Socket installation device of aircraft and aircraft

Abstract

The invention provides a socket installation device of an aircraft and the aircraft, and relates to the technical field of aircrafts, the socket installation device is used for installing a socket of the aircraft, the socket is arranged in a cabin of the aircraft, an opening is formed in the position, opposite to the socket, of the cabin, and when the aircraft is arranged on a launching device, a plug of the launching device can penetrate through the opening and is inserted into the socket. The socket installation device comprises two cover plates, the two cover plates are connected to the inner side of the cabin body in a sliding mode and arranged on the two sides of the opening respectively, the socket is installed on the sides, away from the cabin body, of the two cover plates, and the opposite ends of the two cover plates can abut against the two sides of the plug respectively; one ends of the two elastic pieces are connected with the two cover plates respectively, and the other ends of the two elastic pieces are connected to the inner side of the cabin body, so that the functions of maintaining the aerodynamic shape and preventing rain at the opening after launching are achieved, and compared with the prior art, the side face finish paint of the launching guide frame of the launching device cannot be damaged; therefore, the service life of the hair guide frame is prolonged.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft, and more specifically, relates to a socket installation device for an aircraft and an aircraft. Background Art

[0002] The separation socket is the electrical interface between the aircraft and the launch device, which is used to connect with the separation plug of the launch device. The separation socket is separated from the separation plug after the aircraft is launched. In order to improve the aerodynamic performance and stealth performance of the aircraft, the separation socket of the aircraft is required to be buried inside the aircraft cabin, and after launch, the cabin at the opening position of the separation socket should have shape-maintaining and rainproof functions.

[0003] At present, an automatic flap device is commonly used to maintain the shape and rainproof the opening position of the cabin body. The automatic flap device specifically uses a torsion spring to control the flap state. When the aircraft is on hang-up, the flap is opened and leans on the side of the launcher frame. After the aircraft is launched, it is separated from the launcher frame, the flap is separated from the launcher frame, and the flap is closed by relying on the torsion force of the torsion spring. However, in the process of the aircraft being separated from the launcher, there is friction between the inner surface of this type of automatic locking flap and the side of the launcher frame, which can easily cause damage to the paint on the side of the launcher frame, thereby reducing the service life of the launcher frame. Summary of the invention

[0004] The purpose of the present invention is to provide a socket installation device for an aircraft and an aircraft in view of the deficiencies in the existing technology, so as to solve the problem proposed in the above background technology that the currently commonly used automatic flip cover device is used to shape and rainproof the opening position of the cabin for inserting a plug, but after the aircraft is launched, there is friction between the inner surface of the automatic locking flip cover and the side of the hair guide frame, which easily causes the side paint of the hair guide frame to be damaged, thereby reducing the service life of the hair guide frame.

[0005] In order to achieve the above-mentioned object, the present invention provides a socket installation device for an aircraft, which is used for installing a socket of the aircraft, wherein the socket is arranged inside a cabin of the aircraft, and an opening is arranged in the cabin relative to the socket. When the aircraft is arranged on a launching device, a plug of the launching device can pass through the opening and be inserted into the socket. The socket installation device comprises:

[0006] Two cover plates, the two cover plates are slidably connected to the inner side of the cabin body and are respectively arranged on both sides of the opening, the socket is installed on the side of the two cover plates away from the cabin body, and the opposite ends of the two cover plates can be respectively pressed against the two sides of the plug;

[0007] Two elastic members, one end of the two elastic members is respectively connected to the two cover plates, and the other end of the two elastic members is connected to the inner side of the cabin body. When the plug is detached from the socket, the two cover plates can move in opposite directions under the elastic action of the two elastic members to cover the opening.

[0008] Preferably, the socket mounting device of the aircraft also includes a mounting block, a socket is provided in the middle of the mounting block, one side of the mounting block is connected to the inner side of the cabin, the other side of the mounting block is connected to the socket, the socket and the socket are arranged opposite to each other, the plug can pass through the socket, and the two cover plates are slidably connected to one side of the mounting block.

[0009] Preferably, a concave portion is provided on one side of the mounting block, and the two cover plates are slidably connected inside the concave portion.

[0010] Preferably, both sides of the concave portion are provided with sliding grooves, and both sides of the cover plate are bent to form sliding plates, and the sliding plates on both sides of the cover plate are slidably connected in the sliding grooves on both sides respectively.

[0011] Preferably, both ends of the mounting block are provided with end grooves, and the socket mounting device of the aircraft also includes two rod bodies, one end of the two rod bodies are respectively connected to the opposite end of the two cover bodies, one end of the two elastic members are respectively connected to the end surfaces of the two end grooves, and the other end of the two elastic members are respectively connected to the other end of the two rod bodies.

[0012] Preferably, both ends of the elastic member are connected with hooks, the other ends of the two rod bodies are connected with ring bodies, the end faces of the two end grooves are connected with ring bodies, and the hooks are hung on the matching ring bodies.

[0013] Preferably, the mounting block is provided with four first mounting holes connected to the cabin body.

[0014] Preferably, a mounting groove connected to the socket is provided on the other side of the mounting block, and four second mounting holes connected to the socket are provided in the mounting groove.

[0015] Preferably, the mounting block and the cover plate are arc-shaped, so as to fit the arc-shaped cabin.

[0016] An aircraft includes a socket installation device of the aircraft.

[0017] The present invention provides a socket installation device for an aircraft and an aircraft, and its beneficial effects are: two cover plates of the socket installation device are slidably connected to the two sides of an opening, one end of two elastic members are respectively connected to the two cover plates, and the other ends of the two elastic members are connected to the inner side of a cabin body, and the socket is installed on the side of the two cover plates away from the cabin body. When the aircraft is set on a launching device and before launching, a plug passes through the opening and is inserted into the socket, and the opposite ends of the two cover plates are respectively pressed against the two sides of the plug, and the elastic member is in a stretched state. When the aircraft is separated from the launching device, the plug is separated from the aircraft under the action of the launching device. At this time, the elastic member restores its original state due to the elastic force, and the two elastic members pull the two cover plates to move in opposite directions until the opening for installing the plug is closed, so that the opening has the function of maintaining an aerodynamic shape and rainproof after launching. Compared with the prior art, it will not cause damage to the side surface paint of the guide frame of the launching device, thereby improving the service life of the guide frame.

[0018] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0020] Figure 1 A schematic diagram showing the three-dimensional structure of a socket installation device for an aircraft according to an embodiment of the present invention when installed in a cabin. Figure 1 ;

[0021] Figure 2 A schematic diagram showing the three-dimensional structure of a socket installation device for an aircraft according to an embodiment of the present invention when installed in a cabin. Figure 2 ;

[0022] Figure 3 A schematic diagram of the three-dimensional structure of a socket installation device for an aircraft according to an embodiment of the present invention is shown;

[0023] Figure 4 A schematic diagram of the three-dimensional structure of a socket installation device for an aircraft according to an embodiment of the present invention when two cover plates close an opening;

[0024] Figure 5 A schematic diagram of the three-dimensional structure of a socket installation device for an aircraft according to an embodiment of the present invention when two cover plates are combined;

[0025] Figure 6A schematic diagram of the three-dimensional structure of a mounting block of a socket mounting device for an aircraft according to an embodiment of the present invention is shown;

[0026] Figure 7 A schematic diagram of the three-dimensional structure of a cover body of a socket installation device for an aircraft according to an embodiment of the present invention is shown;

[0027] Description of reference numerals:

[0028] 1. Socket; 2. Cabin; 3. Opening; 4. Plug; 5. Cover; 6. Elastic part; 7. Mounting block; 8. Socket; 9. Slide; 10. Rod; 11. Concave part. DETAILED DESCRIPTION

[0029] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0030] like Figure 1-Figure 4 As shown, the present invention provides a socket installation device for an aircraft, which is used to install a socket 1 of the aircraft. The socket 1 is arranged inside a cabin 2 of the aircraft. The cabin 2 is provided with an opening 3 at a position relative to the socket 1. When the aircraft is arranged on a launching device, a plug 4 of the launching device can pass through the opening 3 and be inserted into the socket 1. The socket installation device includes:

[0031] Two cover plates 5, the two cover plates 5 are slidably connected to the inner side of the cabin 2 and are respectively arranged on both sides of the opening 3, the socket 1 is installed on the side of the two cover plates 5 away from the cabin 2, and the opposite ends of the two cover plates 5 can be respectively pressed against the two sides of the plug 4;

[0032] Two elastic members 6, one end of the two elastic members 6 is connected to the two cover plates 5 respectively, and the other end of the two elastic members 6 is connected to the inner side of the cabin 2. When the plug 4 is disconnected from the socket 1, the two cover plates 5 can move in opposite directions under the elastic action of the two elastic members 6 to cover the opening 3.

[0033] Specifically, in order to solve the problem that the currently commonly used automatic flip cover device maintains the shape and rainproof of the opening position of the cabin for inserting the plug, but after the aircraft is launched, there is friction between the inner surface of the automatic locking flip cover and the side of the launcher, which is easy to cause the side paint of the guide frame to be damaged, thereby reducing the service life of the guide frame, the present invention provides a socket installation device for an aircraft and an aircraft, wherein two cover plates 5 of the socket installation device are slidably connected to both sides of the opening 3, one end of two elastic members 6 are respectively connected to the two cover plates 5, and the other end of the two elastic members 6 are connected to the inner side of the cabin 2, and the socket 1 is installed on the side of the two cover plates 5 away from the cabin. When the aircraft is set on the launch device When the launch device is in the upper position, and before launching, the plug 4 passes through the opening 3 and is inserted into the socket 1, and the opposite ends of the two cover plates 5 are respectively pressed against the two sides of the plug 4. At this time, the elastic member 6 is in a stretched state. When the aircraft is separated from the launching device, the plug 4 is separated from the aircraft under the action of the launching device. At this time, the elastic member 6 restores its original state due to the elastic force, and the two elastic members 6 will pull the two cover plates 5 to move in opposite directions until the opening 3 where the plug 4 is installed is closed, so that the opening 3 has the function of maintaining the aerodynamic shape and rainproof after launching. Compared with the prior art, it will not cause the side surface paint of the guide frame of the launching device to be damaged, thereby improving the service life of the guide frame.

[0034] like Figure 5-Figure 7 As shown, preferably, the socket mounting device of the aircraft also includes a mounting block 7, a socket 8 is provided in the middle of the mounting block 7, one side of the mounting block 7 is connected to the inner side of the cabin 2, and the other side of the mounting block 7 is connected to the socket 1, the socket 1 and the socket 8 are arranged opposite to each other, the plug 4 can pass through the socket 8, and the two cover plates 5 are slidably connected to one side of the mounting block 7.

[0035] Specifically, the mounting block 7 is used to support the socket 1. When the aircraft is set on the launching device and before launching, the plug 4 passes through the opening 3 and the socket 8 in sequence and is inserted into the socket 1. When the aircraft is detached from the launching device and the plug 4 is detached from the aircraft, the two cover plates 5 can slide on one surface of the mounting block 7 under the action of the elastic member 6 until the opening 3 for installing the plug 4 is closed.

[0036] Preferably, a concave portion 11 is provided on one side of the mounting block 7 , and the two cover plates 5 are slidably connected inside the concave portion 11 .

[0037] Specifically, the concave portion 11 is used to assemble the cover plate 5. When the aircraft is detached from the launching device and the plug 4 is detached from the aircraft, the two cover plates 5 can slide in the concave portion 11 under the action of the elastic member 6 until the opening 3 for installing the plug 4 is closed.

[0038] Preferably, both sides of the concave portion 11 are provided with sliding grooves 9 , and both sides of the cover plate 5 are bent to form sliding plates, and the sliding plates on both sides of the cover plate 5 are slidably connected to the sliding grooves 9 on both sides respectively.

[0039] Specifically, the slide groove 9 is used for the sliding of the slide plate and guides the cover plate 5 so that the cover plate 5 can slide stably.

[0040] Preferably, end grooves are provided at both ends of the mounting block, and the socket mounting device of the aircraft also includes two rod bodies 10, one end of the two rod bodies 10 is respectively connected to the opposite end of the two cover bodies 5, one end of the two elastic members 6 is respectively connected to the end surfaces of the two end grooves, and the other ends of the two elastic members 6 are respectively connected to the other ends of the two rod bodies 10.

[0041] Specifically, the other end of the rod body 10 is bent, and the elastic member 6 can be a tension spring. One end of the rod body 10 and the end surface of the end groove are used to realize the connection of the tension spring. The two tension springs will be able to pull the two cover plates 5 to move in opposite directions until the opening 3 for installing the plug 4 is closed.

[0042] Preferably, both ends of the elastic member 6 are connected with hooks, the other ends of the two rod bodies 10 are connected with ring bodies, the end faces of the two end grooves are connected with ring bodies, and the hooks are hung on the matching ring bodies.

[0043] Specifically, one end of each elastic member 6 is hooked on a ring body of a rod body 10 , and the other end is hooked on a ring body of an end groove, so that the elastic member 6 is installed.

[0044] Preferably, the mounting block 7 is provided with four first mounting holes connected to the cabin body 2 .

[0045] Specifically, the first mounting hole is used to fix the mounting block 7 to the cabin body 2 by screws.

[0046] Preferably, a mounting groove connected to the socket 1 is provided on the other side of the mounting block 7 , and four second mounting holes connected to the socket 1 are provided in the mounting groove.

[0047] Specifically, the second mounting hole is used to fix the mounting block 7 and the socket 1 by screws.

[0048] Preferably, the mounting block 7 and the cover plate 5 are arc-shaped, so as to fit the arc-shaped cabin body 2 .

[0049] Specifically, the arc-shaped mounting block 7 and the cover plate 5 can fit on the inner side of the arc-shaped cabin body 2, which can better maintain the aerodynamic shape and improve the rainproof performance.

[0050] An aircraft includes a socket installation device of the aircraft.

[0051] In summary, when the socket installation device of the aircraft is implemented on the aircraft, when the aircraft is set on the launching device and before launching, the plug 4 passes through the opening 3 and is inserted into the socket 1, and the opposite ends of the two cover plates 5 are respectively pressed against the two sides of the plug 4, and the tension spring is in a stretched state. When the aircraft is separated from the launching device, the plug 4 is separated from the aircraft under the action of the launching device. At this time, the tension spring recovers its original state due to the elastic force, and the two tension springs will pull the two cover plates 5 to move in opposite directions until the opening 3 where the plug 4 is installed is closed, so that the opening 3 has the function of maintaining the aerodynamic shape and rainproof after launching, and solves the problem that there is friction between the inner surface of the automatic locking flip cover of the existing separation socket and the side of the guide frame, causing the side paint of the guide frame to be damaged, thereby reducing the service life of the guide frame, and the socket installation device is a pure mechanical component with a simple structure and high reliability. It does not contain pyrotechnics, high-pressure gas and other inflammable and explosive dangerous goods, and has significant advantages in testing, transportation, storage and other aspects.

[0052] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A socket installation device for an aircraft, used for installing a socket of the aircraft, wherein the socket is arranged inside a cabin of the aircraft, and an opening is arranged in the cabin relative to the socket. When the aircraft is arranged on a launching device, the plug of the launching device can pass through the opening and be inserted into the socket, characterized in that: The socket installation device comprises: Two cover plates, the two cover plates are slidably connected to the inner side of the cabin body and are respectively arranged on both sides of the opening, the socket is installed on the side of the two cover plates away from the cabin body, and the opposite ends of the two cover plates can be respectively pressed against the two sides of the plug; Two elastic members, one end of the two elastic members is respectively connected to the two cover plates, and the other end of the two elastic members is connected to the inner side of the cabin body. When the plug is detached from the socket, the two cover plates can move in opposite directions under the elastic action of the two elastic members to cover the opening.

2. The socket installation device for an aircraft according to claim 1, characterized in that: The socket mounting device of the aircraft also includes a mounting block, a socket is provided in the middle of the mounting block, one side of the mounting block is connected to the inner side of the cabin, and the other side of the mounting block is connected to the socket, the socket and the socket are arranged opposite to each other, the plug can pass through the socket, and the two cover plates are slidably connected to one side of the mounting block.

3. The socket installation device for an aircraft according to claim 2, characterized in that: A concave portion is provided on one side of the mounting block, and the two cover plates are slidably connected inside the concave portion.

4. The socket installation device for an aircraft according to claim 3, characterized in that: Slide grooves are provided on both sides of the concave portion, and slide plates are formed by bending on both sides of the cover plate. The slide plates on both sides of the cover plate are respectively slidably connected in the slide grooves on both sides.

5. The socket installation device for an aircraft according to claim 4, characterized in that: Both ends of the mounting block are provided with end grooves, and the socket mounting device of the aircraft also includes two rod bodies, one end of the two rod bodies is respectively connected to the end opposite to the two cover bodies, one end of the two elastic members is respectively connected to the end surfaces of the two end grooves, and the other end of the two elastic members is respectively connected to the other end of the two rod bodies.

6. The socket installation device for an aircraft according to claim 5, characterized in that: Both ends of the elastic member are connected with hooks, the other ends of the two rod bodies are connected with ring bodies, the end faces of the two end grooves are connected with ring bodies, and the hooks are hung on the matching ring bodies.

7. The socket installation device for an aircraft according to claim 2, characterized in that: The mounting block is provided with four first mounting holes connected with the cabin body.

8. The socket installation device for an aircraft according to claim 2, characterized in that: A mounting groove connected to the socket is provided on the other side of the mounting block, and four second mounting holes connected to the socket are provided in the mounting groove.

9. The socket installation device for an aircraft according to claim 2, characterized in that: The mounting block and the cover plate are arc-shaped and are used to adapt to the arc-shaped cabin body.

10. An aircraft, characterized in that: The invention comprises a socket mounting device for an aircraft according to any one of claims 1 to 9.

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