CN113859558B - Foreign trade aircraft instrument board layout structure - Google Patents
Foreign trade aircraft instrument board layout structure Download PDFInfo
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- CN113859558B CN113859558B CN202111317246.8A CN202111317246A CN113859558B CN 113859558 B CN113859558 B CN 113859558B CN 202111317246 A CN202111317246 A CN 202111317246A CN 113859558 B CN113859558 B CN 113859558B
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- instrument board
- display
- main instrument
- fixed
- aircraft
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- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 10
- 239000001301 oxygen Substances 0.000 claims abstract description 10
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 abstract description 11
- 230000000694 effects Effects 0.000 abstract description 3
- 230000006870 function Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 230000036632 reaction speed Effects 0.000 description 4
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 210000003195 fascia Anatomy 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000004973 liquid crystal related substance Substances 0.000 description 1
- 230000009023 proprioceptive sensation Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Instrument Panels (AREA)
Abstract
The invention discloses a foreign trade aircraft instrument panel layout structure, which comprises a support arm, a main instrument panel, a left auxiliary instrument panel, a support, a right auxiliary instrument panel, a light shield, an upper display, an alarm lamp box, a left display, a landing gear comprehensive control panel, a certain function switch control box, an oxygen flow indicator, a right display, a middle display and a signal lamp box. The invention improves the man-machine effect of the cockpit, has convenient installation and disassembly and simple structure, and is convenient for pilots to watch and operate main display equipment.
Description
Technical Field
The invention relates to a foreign trade aircraft instrument panel layout structure, and belongs to the field of aircraft cabin layout design.
Background
The cockpit is the primary place of activity for pilots to perform flight tasks. Pilots must rely on off-board visual searches, on-board information displays, and on their own proprioception to obtain various types of flight information, while in aircraft cabins, pilots obtain information primarily from the aircraft dashboards and various displays. With the continuous improvement of the performance of the aircraft, the amount of flight information transmitted to the pilot through the instrument panel is increased rapidly, and the time for the pilot to call and judge certain information is relatively reduced, so that the instrument panel layout and structure of the aircraft are reasonably designed, the working efficiency of the pilot is related, and the pilot's piloting operation on the aircraft, the success and failure of the flight task and the safety of the aircraft are directly influenced.
Disclosure of Invention
Aiming at the technical problems, the invention provides a foreign trade aircraft instrument board layout structure which is simple in structure and convenient to install and detach, can enable a pilot to quickly look up various information without pressing keys, is a breakthrough in man-machine interaction of a fighter aircraft, can greatly improve the reaction speed of the pilot, and can enhance the fighter capability of the fighter aircraft in a phase change mode.
The technical scheme of the invention is as follows:
a foreign trade aircraft instrument panel layout structure comprises a support arm, a main instrument panel, a left auxiliary instrument panel, a support, a right auxiliary instrument panel, a light shield, an upper display, an alarm lamp box, a left display, a landing gear comprehensive control panel, a certain function switch control box, an oxygen flow indicator, a right display, a middle display and a signal lamp box; one end of the support arm is connected with the main instrument board, and the other end of the support arm is connected with the machine body; the upper end of the left auxiliary instrument board is connected with the lower end of the main instrument board, and the lower end of the left auxiliary instrument board is connected with the machine body; one end of the support is connected with the main instrument panel, and the other end of the support is connected with the machine body; the upper end of the right auxiliary instrument board is connected with the lower end of the main instrument board, and the lower end of the right auxiliary instrument board is connected with the machine body; the light shield is fixed at the upper end of the main instrument board.
Further, in order to ensure that a pilot can quickly look for various information without pressing a plurality of keys, the upper display is fixed at the upper end of the main instrument board, the left display is fixed at the left end of the main instrument board, the middle display is fixed at the middle end of the main instrument board, the right display is fixed at the right end of the main instrument board, the certain function switch control box is fixed at the lower end of the main instrument board, the warning lamp box is fixed at the left end of the main instrument board and is positioned at the upper end of the left display, and the signal lamp box is fixed at the right end of the main instrument board and is positioned at the upper end of the right display.
Further, to ensure that the pilot's reaction speed is raised and space is saved, the upper display is sized 8 x 6 inches; the left and right displays are 6 x 8 inches in size; the middle display is 5 x 7 inches in size.
Further, in order to facilitate the installation and fixation of various electromechanical devices, a plurality of device mounting holes are formed in the main instrument panel, the left auxiliary instrument panel and the right auxiliary instrument panel.
Further, the landing gear comprehensive control board is fixed on the left auxiliary instrument board; the oxygen indicator is fixed on the right auxiliary instrument panel.
Further, in order to ensure that the equipment installed on the main instrument panel is contained in the optimal vision area of the pilot, the installation plane of the main instrument panel is inclined forward by 12 degrees and perpendicular to the normal vision line of the pilot, the installation planes of the left auxiliary instrument panel and the right auxiliary instrument panel are designed to be inclined forward by 12 degrees and inclined inwards by 15 degrees for the convenience of the pilot operation and the installation and disassembly of ground staff, and simultaneously, the left auxiliary instrument panel and the right auxiliary instrument panel are respectively designed to be provided with a tripod for positioning, the upper tripod is connected with the main instrument panel through a screw and a supporting plate nut, and the lower two foot frames are connected with an aircraft console through a screw and a supporting plate nut.
Furthermore, in order to facilitate the installation and the disassembly of the shade, the shade is fixed at the upper end of the main instrument board through screws and supporting plate nuts.
Further, in order to ensure that the main instrument panel does not move in the direction of the flight, the side surfaces of the support arms are riveted to the main instrument panel by rivets, and the front surfaces are connected with the aircraft bevel frame by bolts and nuts.
Further, to ensure that the main fascia is not moved in the spanwise direction, the sides of the mount are attached to the main fascia by screws and pallet nuts and the underside is attached to the aircraft frame rail by bolts and nuts.
Further, to reduce the number of meters and controllers, the foreign trade aircraft dashboard layout structure employs a "one flat three down" layout.
The invention has the advantages that:
1. the aircraft cockpit is different from the traditional aircraft cockpit with the die box instrument, three displays are adopted for displaying information as required in a concentrated mode, the number of instruments and controllers is reduced, the cockpit space is saved, the cockpit is more attractive and concise, and the psychological habit of pilots is met.
2. The whole instrument board mounting surface adopts an inclined design and is perpendicular to the sight of the pilot, so that the pilot can conveniently and quickly acquire the required information, and the instrument board mounting surface accords with the physiological habit of the pilot;
3. every part of instrument board all can be dismantled, has improved the installation effectiveness of instrument board for ground staff, has reduced the maintenance cycle in instrument board later stage.
Drawings
The invention is described in further detail below with reference to the accompanying drawings.
FIG. 1 is a schematic layout of the present invention;
the figure shows: 1-support arm, 2-main instrument board, 3-left auxiliary instrument board, 4-support, 5-right auxiliary instrument board, 6-light shield, 7-upper display, 8-warning lamp box, 9-left display, 10-landing gear integrated control panel, 11-certain function switch control box, 12-oxygen indicator, 13-right display, 14-middle display, 15-signal lamp box.
Detailed Description
For the purpose of making the technical solution and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the embodiments and the accompanying drawings, wherein the exemplary embodiments of the present invention and the descriptions thereof are used for explaining the present invention, but not limiting the present invention.
Further advantages and effects of the present invention will become apparent to those skilled in the art from the disclosure of the present invention, which is described by the following specific examples.
It should be understood that the structures, proportions, sizes, etc. shown in the drawings are for illustration purposes only and should not be construed as limiting the invention to the extent that it can be practiced, since modifications, changes in the proportions, or adjustments of the sizes, which are otherwise, used in the practice of the invention, are included in the spirit and scope of the invention which is otherwise, without departing from the spirit or scope thereof. Also, the terms such as "upper", "lower", "left", "right", "middle", etc. are used herein for convenience of description, but are not to be construed as limiting the scope of the invention, and the relative changes or modifications are not to be construed as essential to the scope of the invention.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "connected," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
The invention relates to a foreign trade aircraft instrument panel layout structure shown in figure 1, which comprises a support arm 1, a main instrument panel 2, a left auxiliary instrument panel 3, a support 4, a right auxiliary instrument panel 5, a light shield 6, an upper display 7, an alarm lamp box 8, a left display 9, a landing gear integrated control board 10, a certain function switch control box 11, an oxygen indicator 12, a right display 13, a middle display 14 and a signal lamp box 15; one end of the support arm 1 is connected with the main instrument board 2, and the other end is connected with the machine body; the upper end of the left auxiliary instrument panel 3 is connected with the lower end of the main instrument panel 2, and the lower end is connected with the machine body; one end of the support 4 is connected with the main instrument panel 2, and the other end of the support is connected with the machine body; the upper end of the right auxiliary instrument board 5 is connected with the lower end of the main instrument board 2, and the lower end is connected with the machine body; the shade 6 is fixed at the upper end of the main instrument panel 2.
The upper display 7 is fixed at the upper end of the main instrument board 2, the left display 9 is fixed at the left end of the main instrument board 2, the middle display 14 is fixed at the middle end of the main instrument board 2, the right display 13 is fixed at the right end of the main instrument board 2, the certain function switch control box 11 is fixed at the lower end of the main instrument board 2, the alarm lamp box 8 is fixed at the left end of the main instrument board 2 and is positioned at the upper end of the left display 9, and the signal lamp box 15 is fixed at the right end of the main instrument board 2 and is positioned at the upper end of the right display 13, so that a pilot can quickly check various information without pressing keys.
The upper display 7 is 8 x 6 inches in size; the left display 9 and the right display 13 are 6 x 8 inches in size; the size of the mid display 14 is 5 x 7 inches, ensuring pilot reaction speed and space savings.
A plurality of equipment mounting holes are formed in the main instrument panel 2, the left auxiliary instrument panel 3 and the right auxiliary instrument panel 5 so as to facilitate the installation and fixation of various electromechanical equipment.
The landing gear integrated control board 10 is fixed on the left auxiliary instrument board 3; the oxygen indicator 12 is fixed to the right auxiliary instrument panel 5.
The installation of the forward inclination 12 degrees of the main instrument panel 2 is perpendicular to the normal vision of a pilot, so that the equipment installed on the main instrument panel is ensured to be contained in an optimal vision area of the pilot, and the installation of the forward inclination 12 degrees and the inward inclination 15 degrees of the left auxiliary instrument panel 3 and the right auxiliary instrument panel 5 are convenient for the pilot to watch and operate the equipment; the left auxiliary instrument board 3 and the right auxiliary instrument board 5 are connected with the main instrument board 2 through screws and supporting plate nuts on the upper surface and are connected with the aircraft console on the lower surface through screws and supporting plate nuts, and the installation mode is convenient for later maintenance.
The light shield 6 is fixed at the upper end of the main instrument board 2 through screws and supporting plate nuts, harmful light is shielded for a display on the instrument board, a pilot can conveniently watch the display, and meanwhile, the light shield 6 is convenient to install and detach.
The side of the support arm 1 is riveted on the main instrument board 2 through rivets, and the front is connected with an aircraft inclined frame through bolts and nuts, so that the main instrument board 2 is fixed from moving in the direction of the aircraft while the mounting surface of the main instrument board 2 is vertical to the normal vision of a pilot.
The side of the support 4 is connected with the main instrument board 2 through bolts and supporting plate nuts, and the lower side of the support is connected with an aircraft mouth frame beam through bolts and nuts, so that the main instrument board is fixed from moving in the span direction while the mounting surface of the main instrument board 2 is perpendicular to the normal vision of a pilot.
The foreign trade aircraft instrument panel layout structure adopts a 'one-flat-three-down' layout, the mode can enable a pilot to quickly look up various information without pressing keys, the mode is a breakthrough in fighter aircraft man-machine interaction, and the 'one-flat' refers to a head-up display, namely a scientific display in front of the fighter aircraft pilot in a film, which is used for displaying green characters on glass, can freely select and display various information, and can be seen without the need of the pilot to go low, so that the head-up display is called. The three-down display is three multifunctional liquid crystal color displays respectively displaying information such as an electronic level meter, a compass, a radar, a map and the like, and a pilot can see the information when looking down, so that the pilot looks down at the display, the concept of 'one-flat-three-down' is that of 'vitrified cabin', mechanical instruments and buttons are arranged everywhere in the prior aircraft cabin, the operation is complex and difficult, and the pilot is inconvenient to acquire the information. Obviously, the vitrified cabin can greatly improve the reaction speed of pilots, and the fighter capability of the fighter is enhanced by changing the phase.
The invention is realized by the following modes: the support arm 1 is riveted on the main instrument board 2, the light shield 6 is fixed on the main instrument board 2 through screws and supporting plate nuts, the support 4 is fixed on an aircraft frame beam through bolts and nuts, the support arm 1 is fixed on an aircraft inclined frame through bolts and nuts, the left auxiliary instrument board 3 and the right auxiliary instrument board 5 are fixed on the main instrument board 2 and an operation desk through screws and supporting plate nuts, and finally the upper display 7, the alarm lamp box 8, the left display 9, the landing gear comprehensive control board 10, a certain function switch control box 11, the oxygen flow indicator 12, the right display 13, the middle display 14, the signal lamp box 15 and a controller device cable are in butt joint with the aircraft cable, and the corresponding display, the instrument and the controller device are fixed on the instrument board through screws.
It should be noted that 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.
The protection scope of the present invention is not limited to the technical solutions disclosed in the specific embodiments, and any modification, equivalent replacement, improvement, etc. made to the above embodiments according to the technical substance of the present invention falls within the protection scope of the present invention.
Claims (9)
1. A foreign trade aircraft instrument board layout structure which characterized in that: the intelligent oxygen indicator comprises a support arm (1), a main instrument board (2), a left auxiliary instrument board (3), a support (4), a right auxiliary instrument board (5), a light shield (6), an upper display (7), an alarm lamp box (8), a left display (9), a landing gear comprehensive control board (10), a certain function switch control box (11), an oxygen flow indicator (12), a right display (13), a middle display (14) and a signal lamp box (15); one end of the support arm (1) is connected with the main instrument board (2), and the other end of the support arm is connected with the machine body; the upper end of the left auxiliary instrument board (3) is connected with the lower end of the main instrument board (2), and the lower end is connected with the machine body; one end of the support (4) is connected with the main instrument board (2), and the other end of the support is connected with the machine body; the upper end of the right auxiliary instrument board (5) is connected with the lower end of the main instrument board (2), and the lower end is connected with the machine body; the light shield (6) is fixed at the upper end of the main instrument board (2); the upper display (7) is fixed at the upper end of the main instrument board (2), the left display (9) is fixed at the left end of the main instrument board (2), the middle display (14) is fixed at the middle end of the main instrument board (2), the right display (13) is fixed at the right end of the main instrument board (2), the certain function switch control box (11) is fixed at the lower end of the main instrument board (2), the alarm lamp box (8) is fixed at the left end of the main instrument board (2) and is positioned at the upper end of the left display (9), and the signal lamp box (15) is fixed at the right end of the main instrument board (2) and is positioned at the upper end of the right display (13); the main instrument board (2) is installed in a forward tilting mode of 12 degrees and is perpendicular to the normal vision of a pilot.
2. The foreign trade aircraft dashboard layout structure of claim 1, wherein: the upper display (7) has dimensions of 8 x 6 inches; the left display (9) and the right display (13) are 6 x 8 inches in size; the mid display (14) is 5 x 7 inches in size.
3. The foreign trade aircraft dashboard layout structure of claim 1, wherein: a plurality of equipment mounting holes are formed in a main instrument board (2), a left auxiliary instrument board (3) and a right auxiliary instrument board (5).
4. The foreign trade aircraft dashboard layout structure of claim 1, wherein: the landing gear comprehensive control board (10) is fixed on the left auxiliary instrument board (3); the oxygen indicator (12) is fixed on the right auxiliary instrument board (5).
5. The foreign trade aircraft dashboard layout structure of claim 1, wherein: the left auxiliary instrument panel (3) and the right auxiliary instrument panel (5) are installed in a forward inclined mode of 12 degrees and an inward inclined mode of 15 degrees; the upper parts of the left auxiliary instrument board (3) and the right auxiliary instrument board (5) are connected with the main instrument board (2), and the lower parts are connected with the aircraft console.
6. The foreign trade aircraft dashboard layout structure of claim 1, wherein: the light shield (6) is fixed at the upper end of the main instrument board (2).
7. The foreign trade aircraft dashboard layout structure of claim 1, wherein: the side surface of the support arm (1) is fixed on the main instrument board (2), and the front surface is connected with the inclined frame of the airplane.
8. The foreign trade aircraft dashboard layout structure of claim 1, wherein: the side surface of the support (4) is connected with the main instrument board (2), and the lower surface is connected with the aircraft mouth frame beam.
9. The foreign trade aircraft dashboard layout structure according to any one of claims 1-8, wherein: the foreign trade aircraft dashboard layout structure adopts a 'one-flat-three-down' layout.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111317246.8A CN113859558B (en) | 2021-11-09 | 2021-11-09 | Foreign trade aircraft instrument board layout structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111317246.8A CN113859558B (en) | 2021-11-09 | 2021-11-09 | Foreign trade aircraft instrument board layout structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113859558A CN113859558A (en) | 2021-12-31 |
| CN113859558B true CN113859558B (en) | 2023-09-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111317246.8A Active CN113859558B (en) | 2021-11-09 | 2021-11-09 | Foreign trade aircraft instrument board layout structure |
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| CN (1) | CN113859558B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1987006017A1 (en) * | 1986-03-31 | 1987-10-08 | Hughes Aircraft Company | Integrated head-up and panel display unit |
| GB201020865D0 (en) * | 2010-12-09 | 2011-01-26 | Elbit Systems Ltd | An irregularly shaped electronic surface display |
| CN102862675A (en) * | 2011-07-08 | 2013-01-09 | 通用电气公司 | A simplified user interface for an aircraft |
| CN103842253A (en) * | 2011-09-30 | 2014-06-04 | 空中客车营运有限公司 | Aircraft cockpit, in particular the front portion of an aircraft cockpit |
| CN104477396A (en) * | 2007-03-30 | 2015-04-01 | 通用电气航空***有限公司 | Aircraft displays and display arrangements |
| CN108459539A (en) * | 2017-02-22 | 2018-08-28 | 霍尼韦尔国际公司 | Flight deck display system for executing glide-path verification procedure and method |
| CN111216912A (en) * | 2018-11-27 | 2020-06-02 | 庞巴迪公司 | Cockpit base and aircraft with cockpit base |
| CN212243852U (en) * | 2020-05-21 | 2020-12-29 | 成都赫尔墨斯科技股份有限公司 | Display and control system for airplane |
-
2021
- 2021-11-09 CN CN202111317246.8A patent/CN113859558B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1987006017A1 (en) * | 1986-03-31 | 1987-10-08 | Hughes Aircraft Company | Integrated head-up and panel display unit |
| CN104477396A (en) * | 2007-03-30 | 2015-04-01 | 通用电气航空***有限公司 | Aircraft displays and display arrangements |
| GB201020865D0 (en) * | 2010-12-09 | 2011-01-26 | Elbit Systems Ltd | An irregularly shaped electronic surface display |
| GB2486247A (en) * | 2010-12-09 | 2012-06-13 | Elbit Systems Ltd | Electronic display having recess or opening, for use in dashboard or cockpit |
| CN102862675A (en) * | 2011-07-08 | 2013-01-09 | 通用电气公司 | A simplified user interface for an aircraft |
| CN103842253A (en) * | 2011-09-30 | 2014-06-04 | 空中客车营运有限公司 | Aircraft cockpit, in particular the front portion of an aircraft cockpit |
| CN108459539A (en) * | 2017-02-22 | 2018-08-28 | 霍尼韦尔国际公司 | Flight deck display system for executing glide-path verification procedure and method |
| CN111216912A (en) * | 2018-11-27 | 2020-06-02 | 庞巴迪公司 | Cockpit base and aircraft with cockpit base |
| CN212243852U (en) * | 2020-05-21 | 2020-12-29 | 成都赫尔墨斯科技股份有限公司 | Display and control system for airplane |
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| Publication number | Publication date |
|---|---|
| CN113859558A (en) | 2021-12-31 |
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Effective date of registration: 20230626 Address after: 561000 Songqi Town, Anshun economic and Technological Development Zone, Guizhou Province Applicant after: AVIC GUIZHOU AIRPLANE Co.,Ltd. Address before: 561099 Anshun economic and Technological Development Zone, Guizhou Province Applicant before: Guizhou Guifei aircraft design and Research Institute Co.,Ltd. |
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