A display screen buffer fixed installation structure in an aircraft control device

Abstract

The present invention discloses a buffering fixed installation structure for a display screen in an aircraft control device, comprising a light-transmitting cover body, which has a cover body top wall, a cover body peripheral wall, and a cover body cavity defined by the cover body top wall and the cover body peripheral wall, wherein the cover body cavity is formed with a downward opening; a display screen, which is placed inside the cover body cavity, wherein the top surface of the display screen and the bottom surface of the cover body top wall are opposite to each other and a gap is defined between the two; and buffer particles, which are placed in the gap. Advantages of the present invention: when the display screen is subjected to vibration impact, the buffer particles and / or the supporting cantilever provide buffering protection for the display screen; when the light-transmitting cover body is deformed by force, the multi-point contact achieved by the buffer particles prevents the entire plane of the display screen from being damaged by force.

Description

Technical Field

[0001] The invention relates to an aircraft control device, in particular to a display screen buffering fixing installation structure in an aircraft control device. Background Art

[0002] At present, the integration of display function and control function in aircraft control devices has become an inevitable trend (for example, the display screen is directly installed on the control button or the control rod head). However, since the display screen itself has poor tolerance to mechanical environment, when it is affected by mechanical forces such as vibration and impact generated by the operation of the control device, the display screen is prone to breakage. It is urgent to focus on how to protect the display screen in the display screen installation and fixing structure. Summary of the invention

[0003] The purpose of the present invention is to solve the problem of poor tolerance of display screens to mechanical environments in the prior art, and to provide a novel buffering fixed installation structure for display screens in aircraft control devices.

[0004] In order to achieve this purpose, the technical solution of the present invention is as follows: a display screen buffer fixing installation structure in an aircraft control device, comprising:

[0005] A light-transmitting cover body, comprising a cover body top wall, a cover body peripheral wall, and a cover body cavity defined by the cover body top wall and the cover body peripheral wall, wherein the cover body cavity is formed with a downward opening;

[0006] a display screen, which is disposed inside the housing chamber, wherein the top surface of the display screen is opposite to the bottom surface of the housing top wall and a gap is defined between the two; and,

[0007] Buffer particles are placed in the gap, the material stiffness of the buffer particles is lower than the material stiffness of the top wall of the cover and the display screen, and the number of the buffer particles is plural, so that the top wall of the cover and the display screen form multi-point contact force.

[0008] As a preferred solution for a buffer fixed installation structure of a display screen in an aircraft control device, the light-transmitting cover body adopts a square structure; the number of the buffer particles is four, which are respectively arranged at the four corners of the top wall of the cover body.

[0009] As a preferred solution for a buffer fixed installation structure of a display screen in an aircraft control device, an upwardly recessed receiving slot is formed on the bottom surface of the top wall of the cover body, the upper portion of the buffer particles is embedded in the interior of the receiving slot, and the lower portion of the buffer particles is exposed outside the receiving slot.

[0010] As a preferred solution for a buffered fixed installation structure of a display screen in an aircraft control device, it also includes a buffer base, which is placed inside the cover body cavity and below the display screen. The buffer base has a base bottom wall and a base peripheral wall. A positioning protrusion corresponding to the positioning slot is formed on the base peripheral wall and the positioning protrusion extends into the interior of the positioning slot. The positioning protrusion cooperates with the positioning slot so that the base peripheral wall is fixedly connected to the cover body peripheral wall.

[0011] As a preferred solution for a buffered fixed installation structure of a display screen in an aircraft control device, a supporting cantilever is formed on the bottom wall of the base, the supporting cantilever has a fixed end and a free end, a supporting protrusion is formed on the free end of the supporting cantilever, the top surface of the supporting protrusion is abutted against the bottom surface of the display screen, and the supporting protrusion provides an upward elastic force to the display screen.

[0012] As a preferred solution for a buffered fixed installation structure of a display screen in an aircraft control device, the supporting protrusion is a semicircular arc segment that is bent upward as a whole.

[0013] Compared with the prior art, the beneficial effects of the present invention are at least that: when the display screen is subjected to vibration impact, the buffer particles and / or the supporting cantilever provide buffering protection for the display screen; when the light-transmitting cover body is deformed under force, the multi-point contact achieved by the buffer particles prevents the entire display screen plane from being damaged by force. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic structural diagram of an embodiment of the present invention (exploded state).

[0015] Figure 2 It is a structural schematic diagram of an embodiment of the present invention (assembled state).

[0016] Figure 3 Schematic diagram of the structure of a light-transmitting cover body in one embodiment of the present invention.

[0017] Figure 4 It is a schematic structural diagram of a buffer base in one embodiment of the present invention. DETAILED DESCRIPTION

[0018] The present invention is further described in detail below by means of specific embodiments connected with the accompanying drawings. It should be noted that the description of these embodiments is used to help understand the present invention, but does not constitute a limitation of the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0019] See also Figures 1 to 4The figure shows a buffer fixed installation structure of a display screen in an aircraft control device. The buffer fixed installation structure is composed of a light-transmitting cover body 1, a display screen 2, buffer particles 3, a buffer base 4 and other components.

[0020] The light-transmitting cover body 1 comprises a cover body top wall 11, a cover body peripheral wall 12 and a cover body cavity defined by the cover body top wall 11 and the cover body peripheral wall 12. The cover body cavity is formed with a downward opening. The cover body peripheral wall 12 is continuous in the circumferential direction. A positioning card slot 121 is formed on the inner surface of the cover body peripheral wall 12. In this embodiment, the light-transmitting cover body 1 adopts a square structure.

[0021] The display screen 2 is placed inside the housing chamber. The top surface of the display screen 2 is opposite to the bottom surface of the housing top wall 11 and a gap is defined between the two.

[0022] The buffer particles 3 are placed in the gap. The buffer particles 3 are compressed. The material stiffness of the buffer particles 3 is lower than the material stiffness of the cover top wall 11 and the display screen 2. The number of the buffer particles 3 is plural, so that the cover top wall 11 and the display screen 2 form a multi-point contact force instead of a conventional surface contact or line contact force, so as to reduce the plane deformation of the cover top wall 11 and cause the display screen 2 to break. In this embodiment, the number of the buffer particles 3 is four, which are respectively arranged at the four corners of the cover top wall 11.

[0023] In order to position the buffer particles 3 , a receiving slot 122 is formed on the bottom surface of the cover top wall 11 or the cover peripheral wall 12 .

[0024] The buffer base 4 is placed inside the chamber of the cover body and below the display screen 2. The buffer base 4 has a base bottom wall 41 and a base peripheral wall 42. The base peripheral wall 42 is discontinuously disconnected in the circumferential direction, reducing the structural strength of the base peripheral wall 42, so as to facilitate the interference installation of the buffer base 4 and the light-transmitting cover body 1. A positioning protrusion 420 corresponding to the positioning card slot 121 is formed on the base peripheral wall 42, and the positioning protrusion 420 extends into the interior of the positioning card slot 121. The positioning protrusion 420 cooperates with the positioning card slot 121, so that the base peripheral wall 42 is fixedly connected to the cover body peripheral wall 12.

[0025] A supporting cantilever 410 is formed on the bottom wall 41 of the base. The supporting cantilever 410 is located at the notch of the peripheral wall 42 of the base. The supporting cantilever 410 has a fixed end and a free end. A supporting protrusion 4101 is formed on the free end of the supporting cantilever 410. The supporting protrusion 4101 is the highest part of the buffer base 4. In this embodiment, the supporting protrusion 4101 is a semicircular arc segment that is bent upward as a whole. When the positioning protrusion 420 is matched with the positioning card slot 121, the top surface of the supporting protrusion 4101 is against the bottom surface of the display screen 2 and the supporting protrusion 4101 provides an upward elastic force (the force generated by the downward deformation of the supporting protrusion 4101) to the display screen 2, so as to push the display screen 2 to ensure that the display screen 2 squeezes the buffer particles 3. If the display screen 2 is impacted by vibration, the supporting cantilever 410 will continue to deform downward to form a larger deformation, thereby achieving the purpose of buffering and protecting the display screen 2.

[0026] It should be noted that, in order to integrate the display function and the control function, the light-transmitting cover 1 and the display screen 2 are designed to be small in size and installed on the aircraft control device (such as a control button or a control rod head).

[0027] The above only expresses the implementation mode of the practical emergency new type, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be based on the attached claims.

Claims

1. A display screen buffer fixed installation structure in an aircraft control device, It is characterized in that Contains: A light-transmitting cover body, comprising a cover body top wall, a cover body peripheral wall, and a cover body cavity defined by the cover body top wall and the cover body peripheral wall, wherein the cover body cavity is formed with a downward opening, and a positioning groove is formed on the inner surface of the cover body peripheral wall; A display screen is disposed inside the housing chamber, wherein the top surface of the display screen is opposite to the bottom surface of the housing top wall and a gap is defined between the two; Buffer particles are placed in the gap, the material stiffness of the buffer particles is lower than the material stiffness of the top wall of the cover and the display screen, and the number of the buffer particles is plural, so that the top wall of the cover and the display screen form multi-point contact force; as well as, A buffer base is disposed inside the cover body cavity and below the display screen, the buffer base having a base bottom wall and a base peripheral wall, a positioning protrusion corresponding to the positioning slot is formed on the base peripheral wall and the positioning protrusion extends into the interior of the positioning slot, the positioning protrusion cooperates with the positioning slot so that the base peripheral wall is fixedly connected to the cover body peripheral wall, a supporting cantilever is formed on the base bottom wall, the supporting cantilever has a fixed end and a free end, a supporting protrusion is formed on the free end of the supporting cantilever, the top surface of the supporting protrusion is against the bottom surface of the display screen and the supporting protrusion provides an upward elastic force to the display screen.

2. A display screen buffering fixed installation structure in an aircraft control device according to claim 1, It is characterized in that The light-transmitting cover body adopts a square structure; the number of the buffer particles is four, which are respectively arranged at the four corners of the top wall of the cover body.

3. The display screen buffering fixed installation structure in an aircraft control device according to claim 2, It is characterized in that An upwardly recessed accommodating slot is formed on the bottom surface of the top wall of the cover body, the upper portion of the buffer particle is embedded in the accommodating slot, and the lower portion of the buffer particle is exposed outside the accommodating slot.

4. The display screen buffering fixed installation structure in an aircraft control device according to claim 1, It is characterized in that The supporting protrusion is a semicircular arc segment that is bent upward as a whole.

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