CN111645869A - Anti-atomization instrument panel for general aircraft - Google Patents
Anti-atomization instrument panel for general aircraft Download PDFInfo
- Publication number
- CN111645869A CN111645869A CN202010315829.6A CN202010315829A CN111645869A CN 111645869 A CN111645869 A CN 111645869A CN 202010315829 A CN202010315829 A CN 202010315829A CN 111645869 A CN111645869 A CN 111645869A
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- instrument
- installation chassis
- front surface
- panel
- general
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- 238000000889 atomisation Methods 0.000 title abstract description 5
- 238000009434 installation Methods 0.000 claims abstract description 44
- 238000007789 sealing Methods 0.000 claims abstract description 30
- 238000007790 scraping Methods 0.000 claims abstract description 16
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 16
- 230000005540 biological transmission Effects 0.000 claims description 44
- 239000003665 fog water Substances 0.000 claims description 7
- 238000012546 transfer Methods 0.000 claims description 7
- 210000001503 joint Anatomy 0.000 claims description 6
- 230000007246 mechanism Effects 0.000 claims description 5
- 239000004020 conductor Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 10
- 238000012423 maintenance Methods 0.000 abstract description 9
- 230000008439 repair process Effects 0.000 abstract description 8
- 239000003595 mist Substances 0.000 abstract description 5
- 239000003897 fog Substances 0.000 description 7
- 230000009471 action Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Images
Classifications
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- 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
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- 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
- B64D43/02—Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
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- 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
- B64D47/00—Equipment not otherwise provided for
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Instrument Panels (AREA)
Abstract
The invention discloses an anti-atomization instrument panel for a general airplane, which comprises an instrument main panel, wherein an installation chassis is movably arranged on the front surface of the instrument main panel, an instrument shell is fixedly embedded and installed on the front surface of the installation chassis, a transparent sealing cover is fixedly covered and installed on the front surface of the installation chassis, a mist scraping water sheet frame is movably installed on the front surface of the transparent sealing cover, a starting key hole is formed in one side, located on the installation chassis, of the front surface of the instrument main panel, and a motor switch is fixedly installed on the other side, located on the starting key hole, of the front surface of the instrument main panel. The anti-fogging instrument panel for the general airplane can facilitate later maintenance and repair of the instrument panel, can maintain other rear control elements, reduces troubles brought by disassembly during maintenance and repair, can enable the rubber scraper to scrape off fog on the surface of the transparent sealing cover, achieves the effect of quick demisting, and can prevent danger caused by the fact that the instrument panel cannot be checked in time.
Description
Technical Field
The invention relates to the field of instrument panels, in particular to an anti-atomization instrument panel for a general airplane.
Background
The flight instrument is an instrument for indicating the motion parameters of the airplane in flight, the flight state parameters comprise flight height, flight speed and acceleration, attitude angle and attitude angular velocity, and the flight instrument mainly comprises: the altimeter, airspeed meter, Mach number meter, lifting speed meter, horizon meter, turning sideslip meter, ground speed drift angle indicator, etc. the flying altitude refers to the vertical distance of the aircraft gravity center relative to a certain reference plane, the measuring instrument is called altimeter, mainly includes two kinds of air pressure type and radio type, the flying speed of the aircraft mainly includes airspeed and lifting speed, the airspeed refers to the current flying speed of the aircraft relative to the air, the measuring instrument is called airspeed meter, the lifting speed refers to the moving speed component of the aircraft gravity center along the ground vertical direction, the measuring instrument is called lifting speed meter, the measuring purpose is to ensure the aircraft horizontal flight, the attitude instrument of the aircraft includes horizon meter, turning sideslip meter, etc. which are designed by using the gyro principle, the gyro is a device capable of keeping the self-rotating shaft unchanged, when the rotor rotates at high speed, the gyro rotating shaft always faces the earth, when the attitude of the, the gyroscope can sense in time and measure corresponding changes, has good monitoring and displaying effects, is low in power consumption and can be widely applied to the field of aviation;
however, the existing instrument panel for the airplane has certain disadvantages when in use, and when the internal temperature is higher due to the influence of weather in use, fog is easy to be atomized and attached to the surface of the instrument panel, so that a pilot cannot check the fog in time, and the trouble of wiping the fog one by one is avoided, accidents are easy to occur under some emergency situations or in bad weather flight, and in addition, when in maintenance and overhaul, the instrument panel needs to be subjected to complex disassembly and assembly processes, so that time is wasted and a navigation process is delayed.
Disclosure of Invention
The invention mainly aims to provide an anti-atomization instrument panel for a general airplane, which can effectively solve the problems in the background technology.
In order to achieve the purpose, the invention adopts the technical scheme that:
the utility model provides a general aircraft is with anti-fogging panel board, includes the instrument master, the front surface movable mounting of instrument master has an installation chassis, the front fixed surface of installation chassis inlays to establish and installs instrument shell, the front fixed surface cover of installation chassis establishes installs transparent sealed cowling, the front surface movable mounting of transparent sealed cowling has the water film frame of scraping fog, one side that the front surface of instrument master is located the installation chassis is equipped with the start key hole, the front surface of instrument master is located the last other side fixed mounting who starts the key hole and has motor switch, the front surface of instrument master is close to the equal fixed mounting in upper surface and both sides border position and shelters from the border board.
Preferably, the installation chassis includes fixed lock, hinge, rubber gasket, sealed fixture block and No. two rubber gaskets, the front surface of installation chassis is close to upper surface border position fixed mounting and has fixed lock, the lower surface border position fixed mounting on installation chassis has the hinge, the rear surface of installation chassis is close to both sides and the equal fixed mounting of upper surface border position has a rubber gasket, the rear surface of installation chassis is located lower surface border position fixed mounting and has sealed fixture block, the front surface fixed mounting of sealed fixture block has No. two rubber gaskets.
Preferably, the sealing fixture block forms a seal with the instrument main disc through a second rubber gasket, the mounting chassis forms a seal with the instrument main disc through a first rubber gasket, the mounting chassis is movably connected with the instrument main disc through a hinge, and the mounting chassis is connected and locked with the instrument main disc through a fixing lock.
Preferably, the rear surface of the instrument shell is fixedly connected with a spiral wire, and the outer surface of the instrument shell is in sealing butt joint with the installation chassis through a sealing ring.
Preferably, the fog-scraping water sheet frame comprises a first rotating shaft, a first connecting sheet, a transmission rod, a second rotating shaft, a second connecting sheet, a third rotating shaft, an output shaft, a fixing screw, a transmission turbine, a power motor, a transmission worm and a rubber scraper, the lower end of the fog-scraping water sheet frame is fixedly connected with the first rotating shaft, the rear surface of the fog-scraping water sheet frame is fixedly provided with the rubber scraper, the other end of the first rotating shaft is fixedly provided with the first connecting sheet, the lower end of the first connecting sheet is movably connected with the transmission rod, the surface of the transmission rod is fixedly provided with the second rotating shaft near one end, the transmission rod is movably connected with the second connecting sheet near the other end, the surface of the transmission rod is fixedly provided with the third rotating shaft near the other end, the upper end of the second connecting sheet is fixedly connected with the output shaft, and the other end of the output, the surface of the second connecting piece is fixedly and spirally provided with a fixing screw, the surface of the transmission worm wheel is movably provided with a transmission worm, and one end of the transmission worm is movably connected with a power motor.
Preferably, a pivot passes through bearing frame and instrument master swing joint, a connection piece passes through No. two pivots and transfer line swing joint, the transfer line passes through No. three pivots and No. two connection piece swing joint, No. two connection pieces pass through the one end fixed connection of set screw and output shaft, scrape the one end fixed connection of fog water piece frame through connecting screw and a pivot, motor power passes through output and transmission worm swing joint, motor power's fixed surface installs radiating fin.
Preferably, the number of the meter shells is eight, the meter shells are uniformly distributed on the surface of the mounting base plate, and the meter shells are electrically connected with the meter output mechanism through spiral leads.
Preferably, the front surface of the instrument main panel is provided with a screw interface, and the instrument main panel passes through the screw interface through screws and is fixedly connected with the aircraft cockpit.
Compared with the prior art, the invention has the following beneficial effects:
according to the invention, through the arranged installation chassis, the installation chassis is opened through the hinge linkage, so that a spiral wire at the rear part of the instrument shell can be connected, and when the installation chassis is closed after connection, the installation chassis and the instrument main disk can be in sealed butt joint under the sealing action of the first rubber gasket and the second rubber gasket, so that the arranged installation chassis can facilitate later maintenance and repair of the instrument panel, and can maintain other rear control elements, and the trouble caused by disassembly during maintenance and repair is reduced;
through the fog water piece frame of scraping that sets up, it is rotatory that the fog water piece frame passes through motor power and drives the transmission worm, the transmission worm drives the transmission turbine rotation again, thereby reach speed reduction and the effect of increase torque force, pivoted torque force will drive the output shaft rotatory this moment, the output shaft drives the connection piece rotation No. two again, then drive the push-and-pull about the transfer line under the rotation of No. three pivots, the transfer line drives the connection piece No. one again through No. two pivots, make a connection piece swing under the rotation of a pivot, drive simultaneously and scrape the front surface swing of fog water piece frame at transparent sealing cover, thereby make the rubber doctor-bar strike off the fog water that goes the transparent sealing cover surface, reach the effect of quick defogging, like this alright prevent because of can't in time look over the danger.
Drawings
FIG. 1 is a schematic view of the overall structure of an anti-fogging instrument panel for a general-purpose aircraft according to the present invention;
FIG. 2 is a top view of a transmission mechanism of a water scraping frame of an anti-fogging instrument panel for a general-purpose aircraft according to the present invention;
FIG. 3 is a front view of a transmission mechanism of a wiper blade holder of an anti-fogging instrument panel for a general-purpose aircraft according to the present invention;
FIG. 4 is a partial cross-sectional view of an anti-fogging instrument panel for a general-purpose aircraft according to the present invention;
fig. 5 is a partial cross-sectional view of a mounting base plate and transparent sealing cover of an anti-fogging instrument panel for a general-purpose aircraft according to the present invention.
In the figure: 1. an instrument main panel; 2. installing a chassis; 201. fixing a lock; 202. a hinge; 203. a first rubber gasket; 204. sealing the clamping block; 205. a second rubber gasket; 3. a meter housing; 301. a helical wire; 4. a transparent sealing cover; 5. a mist scraping water sheet rack; 501. a first rotating shaft; 502. a first connecting sheet; 503. a transmission rod; 504. a second rotating shaft; 505. a second connecting sheet; 506. a third rotating shaft; 507. an output shaft; 508. a set screw; 509. a drive turbine; 5010. a power motor; 5011. a drive worm; 5012. a rubber blade; 6. starting a key hole; 7. a motor switch; 8. and an edge shielding plate.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "rear", "both ends", "one end", "the other end", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, such as "connected," which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1-5, an anti-fogging instrument panel for a general airplane comprises an instrument main panel 1, wherein an installation chassis 2 is movably installed on the front surface of the instrument main panel 1, an instrument shell 3 is fixedly embedded and installed on the front surface of the installation chassis 2, a transparent sealing cover 4 is fixedly covered and installed on the front surface of the installation chassis 2, a mist-scraping water sheet frame 5 is movably installed on the front surface of the transparent sealing cover 4, a starting key hole 6 is arranged on one side, located on the installation chassis 2, of the front surface of the instrument main panel 1, a motor switch 7 is fixedly installed on the opposite side, located on the starting key hole 6, of the front surface of the instrument main panel 1, and shielding edge plates 8 are fixedly installed on the positions, close to the upper surface and the edges of the two sides, of the;
the mounting chassis 2 comprises a fixed lock 201, a hinge 202, a first rubber gasket 203, a sealing fixture block 204 and a second rubber gasket 205, the fixed lock 201 is fixedly mounted on the edge position of the front surface of the mounting chassis 2 close to the upper surface, the hinge 202 is fixedly mounted on the edge position of the lower surface of the mounting chassis 2, the first rubber gasket 203 is fixedly mounted on the edge position of the rear surface of the mounting chassis 2 close to the two sides and the upper surface, the sealing fixture block 204 is fixedly mounted on the edge position of the rear surface of the mounting chassis 2 close to the lower surface, and the second rubber gasket 205 is fixedly mounted on the front surface of the sealing fixture block 204; the sealing fixture block 204 is sealed with the instrument main disc 1 through a second rubber gasket 205, the mounting chassis 2 is sealed with the instrument main disc 1 through a first rubber gasket 203, the mounting chassis 2 is movably connected with the instrument main disc 1 through a hinge 202, the mounting chassis 2 is connected and locked with the instrument main disc 1 through a fixing lock 201, when the mounting chassis 2 is closed, the mounting chassis 2 can be in sealing butt joint with the instrument main disc 1 under the sealing effect of the first rubber gasket 203 and the second rubber gasket 205, the mounting chassis 2 arranged in such a way can facilitate later maintenance and repair of the instrument panel, and can maintain other control elements at the back, thereby reducing the trouble caused by disassembly during maintenance and repair; the rear surface of the instrument shell 3 is fixedly connected with a spiral lead 301, and the outer surface of the instrument shell 3 is in sealing butt joint with the installation chassis 2 through a sealing ring; the fog-wiping water sheet rack 5 comprises a first rotating shaft 501, a first connecting piece 502, a transmission rod 503, a second rotating shaft 504, a second connecting piece 505, a third rotating shaft 506, an output shaft 507, a fixing screw 508, a transmission turbine 509, a power motor 5010, a transmission worm 5011 and a rubber blade 5012, wherein the first rotating shaft 501 is fixedly connected and installed at the lower end of the fog-wiping water sheet rack 5, the rubber blade 5012 is fixedly installed on the rear surface of the fog-wiping water sheet rack 5, the first connecting piece 502 is fixedly installed at the other end of the first rotating shaft 501, the transmission rod 503 is movably connected and installed at the lower end of the first connecting piece 502, the second rotating shaft 504 is fixedly installed at the position, close to one end, of the transmission rod 503, the second connecting piece 505 is movably connected and installed at the other end, the third rotating shaft 506 is fixedly installed at the position, close to the other end, of the surface of, the other end of the output shaft 507 is fixedly connected with a transmission worm wheel 509, the surface of the second connecting piece 505 is fixedly and spirally provided with a fixing screw 508, the surface of the transmission worm wheel 509 is movably provided with a transmission worm 5011, one end of the transmission worm 5011 is movably connected with a power motor 5010, the power motor 5010 drives the transmission worm 5011 to rotate when working, and the transmission worm 5011 drives the transmission worm wheel 509 to rotate, so that the effects of reducing speed and increasing torque are achieved; the first rotating shaft 501 is movably connected with the instrument main disc 1 through a bearing seat, the first connecting piece 502 is movably connected with the driving rod 503 through a second rotating shaft 504, the driving rod 503 is movably connected with the second connecting piece 505 through a third rotating shaft 506, the second connecting piece 505 is fixedly connected with one end of the output shaft 507 through a fixing screw 508, the mist scraping water sheet frame 5 is fixedly connected with one end of the first rotating shaft 501 through a connecting screw, the power motor 5010 is movably connected with the transmission worm 5011 through an output end, the surface of the power motor 5010 is fixedly provided with radiating fins, and the power motor 5010 drives the mist scraping water sheet frame 5 to swing on the front surface of the transparent sealing cover 4, so that the rubber scraper 5012 scrapes off mist on the surface of the transparent sealing cover 4, the effect of quick demisting is achieved, and the danger caused by the fact that a dial cannot be checked in time can; the number of the meter shells 3 is eight, the meter shells are uniformly distributed on the surface of the mounting base plate 2, and the meter shells 3 are electrically connected with a meter output mechanism through spiral leads 301; the front surface of the instrument main panel 1 is provided with a screw interface, and the instrument main panel 1 penetrates through the screw interface through screws to be fixedly connected with the aircraft cockpit.
It should be noted that the invention is an anti-fogging instrument panel for a general-purpose aircraft, when in use, firstly, the instrument main panel 1 is fixedly embedded and installed at the front end of an aircraft cockpit, after the fixation, a specific key is inserted into a fixed lock 201 for unlocking, so that an installation chassis 2 is opened through linkage of a hinge 202, thus a spiral conducting wire 301 at the back of an instrument shell 3 can be connected, the installation chassis 2 is closed after the connection, and simultaneously, the installation chassis 2 and the instrument main panel 1 can be in sealing butt joint under the sealing action of a first rubber gasket 203 and a second rubber gasket 205, the installation chassis 2 arranged in this way can facilitate the later maintenance and repair of the instrument panel, and can maintain other control elements at the back, thereby reducing the trouble brought by disassembly during the maintenance and repair, when the instrument main panel 1 and the installation chassis 2 are installed, a pilot can use the key to be inserted into a starting key hole 6 to start the aircraft during use, during the airplane driving, a pilot needs to check the corresponding indicated value on the instrument shell 3 all the time, and in a cockpit, particularly in winter, a layer of fog is easily covered on the transparent cover of the instrument shell 3, so that the value cannot be visually and accurately seen, at the moment, the pilot can manually operate the motor switch 7, so that the power motor 5010 drives the transmission worm 5011 to rotate, the transmission worm 5011 drives the transmission turbine 509 to rotate, the effect of reducing the speed and increasing the torque force is achieved, the rotating torque force drives the output shaft 507 to rotate, the output shaft 507 drives the second connecting piece 505 to rotate, then the driving rod 503 is driven to push and pull left and right under the rotation of the third rotating shaft 506, the driving rod 503 drives the first connecting piece 502 through the second rotating shaft 504, so that the first connecting piece 502 swings under the rotation of the first rotating shaft 501, and simultaneously drives the fog-scraping film frame 5 to swing on the front surface of the transparent sealing cover, thereby make rubber doctor 5012 strike off the fog on transparent sealing boot 4 surface, reach the effect of quick defogging, alright prevent like this because of can't in time look over the danger that the dial plate brought, alright close motor switch 7 after the fog on transparent sealing boot 4 surface strikes off.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. The utility model provides a general aircraft is with preventing atomizing panel board which characterized in that: including instrument master (1), the preceding surface movable mounting of instrument master (1) has installation chassis (2), the front fixed surface of installation chassis (2) inlays to establish and installs instrument shell (3), the front fixed surface cover of installation chassis (2) establishes installs transparent sealed cowling (4), the front surface movable mounting of transparent sealed cowling (4) has the fog water film frame (5) of scraping, one side that the front surface of instrument master (1) is located installation chassis (2) is equipped with starts key hole (6), the front surface of instrument master (1) is located the last other side fixed mounting who starts key hole (6) and has motor switch (7), the front surface of instrument master (1) is close to the equal fixed mounting in upper surface and both sides border position and shelters from border board (8).
2. The anti-fogging instrument panel for general-purpose aircraft according to claim 1, wherein: installation chassis (2) are including fixed lock (201), hinge (202), rubber gasket (203), sealed fixture block (204) and No. two rubber gaskets (205), the front surface of installation chassis (2) is close to upper surface border position fixed mounting and has fixed lock (201), the lower surface border position fixed mounting of installation chassis (2) has hinge (202), the rear surface of installation chassis (2) is close to both sides and the equal fixed mounting of upper surface border position has rubber gasket (203), the rear surface of installation chassis (2) is located lower surface border position fixed mounting and has sealed fixture block (204), the front surface fixed mounting of sealed fixture block (204) has No. two rubber gaskets (205).
3. The anti-fogging instrument panel for general-purpose aircraft according to claim 2, wherein: sealed fixture block (204) form sealedly through No. two rubber gasket (205) and instrument master (1), installation chassis (2) form sealedly through a rubber gasket (203) and instrument master (1), installation chassis (2) are through hinge (202) and instrument master (1) swing joint, installation chassis (2) are connected the locking through fixed lock (201) and instrument master (1).
4. The anti-fogging instrument panel for general-purpose aircraft according to claim 1, wherein: the rear surface fixed connection of instrument shell (3) installs spiral conductor (301), the surface of instrument shell (3) passes through the sealed butt joint installation of sealing washer and installation chassis (2).
5. The anti-fogging instrument panel for general-purpose aircraft according to claim 1, wherein: the fog-scraping water sheet rack (5) comprises a first rotating shaft (501), a first connecting piece (502), a transmission rod (503), a second rotating shaft (504), a second connecting piece (505), a third rotating shaft (506), an output shaft (507), a fixing screw (508), a transmission turbine (509), a power motor (5010), a transmission worm (5011) and a rubber scraper (5012), wherein the first rotating shaft (501) is fixedly connected and installed at the lower end of the fog-scraping water sheet rack (5), the rubber scraper (5012) is fixedly installed on the rear surface of the fog-scraping water sheet rack (5), the first connecting piece (502) is fixedly installed at the other end of the first rotating shaft (501), the transmission rod (503) is installed at the lower end of the first connecting piece (502) in a movable connection mode, the second rotating shaft (504) is fixedly installed on the surface of the transmission rod (503) close to one end position, and the second connecting piece (505) is installed on the transmission rod (503, the surface of transfer line (503) is close to another end position fixed mounting and has No. three pivot (506), and the upper end fixed surface of No. two connection pieces (505) is connected and is installed output shaft (507), transmission turbine (509) are installed to the other end fixed connection of output shaft (507), set screw (508) are installed to the fixed surface spiral of No. two connection pieces (505), the surface movable mounting of transmission turbine (509) has transmission worm (5011), the one end swing joint of transmission worm (5011) has motor power (5010).
6. The anti-fogging instrument panel for general-purpose aircraft according to claim 5, wherein: a pivot (501) is through bearing frame and instrument main board (1) swing joint, a connection piece (502) is through No. two pivot (504) and transfer line (503) swing joint, transfer line (503) is through No. three pivot (506) and No. two connection piece (505) swing joint, No. two connection piece (505) are through the one end fixed connection of set screw (508) and output shaft (507), scrape the one end fixed connection of fog water piece frame (5) through connecting screw and a pivot (501), motor power (5010) is through output and transmission worm (5011) swing joint, the fixed surface of motor power (5010) installs radiating fin.
7. The anti-fogging instrument panel for general-purpose aircraft according to claim 4, wherein: the number of the instrument shells (3) is eight, the instrument shells are uniformly distributed on the surface of the installation chassis (2), and the instrument shells (3) are electrically connected with the instrument output mechanism through spiral leads (301).
8. The anti-fogging instrument panel for general-purpose aircraft according to claim 5, wherein: the front surface of the instrument main panel (1) is provided with a screw interface, and the instrument main panel (1) penetrates through the screw interface through screws to be fixedly connected with the aircraft cockpit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010315829.6A CN111645869B (en) | 2020-04-21 | 2020-04-21 | Anti-atomization instrument panel for general aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010315829.6A CN111645869B (en) | 2020-04-21 | 2020-04-21 | Anti-atomization instrument panel for general aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN111645869A true CN111645869A (en) | 2020-09-11 |
| CN111645869B CN111645869B (en) | 2023-07-18 |
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| CN205748531U (en) * | 2016-05-17 | 2016-11-30 | 华北理工大学 | Antifog flow meter |
| CN206696619U (en) * | 2017-04-18 | 2017-12-01 | 福州珂麦表业有限公司 | A kind of wrist-watch of automatic defrosting |
| CN209290179U (en) * | 2018-07-13 | 2019-08-23 | 浙江金旭汽车仪表有限公司 | A kind of automobile instrument panel except fog |
| CN110085279A (en) * | 2019-05-22 | 2019-08-02 | 诸暨市火鸟工业设计工作室 | A kind of Intelligent instrument panel with anti-pollution function |
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