | 2002-05-03 | 2003-11-20 | Jackson Frank T. | Flush handle assembly |
| US20100303542A1 (en) * | 2007-12-21 | 2010-12-02 | Sfs Intec Holding Ag | Plug mounting |
| CN101519119A (en) * | 2009-03-13 | 2009-09-02 | 贵州航天精工制造有限公司 | Fast-disassembly method of aeroplane access cover and bearing lock |
| US20100243809A1 (en) * | 2009-03-30 | 2010-09-30 | The Boeing Company | Opening plug and method of installing the same |
| WO2017003671A1 (en) * | 2015-07-02 | 2017-01-05 | Northrop Grumman Systems Corporation | Rotary ball lock latching mechanism |
| CN105217014A (en) * | 2015-10-15 | 2016-01-06 | 中国航天科技集团公司第四研究院第四十一研究所 | A kind of quick-release opening cover device |
| CN108609190A (en) * | 2016-12-12 | 2018-10-02 | 中国航空工业集团公司成都飞机设计研究所 | Rotary stealthy multi-functional lid |
| US20190162225A1 (en) * | 2017-11-27 | 2019-05-30 | The Boeing Company | Seal system and method |
| CN209290660U (en) * | 2018-12-01 | 2019-08-23 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of quick release aircraft wing hanging point lid |
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Application publication date: 20210209 |