CN115195989A - A kind of multifunctional mouth cover for aircraft - Google Patents

Abstract

The application discloses a multifunctional flap for an aircraft, which relates to the technical field of spaceflight and comprises a main body part, a plurality of lifting point pieces and a plurality of connecting pieces, wherein the main body part comprises a flap part and flap periphery side region parts surrounding the flap part, the flap part comprises an operation flap and a wave-transparent flap, and the wave-transparent flap is embedded in the operation flap; a plurality of lifting point members distributed around the main body portion; a plurality of connecting pieces are distributed around the main body part, and the opening cover part is connected with the area part on the periphery of the opening cover through the connecting pieces. The application provides a pair of multi-functional flap for aircraft collects the operation, passes through the wave, lifts by crane a plurality of functions in an organic whole, avoids aircraft cabin body to set up too much opening structurally and leads to aircraft overall structure rigidity to reduce.

Description

A multifunctional flap for aircraft

technical field

The present application relates to the field of aerospace technology, in particular to a multifunctional flap for aircraft.

Background technique

At present, the cabin structure of the aircraft usually has an operation port that is conducive to personnel operation and used to install instruments and equipment, and an operation port cover is installed on the outside of the opening. The wave-transmitting port has a wave-transmitting port cover installed at the opening; in order to meet the lifting needs during the installation and transfer of the aircraft, a lifting point is usually set, and a plug and other structures need to be installed at the opening of the lifting point. These covers and plugs are non-load-bearing structures and are mainly used to realize the opening function on the aircraft and maintain the aerodynamic shape of the outer surface of the cabin.

In the related art, the operating cover, the wave-transmitting cover and the lifting point on the aircraft cabin structure are all located at different positions of the aircraft cabin. For aircraft with small diameter and high loading ratio, too many openings will affect the aircraft. The rigidity of the overall structure will also make the operation more cumbersome.

SUMMARY OF THE INVENTION

Embodiments of the present application provide a multifunctional flap for an aircraft, so as to solve the problem of reducing the rigidity of the overall structure of the aircraft due to too many openings in the cabin structure of the aircraft in the related art.

The present application provides a multifunctional flap for aircraft, including:

The main body part includes an opening cover part and a cover peripheral area part surrounding the opening cover part, the opening cover part includes an operation opening cover and a wave-transmitting opening cover, and the wave-transmitting opening cover is embedded in the inside the operating cover;

a plurality of lifting point pieces, which are distributed around the main body part;

A plurality of connecting pieces are distributed around the main body portion, and the flap portion is connected with the peripheral side region portion of the flap through the connecting pieces.

In some embodiments, the wave-transmitting port cover is in the shape of a boss, the middle of the operation port cover is provided with a through hole whose size is matched with the wave-transmitting port cover, and the wave-transmitting port cover is embedded in the through hole. middle.

In some embodiments, the peripheral region portion of the flap is a frame-like structure, and a limiting plate extending toward the flap portion is provided around the bottom of the peripheral region portion of the flap.

In some embodiments, the hoisting point piece includes a hoisting point steel sleeve and a hoisting point heat-proof plug, the hoisting point steel sleeve and the hoisting point heat-proof plug are embedded in the main body, and the hoisting point heat-proof plug is provided. on the top surface of the steel sleeve at the lifting point, and the top surface of the heat protection plug at the lifting point is flush with the outer surface of the cover portion.

In some embodiments, two blind holes are provided inside the hanging point heat plug.

In some embodiments, the connector includes a special screw and a heat protection plug, the special screw and the heat protection plug are embedded in the main body portion, the heat protection plug is arranged on the top surface of the special screw, and the The top surface of the glow plug is flush with the outer surface of the flap portion.

In some embodiments, the main body further includes an antenna, and the antenna is disposed inside the wave-transmitting port cover.

In some embodiments, the antenna is in the shape of a boss, a pressure plate is sleeved around the antenna boss, and the pressure plate is a frame-shaped structure with a hollow center.

In some embodiments, a first gasket is embedded between the wave-transmitting port cover and the pressing plate.

In some embodiments, a second gasket is sleeved on the peripheral side of the projection of the wave-transmitting port cover.

The beneficial effects brought by the technical solutions provided in the present application include: the embodiment of the present application provides a multi-functional port cover for an aircraft, and the wave-transmitting port cover is embedded in the operation port cover, which can be beneficial to personnel operation and can be used for installation. The operation port of the instrument and the port cover of the wave-transmitting port used for the antenna wave transmission are located on the same main body port cover, so as to avoid too many openings that will affect the overall structural rigidity of the aircraft; the lifting point components are arranged around the main body part, which is convenient for lifting and The lifting point component can also cooperate with the connecting piece to realize the function of connecting and fixing the flap portion and the peripheral region portion of the flap, and the present application has multiple functions of operation, wave transmission, and lifting.

Description of drawings

In order to illustrate the technical solutions in the embodiments of the present application more clearly, the following briefly introduces the drawings that are used in the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without creative effort.

FIG. 1 is an overall schematic diagram of a multi-functional port cover for an aircraft provided by an embodiment of the present application;

FIG. 2 is a schematic diagram of the composition of a multifunctional flap for an aircraft according to an embodiment of the present application;

FIG. 3 is a schematic diagram of the composition of the mouth cover provided in the embodiment of the present application;

FIG. 4 is an overall schematic diagram of a mouth cover provided in an embodiment of the present application;

FIG. 5 is a schematic diagram of the peripheral region of the mouth cover provided by the embodiment of the present application;

6 is a schematic diagram of a wave-transmitting port cover provided in an embodiment of the present application;

7 is a schematic diagram of an operation port cover provided in an embodiment of the present application;

FIG. 8 is a schematic diagram of an antenna provided by an embodiment of the present application;

FIG. 9 is a schematic diagram of a pressing plate provided in an embodiment of the present application;

10 is a schematic diagram of a specially made screw provided by an embodiment of the application;

FIG. 11 is a schematic diagram of a heat plug provided by an embodiment of the present application;

FIG. 12 is a schematic diagram of a lifting point steel sleeve provided in an embodiment of the application;

FIG. 13 is a schematic diagram of a lifting point heat protection plug provided by an embodiment of the present application;

14 is a schematic diagram of a first gasket provided in an embodiment of the application;

FIG. 15 is a schematic diagram of a second gasket provided in an embodiment of the present application.

In the figure: 1. Main body part; 2. Hanging point piece; 3. Connecting piece; 4. First gasket; 5. Second gasket; Antenna; 14. Pressure plate; 21. Steel sleeve for lifting point; 22. Heat-proof plug for lifting point; 31. Special screw; 32. Heat-proof plug; 111. Operation cover; 112. Wave-transmitting cover; 114, limit plate; 221, blind hole.

Detailed ways

In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments It is a part of the embodiments of this application, but not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present application.

The embodiments of the present application provide a multifunctional flap for an aircraft, which can solve the problem of reducing the rigidity of the overall structure of the aircraft due to too many openings in the aircraft cabin structure in the related art.

Referring to FIG. 1 , an embodiment of the present application provides a multifunctional flap for an aircraft, including: a main body 1 , a plurality of hanging point pieces 2 and a plurality of connecting pieces 3 , and the main body 1 includes a flap portion 11 and a surrounding In the peripheral area portion 12 of the mouth cover around the mouth cover portion 11, the mouth cover portion 11 includes an operation mouth cover 111 and a wave-transmitting mouth cover 112, and the wave-transmitting mouth cover 112 is embedded in the operation mouth cover 111; see FIG. 2 . , a plurality of hanging point pieces 2 are distributed around the main body portion 1 ; a plurality of connecting pieces 3 are distributed around the main body portion 1 , and the cover portion 11 is connected to the peripheral region portion 12 of the mouth cover through the connecting pieces 3 . Correspondingly, the flap portion 11 and the flap peripheral region portion 12 are provided with mounting holes that match the dimensions of the hanging point piece 2 and the connecting piece 3 . The application does not limit the specific size and quantity of the lifting point piece 2 and the connecting piece 3 .

Compared with the prior art, in the multi-function port cover for an aircraft in the embodiment of the present application, the wave-transmitting port cover 112 is embedded in the operation port cover 111, which can realize the operation that is beneficial to the operation of personnel and used for installing instruments and equipment. The port and the port cover of the wave-transmitting port for the antenna 13 to transmit the wave are located on the same main body port cover, so as to avoid too many openings which will affect the overall structural rigidity of the aircraft; The point piece 2 can also cooperate with the connecting piece 3 to realize the function of connecting and fixing the flap portion 11 and the peripheral side region portion 12 of the flap. The present application has multiple functions of operation, wave transmission, and lifting.

As an optional embodiment, as shown in FIG. 6 , the wave-transmitting port cover 112 is in the shape of a boss, and as shown in FIG. 7 , the operation port cover 111 is provided with a through hole 113 in the middle of the size matching the wave-transmitting port cover 112 , Referring to FIG. 4 , the wave-transmitting cover 112 is embedded in the through hole 113 , and the wave-transmitting cover 112 is used for transmitting the waves of the antenna 13 . The present application does not limit the specific connection manner of the wave-transmitting port cover 112 and the operation port cover 111 .

As an optional embodiment, as shown in FIG. 5 , the peripheral region portion 12 of the flap is a frame-like structure, and a limit plate 114 extending toward the flap portion 11 is provided around the bottom of the peripheral region 12 of the flap. The limiting plate 114 is provided with a slightly larger mounting hole for mounting the hanging point piece 2 and a slightly smaller mounting hole for mounting the connecting piece 3 .

As an optional embodiment, as shown in FIG. 12 and FIG. 13 , the lifting point piece 2 includes a lifting point steel sleeve 21 and a lifting point heat protection plug 22 , as shown in FIG. 2 , the lifting point steel sleeve 21 and the The heat plug 22 is embedded in the main body portion 1 , the hanging point heat plug 22 is arranged on the top surface of the hanging point steel sleeve 21 , and the top surface of the hanging point heat plug 22 is flush with the outer surface of the cover portion 11 . In the embodiment of the present application, there is a certain gap between the top surface of the lifting point steel sleeve 21 and the lifting point heat protection plug 22. Both the lifting point steel sleeve 21 and the lifting point heat protection plug 22 are threadedly connected to the main body 1, which is convenient for disassembly and assembly. After removing the hoisting point heat-proof plug 22 and the hoisting point steel sleeve 21, the exposed threaded holes can be installed with special hoisting tooling for hoisting the aircraft, and the hoisting point piece 2 can cooperate with the connecting piece 3 to further connect the fixed port cover 11 and the The flap peripheral side region portion 12 .

As an optional embodiment, as shown in FIG. 13 , two blind holes 221 are provided inside the lifting point heat protection plug 22 , and the lifting point heat protection plug 22 can be easily disassembled by using the blind holes 221 .

As an optional embodiment, as shown in FIGS. 10 and 11 , the connector 3 includes special screws 31 and heat plugs 32 , the special screws 31 and heat plugs 32 are embedded in the main body 1 , and the heat plugs 32 It is arranged on the top surface of the special screw 31, and the top surface of the heat protection plug 32 is flush with the outer surface of the cover portion 11. The top surface of the heat protection plug 32 is also provided with a blind hole, which is convenient for disassembly and assembly.

As an optional embodiment, as shown in FIG. 3 , the main body portion 1 further includes an antenna 13 , and the antenna 13 is arranged inside the wave-transmitting port cover 112 to ensure wave-transmission of the antenna.

As an optional embodiment, as shown in FIG. 8 , the antenna 13 is in the shape of a boss, and a pressure plate 14 is sleeved around the boss of the antenna 13 , as shown in FIG. 9 , the pressure plate 14 is in the shape of a hollow frame in the middle, which is used for protection The antenna 13 is not damaged; the pressing plate 14 is provided with through holes and threaded holes, wherein the through holes are used for the connection between the pressing plate 14 and the operation port cover 111, and the threaded holes are used for installing the antenna 13. No restrictions.

As an optional embodiment, as shown in FIG. 14 , a first gasket 4 is embedded between the wave-transmitting port cover 112 and the pressing plate 14 .

As an optional embodiment, as shown in FIG. 15 , a second gasket 5 is sleeved on the peripheral side of the boss of the wave-transmitting port cover 112 . The first gasket 4 and the second gasket 5 are both made of rubber and used for Avoid damage to the wave-transmitting cover 112 .

After the assembly of the aircraft structure is completed, when the aircraft needs to be lifted, the lifting point steel sleeve 21 and the lifting point heat protection plug 22 can be removed first, and then a lifting tool is installed at the corresponding lifting point hole to realize the lifting of the aircraft. When the instruments and equipment in the aircraft need to be replaced, the special screws 31, heat protection plugs 32, lifting point steel sleeves 21, lifting point heat protection plugs 22 and the cover 11 can be removed, and the instruments and equipment can be replaced through the opening on the aircraft; The cover 112 can meet the wave transmission requirements of the antenna 13 .

In the description of this application, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the application and simplifying the description, Rather than indicating or implying that the referred device or element must have a particular orientation, be constructed and operate in a particular orientation, it should not be construed as a limitation on the application. Unless otherwise expressly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection, It can also be an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or an internal connection between two components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific situations.

It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply Any such actual relationship or sequence exists between these entities or operations. Moreover, the terms "comprising", "comprising" or any other variation thereof are intended to encompass a non-exclusive inclusion such that a process, method, article or device that includes a list of elements includes not only those elements, but also includes not explicitly listed or other elements inherent to such a process, method, article or apparatus. Without further limitation, an element qualified by the phrase "comprising a..." does not preclude the presence of additional identical elements in a process, method, article or apparatus that includes the element.

The above descriptions are only specific embodiments of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, this application is not intended to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims (10)

1. The utility model provides a multi-functional flap for aircraft which characterized in that, it includes:

the main body part (1) comprises a mouth cover part (11) and a mouth cover peripheral side region part (12) surrounding the mouth cover part (11), the mouth cover part (11) comprises an operation mouth cover (111) and a wave-transmitting mouth cover (112), and the wave-transmitting mouth cover (112) is embedded in the operation mouth cover (111);

a plurality of lifting point members (2) distributed around the main body portion (1);

a plurality of connecting pieces (3) distributed around the main body part (1), and the flap part (11) is connected with the flap peripheral side region part (12) through the connecting pieces (3).

2. The multi-functional flap for an aircraft according to claim 1, wherein: wave-transparent flap (112) are the boss form, operation flap (111) middle part be equipped with wave-transparent flap (112) size matching's through-hole (113), wave-transparent flap (112) inlay and locate in through-hole (113).

3. The multi-functional flap for an aircraft according to claim 1, wherein: regional portion (12) all sides of flap are frame column structure, and are equipped with around regional portion (12) bottom of all sides of flap and to limiting plate (114) that flap portion (11) extend.

4. The multi-functional flap for an aircraft according to claim 1, wherein: hoisting point spare (2) include hoisting point steel bushing (21) and hoisting point anti-heat stopper (22), hoisting point steel bushing (21) and hoisting point anti-heat stopper (22) are inlayed and are located in main part (1), hoisting point anti-heat stopper (22) are located hoisting point steel bushing (21) top surface, just hoisting point anti-heat stopper (22) top surface with mouthful cap portion (11) surface parallel and level.

5. The multi-functional flap for an aircraft of claim 4, further comprising: two blind holes (221) are formed in the hoisting point heat-proof plug (22).

6. The multi-functional flap for an aircraft according to claim 1, wherein: the connecting piece (3) comprises a special screw (31) and a heat-proof plug (32), the special screw (31) and the heat-proof plug (32) are embedded in the main body part (1), the heat-proof plug (32) is arranged on the top surface of the special screw (31), and the top surface of the heat-proof plug (32) is flush with the outer surface of the mouth cover part (11).

7. The multi-functional flap for an aircraft according to claim 1, wherein: the main body part (1) further comprises an antenna (13), and the antenna (13) is arranged on the inner side of the wave-transparent cover (112).

8. The multi-functional flap for an aircraft according to claim 7, wherein: the antenna (13) is in a boss shape, a pressing plate (14) is sleeved on the periphery of the boss of the antenna (13), and the pressing plate (14) is in a frame-shaped structure with a hollow middle part.

9. The multi-functional flap for an aircraft according to claim 8, wherein: a first gasket (4) is embedded between the wave-transmitting opening cover (112) and the pressing plate (14).

10. The multi-functional flap for an aircraft according to claim 1, wherein: the periphery of the boss of the wave-transmitting opening cover (112) is sleeved with a second gasket (5).

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