CN210405919U

CN210405919U - Civil aircraft display controller

Info

Publication number: CN210405919U
Application number: CN201921272877.0U
Authority: CN
Inventors: 康凯
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-08-07
Filing date: 2019-08-07
Publication date: 2020-04-24
Anticipated expiration: 2029-08-07

Abstract

A civil aircraft display controller comprises a controller body, the controller body comprises a shell arranged outside, the edge of one end of the shell is provided with a convex edge, one side of the front end of the shell is provided with a control panel, the two ends of the bottom of the shell are provided with sliders, vertical supporting blocks are sleeved on the sliders, the inner sides of the vertical supporting blocks are connected with transverse supporting blocks, anti-skid rubber pads are embedded in the bottoms of the transverse supporting blocks, the tops of the vertical supporting blocks are provided with chutes corresponding to the positions of the sliders, the sliders are inserted in the chutes and fixed through fixing bolts, the top end of the shell is provided with a protection mechanism, the protection mechanism comprises square blocks, protective covers, moving grooves, threaded holes, supporting rods and rollers, the square blocks are fixed at the two ends of the top of the shell, the protective covers are arranged at the inner sides of the square blocks, the placing stability is high, the heat dissipation efficiency is high, and when the heat dissipation device is not used, the front end of the shell can be protected, and the heat dissipation device is favorable for use.

Description

Civil aircraft display controller

Technical Field

The utility model relates to a controller specifically is a civil aircraft display controller.

Background

The display controller realizes the control operation of the display controller and the relevant cross-linking equipment through keys on the light guide plate. The conventional display controller power control circuit includes: light guide plate, power module, opto-coupler, singlechip, CPU, GPU and DC/DC power. The key signals are input to the single chip microcomputer through the optical coupler, the single chip microcomputer periodically scans the key input, a progressive scanning method is adopted, and the key values of the keys are obtained through time delay anti-shaking. The singlechip must scan constantly every cycle, and simultaneously, the CPU and the GPU need to be used, and the GPU does not use a low power consumption mode, so that the power consumption of the display is larger.

The stability is not high when current civil aircraft display controller is placed, and easy the slip, and when placing the casing bottom with place the face contact, the bottom radiating efficiency is low, when not using, the dust is easily fallen to the front end, is unfavorable for the use.

SUMMERY OF THE UTILITY MODEL

To the above situation, for overcoming prior art's defect, the utility model provides a civil aircraft display controller, effectual solved current civil aircraft display controller when placing stability is not high, easily slides, and the casing bottom contacts with placing the face when placing, and the bottom radiating efficiency is low, and when not using, the front end easily falls the ash, is unfavorable for the problem of use.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model comprises a controller body, a shell, a convex edge, a control panel, a slide block, a vertical support block, a horizontal support block, an anti-skid rubber pad, a fixing bolt, a protection mechanism, a square block, a protective cover, a moving groove, a threaded hole, a support rod, a roller and a sliding groove, wherein the controller body comprises a shell arranged outside, the convex edge is arranged at the edge of one end of the shell, the control panel is arranged at one side of the front end of the shell, the slide block is arranged at both ends of the bottom of the shell, the vertical support block is sleeved on the slide block, the horizontal support block is connected at the inner side of the vertical support block, the anti-skid rubber pad is embedded at the bottom of the horizontal support block, the sliding groove is arranged at the top of the vertical support block corresponding to the position of the slide block, the slide block is inserted in the, the both ends at the casing top are fixed to the square, and the visor is installed to the inboard of square, and the shifting chute has been seted up to the inboard of square, and the both ends of protection bottom of the cover all set up threaded hole, and the internally mounted of screw hole has the bracing piece, and the gyro wheel is installed to the one end of bracing piece.

Preferably, the position of the supporting rod corresponding to the threaded hole is a threaded rod.

Preferably, the vertical supporting block is provided with a threaded hole at a position corresponding to the fixing bolt.

Preferably, the number of the fixing bolts is three.

Preferably, the protective cover is a member made of a transparent material.

The utility model discloses novel structure, think about ingeniously, place stability height, the radiating efficiency is high, and when not using, can protect the casing front end, is favorable to using.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention. In the drawings:

fig. 1 is a schematic three-dimensional structure of the present invention;

FIG. 2 is a schematic diagram of the three-dimensional structure of the square block of the present invention;

FIG. 3 is a schematic diagram of the three-dimensional structure of the vertical supporting block of the present invention;

FIG. 4 is a schematic view of a three-dimensional structure of the protective cover of the present invention;

reference numbers in the figures: 1. a controller body; 2. a housing; 3. a convex edge; 4. a control panel; 5. a slider; 6. a vertical supporting block; 7. a cross support block; 8. an anti-skid rubber pad; 9. fixing the bolt; 10. a protection mechanism; 11. a square block; 12. a protective cover; 13. a moving groove; 14. a threaded hole; 15. a support bar; 16. a roller; 17. a chute.

Detailed Description

The following describes the present invention in further detail with reference to the accompanying fig. 1-4.

Embodiment one, given by fig. 1-4, the utility model provides a civil aircraft display controller, which comprises a controller body 1, a housing 2, a convex edge 3, a control panel 4, a slider 5, a vertical support block 6, a horizontal support block 7, an antiskid rubber pad 8, a fixing bolt 9, a protection mechanism 10, a square block 11, a protective cover 12, a moving groove 13, a threaded hole 14, a support rod 15, a roller 16 and a sliding groove 17, wherein the controller body 1 comprises the housing 2 arranged outside, the convex edge 3 is arranged at one end edge of the housing 2, the control panel 4 is arranged at one side of the front end of the housing 2, the sliders 5 are arranged at two ends of the bottom of the housing 2, the vertical support block 6 is sleeved on the sliders 5, the horizontal support block 7 is connected to the inner side of the vertical support block 6, the antiskid rubber pad 8 is embedded in the bottom of the horizontal support block 7, the sliding groove 17 is arranged at the position, slider 5 pegs graft in spout 17 and is fixed through fixing bolt 9, protection machanism 10 is installed on the top of casing 2, protection machanism 10 includes square piece 11, visor 12, shifting chute 13, screw hole 14, bracing piece 15 and gyro wheel 16, square piece 11 is fixed at the both ends at casing 2 top, visor 12 is installed to square piece 11's inboard, shifting chute 13 has been seted up to square piece 11's inboard, screw hole 14 has all been seted up at the both ends of visor 12 bottom, the internally mounted of screw hole 14 has bracing piece 15, gyro wheel 16 is installed to the one end of bracing piece 15.

The position of the support rod 15 corresponding to the threaded hole 14 is a threaded rod, so that the support rod 15 can be conveniently installed and fixed.

The vertical supporting block 6 is provided with a threaded hole at the position corresponding to the fixing bolt 9, so that the fixing bolt 9 can be conveniently installed and fixed.

The number of the fixing bolts 9 is three, so that the fixing stability is improved.

The protective cover 12 is a transparent member, which facilitates the installation and use of the protective cover 12.

The utility model discloses during the installation, peg graft in the spout 17 on erecting supporting shoe 6 with the slider 5 of 2 bottoms of casing, and screw three fixing bolt 9 and can accomplish casing 2 fixed, after the installation is accomplished, anti-skidding rubber pad 8 that 7 bottoms of cross-brace piece embedding set up makes controller body 1 stability high after placing, difficult slip, and when placing, 2 bottoms of casing do not with place the face direct contact, can make casing 2's bottom radiating efficiency high like this, when stacking simultaneously, casing 2 can not the mutual contact, can not damage casing 2, be favorable to the use of controller body 1, and simultaneously, controller body 1 is when not using, with visor 12 under the cooperation of gyro wheel 16 with shifting chute 13, slide visor 12 to the front end, turn down visor 12 again, visor 12 can protect the front end of casing 2, be favorable to using.

The utility model discloses novel structure, think about ingeniously, place stability height, the radiating efficiency is high, and when not using, can protect 2 front ends of casing, is favorable to using.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A civil aircraft display controller comprises a controller body (1), a shell (2), convex edges (3), a control panel (4), a sliding block (5), vertical supporting blocks (6), transverse supporting blocks (7), anti-skid rubber pads (8), fixing bolts (9), a protection mechanism (10), square blocks (11), a protective cover (12), a moving groove (13), a threaded hole (14), a supporting rod (15), rollers (16) and sliding grooves (17), and is characterized in that the controller body (1) comprises the shell (2) which is arranged outside, the convex edges (3) are arranged at the edge of one end of the shell (2), the control panel (4) is arranged at one side of the front end of the shell (2), the sliding blocks (5) are arranged at two ends of the bottom of the shell (2), the vertical supporting blocks (6) are sleeved on the sliding blocks (5), the transverse supporting blocks (7) are connected to the inner side of the vertical supporting blocks (6, the bottom of the transverse supporting block (7) is embedded with an anti-skid rubber pad (8), the top of the vertical supporting block (6) is provided with a sliding groove (17) corresponding to the position of the sliding block (5), the sliding block (5) is inserted in the sliding groove (17) and fixed through a fixing bolt (9), the top end of the shell (2) is provided with a protection mechanism (10), the protection mechanism (10) comprises a square block (11), a protective cover (12) and a moving groove (13), screw hole (14), bracing piece (15) and gyro wheel (16), square piece (11) are fixed at the both ends at casing (2) top, and visor (12) are installed to the inboard of square piece (11), and shifting chute (13) have been seted up to the inboard of square piece (11), and screw hole (14) have all been seted up at the both ends of visor (12) bottom, and the internally mounted of screw hole (14) has bracing piece (15), and gyro wheel (16) are installed to the one end of bracing piece (15).

2. The civil aircraft display controller according to claim 1, wherein the support rod (15) is a threaded rod corresponding to the threaded hole (14).

3. The civil aircraft display controller according to claim 1, wherein the vertical support block (6) is provided with a threaded hole at a position corresponding to the fixing bolt (9).

4. Civil aircraft display controller according to claim 1, characterised in that the number of fixing bolts (9) installed is three.

5. A civil aircraft display controller according to claim 1, characterised in that the protective cover (12) is a member of transparent material.