CN213628648U - Real-time monitoring equipment for airplane information - Google Patents
Real-time monitoring equipment for airplane information Download PDFInfo
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- CN213628648U CN213628648U CN202022442125.3U CN202022442125U CN213628648U CN 213628648 U CN213628648 U CN 213628648U CN 202022442125 U CN202022442125 U CN 202022442125U CN 213628648 U CN213628648 U CN 213628648U
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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Abstract
The utility model discloses a be used for aircraft information real time monitoring equipment, including shell, positioning monitoring subassembly, singlechip and pressure sensor, the mount pad has been placed in the shell, and embedded battery, positioning monitoring subassembly and the singlechip of being fixed with in the mount pad, it has rubber strip and gasbag strip to bond between the bottom of mount pad and the inner wall of shell, and the bottom edge of shell runs through first spring and is fixed with the erection column to the bottom bolted fixation of erection column has pressure sensor, the air intake has been seted up in the outside of shell, the mounting groove has been seted up to the top edge of shell, the top reservation of shell has receive and release the groove, states and receive and release tank bottom hub connection and have electric putter. This be used for aircraft information real time monitoring equipment has good buffering effect, and inside electron device is impaired when avoiding dropping, plays its simultaneously again behind, can expand the use to the solar energy electroplax, protects the solar energy electroplax.
Description
Technical Field
The utility model relates to an information monitoring technology field specifically is a be used for aircraft information real time monitoring equipment.
Background
In an aircraft, a "black box" is generally adopted to monitor information of the aircraft, including operation conditions of the aircraft and positioning information of the aircraft, after the aircraft is crashed, the "black box" falls off, and a location of the aircraft crash needs to be positioned through the positioning information in the "black box", and a device for monitoring the aircraft information in real time, disclosed as (CN 209051598U), includes a support plate and a second carrying handle, a left end of a front surface of the support plate is provided with an interface controller.
The device cushions the protection through the rubber post after dropping, because the device drops from the high altitude, receives the acceleration influence, and it is fast that it drops, only cushions through the rubber post and protects the unable better buffering protection to inside electron device, and the risk that the damage appears is great, and when generating electricity through the solar energy electroplax, the solar energy electroplax is inconvenient receive and releases simultaneously, directly exposes externally, damages easily.
Aiming at the problems, innovative design is urgently needed on the basis of the original airplane information real-time monitoring equipment.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a be used for aircraft information real time monitoring equipment to solve above-mentioned background art and provide some aircraft information real time monitoring equipment, only cushion through the rubber column and protect the unable better buffering protection to inside electron device, the solar energy electroplax is inconvenient receive and releases simultaneously, directly exposes externally, problem easy damage.
In order to achieve the above object, the utility model provides a following technical scheme: a real-time monitoring device for airplane information comprises a shell, a positioning monitoring component, a single chip microcomputer and a pressure sensor, wherein a mounting seat is placed in the shell, a storage battery, the positioning monitoring component and the single chip microcomputer are embedded and fixed in the mounting seat, a rubber strip and an air bag strip are bonded between the bottom of the mounting seat and the inner wall of the shell, a mounting column penetrates through and is fixed at the edge of the bottom of the shell through a first spring, the pressure sensor is fixed at the bottom of the mounting column through a bolt, magnetic blocks are bonded on the outer side of the mounting seat and the side wall of the shell, an air inlet is formed in the outer side of the shell, an air guide sheet is fixed on the outer side of the shell and is positioned above the air inlet, a mounting groove is formed in the edge of the top of the shell, a flexible sheet is connected in the mounting groove through a second spring, a folding and unfolding groove is reserved in the top of the shell, the shaft at the bottom of the retraction groove is connected with an electric push rod, one end of the electric push rod is positioned in the guide groove, and the guide groove is arranged at the bottom of the solar panel.
Preferably, the rubber strips and the air bag strips are distributed in a staggered mode, and the two sides of each rubber strip are designed into arc-shaped concave structures.
Preferably, the mounting posts form an elastic sliding structure with the housing through the first spring, and the number of the mounting posts is 4 symmetrically arranged about the central axis of the housing.
Preferably, the flexible sheets are designed to be of an arc-shaped structure, and 2 flexible sheets are symmetrically arranged on the central axis of the shell.
Preferably, the top of the electric push rod is designed to be a spherical structure, the top of the electric push rod is connected with the guide groove in a sliding mode, and the diameter of the top of the electric push rod is equal to the inner diameter of the guide groove.
Preferably, the magnetic blocks are distributed on the inner wall of the shell and the outer side of the mounting seat in a staggered mode, and the cross sections of the magnetic blocks are designed to be isosceles trapezoid structures.
Compared with the prior art, the beneficial effects of the utility model are that: the device for monitoring the airplane information in real time;
1. through the mounting groove arranged at the top of the shell and the flexible sheet with the arc-shaped structure, when the shell falls, wind enters the mounting groove from the wind guide sheet and the wind inlet, blows the flexible sheet, and is matched with the use of the second spring, so that the flexible sheet can form certain resistance to slow down the falling of the shell;
2. constitute elastic sliding structure between four erection columns through first spring and the shell through setting up, when the shell whereabouts, erection column bottom pressure sensor pressurized, with signal transmission to singlechip, through singlechip control electric putter's operation, the spherical structure at electric putter top slides in the guide slot for the one end perk of solar energy electroplax absorbs solar energy and supplies power, realizes the perk use of solar energy electroplax after the shell reachs ground, effectively protects the solar energy electroplax.
Drawings
FIG. 1 is a schematic view of a front cross-sectional structure of the present invention;
FIG. 2 is a schematic top view of the cross-sectional structure of the present invention;
FIG. 3 is a schematic diagram of a side-cut structure of the film of the present invention;
FIG. 4 is a schematic view of the top cross-sectional structure of the mounting post of the present invention;
fig. 5 is a schematic side sectional view of the solar panel of the present invention;
fig. 6 is a schematic flow chart of the present invention.
In the figure: 1. a housing; 2. a mounting seat; 3. a storage battery; 4. positioning a monitoring component; 5. a single chip microcomputer; 6. a rubber strip; 7. an air bag strip; 8. a first spring; 9. mounting a column; 10. a pressure sensor; 11. an air inlet; 12. a wind guide sheet; 13. mounting grooves; 14. a second spring; 15. a flexible sheet; 16. a retraction slot; 17. a solar panel; 18. an electric push rod; 19. a guide groove; 20. a magnetic block.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-6, the present invention provides a technical solution: a real-time monitoring device for airplane information comprises a shell 1, a mounting seat 2, a storage battery 3, a positioning monitoring component 4, a single chip microcomputer 5, a rubber strip 6, an air bag strip 7, a first spring 8, a mounting column 9, a pressure sensor 10, an air inlet 11, an air guide sheet 12, a mounting groove 13, a second spring 14, a soft sheet 15, a retraction groove 16, a solar panel 17, an electric push rod 18, a guide groove 19 and a magnet 20, wherein the mounting seat 2 is placed in the shell 1, the storage battery 3, the positioning monitoring component 4 and the single chip microcomputer 5 are embedded and fixed in the mounting seat 2, the rubber strip 6 and the air bag strip 7 are bonded between the bottom of the mounting seat 2 and the inner wall of the shell 1, the mounting column 9 penetrates through the first spring 8 at the edge of the bottom of the shell 1, the pressure sensor 10 is fixed at the bottom of the mounting column 9 through a bolt, the magnet 20 is bonded on the outer side of the mounting seat 2 and the, an air inlet 11 is formed in the outer side of the shell 1, an air guide sheet 12 is fixed on the outer side of the shell 1, the air guide sheet 12 is located above the air inlet 11, a mounting groove 13 is formed in the edge of the top of the shell 1, a flexible sheet 15 is connected to the inside of the mounting groove 13 through a second spring 14, a retraction groove 16 is reserved in the top of the shell 1, one end of a solar electric plate 17 is connected to the side wall of the retraction groove 16 in a shaft mode, an electric push rod 18 is connected to the bottom of the retraction groove 16 in a shaft mode, one end of the electric push rod 18 is located in a guide groove 19, and the guide groove 19 is formed in;
the rubber strips 6 and the air bag strips 7 are distributed in a staggered mode, the two sides of each rubber strip 6 are designed to be arc-shaped concave structures, and when the shell 1 is stressed and impacted, the rubber strips 6 and the air bag strips 7 have double buffering effects to protect the installation seat 2 in the shell 1;
the mounting columns 9 form an elastic sliding structure with the shell 1 through the first springs 8, 4 mounting columns 9 are symmetrically arranged about the central axis of the shell 1, when the shell 1 falls on the ground, the pressure sensors 10 at the bottoms of the mounting columns 9 sense pressure, meanwhile, the mounting columns 9 elastically contract on the shell 1 through the first springs 8 to protect the pressure sensors 10, the use of the 4 mounting columns 9 avoids uneven ground, and the pressure sensors 10 can sense pressure information;
the flexible sheets 15 are designed to be arc-shaped structures, 2 flexible sheets 15 are symmetrically arranged about the central axis of the shell 1, when the shell 1 falls, wind is guided into the shell 1 through the wind guide sheets 12 and the wind inlets 11 and blown to the bottom of the mounting groove 13, so that the flexible sheets 15 are supported under stress, and the flexible sheets 15 can slow down the falling speed of the shell 1 by using certain wind power by matching with the use of the second springs 14;
the top of the electric push rod 18 is designed to be a spherical structure, the top of the electric push rod 18 is connected with the guide groove 19 in a sliding mode, the diameter of the top of the electric push rod 18 is equal to the inner diameter of the guide groove 19, when the electric push rod 18 is driven, the top of the electric push rod 18 slides in the guide groove 19 in a fitting mode, one end of the solar electric plate 17 is pushed to tilt, the solar electric plate 17 moves out of the retraction groove 16, power generation operation is carried out through the solar electric plate 17, and meanwhile when the solar electric plate 17 rotates into the retraction groove 16, the solar electric plate 17 can be protected;
The working principle is as follows: in using the device for real-time monitoring of aircraft information, as in fig. 1-3, first when the housing 1 is dropped, the wind is guided into the shell 1 through the wind guide sheet 12 and the wind inlet 11 and is blown to the bottom of the mounting groove 13, the flexible sheet 15 is supported by force, and the use of the second spring 14 is matched, so that the flexible sheet 15 can utilize certain wind power to slow down the falling speed of the shell 1, and meanwhile, when the shell 1 reaches the ground, the double buffering action of the rubber strip 6 and the air bag strip 7, the mounting seat 2 in the shell 1 is protected, the magnetic blocks 20 in the shell 1 and the mounting seat 2 are buffered under the action of repulsion force, the mounting base 2 is further protected, internal parts are effectively prevented from being damaged, electric elements such as the positioning monitoring component 4 and the single chip microcomputer 5 are powered through the storage battery 3, and positioning and signal transmission are carried out through the positioning monitoring component 4;
then, as shown in fig. 1 and fig. 4-6, when the housing 1 is dropped to the ground, the pressure sensor 10 at the bottom of the mounting post 9 senses the pressure, transmits the signal to the single chip 5, the singlechip 5 controls the operation of the electric push rod 18, the top of the electric push rod 18 slides in the guide groove 19 in a fitting manner, one end of the solar panel 17 is pushed to tilt, so that the solar panel 17 can move out of the retraction slot 16, the solar panel 17 is utilized to carry out power generation operation, meanwhile, when the solar panel 17 rotates into the retraction slot 16, the solar panel 17 can be protected, the mounting post 9 elastically contracts on the shell 1 through the first spring 8, protect pressure sensor 10, the use of 4 erection columns 9 avoids the ground uneven for a plurality of pressure sensor 10 can sense pressure information, and the counter weight is added to the bottom of shell 1, makes things convenient for it to drop steadily and the bottom lands.
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 or portions thereof without departing from the spirit and scope of the invention.
Claims (6)
1. The utility model provides a be used for aircraft information real-time monitoring equipment, includes shell (1), location monitoring subassembly (4), singlechip (5) and pressure sensor (10), its characterized in that: the air-conditioning device is characterized in that a mounting seat (2) is placed in the shell (1), a storage battery (3), a positioning monitoring assembly (4) and a single chip microcomputer (5) are fixedly embedded in the mounting seat (2), a rubber strip (6) and an air bag strip (7) are bonded between the bottom of the mounting seat (2) and the inner wall of the shell (1), a mounting column (9) penetrates through and is fixed at the bottom edge of the shell (1) through a first spring (8), a pressure sensor (10) is fixed at the bottom of the mounting column (9) through a bolt, magnetic blocks (20) are bonded on the outer side of the mounting seat (2) and the side wall of the shell (1), an air inlet (11) is formed in the outer side of the shell (1), an air guide sheet (12) is fixed at the outer side of the shell (1) and is located above the air inlet (11), a mounting groove (13) is formed in the top edge of the shell (, and a film (15) is connected in the mounting groove (13) through a second spring (14), a retraction groove (16) is reserved at the top of the shell (1), one end of a solar electric plate (17) is in shaft connection with the side wall of the retraction groove (16), an electric push rod (18) is in shaft connection with the bottom of the retraction groove (16), one end of the electric push rod (18) is located in a guide groove (19), and the guide groove (19) is arranged at the bottom of the solar electric plate (17).
2. The real-time aircraft information monitoring device according to claim 1, wherein: the rubber strips (6) and the air bag strips (7) are distributed in a staggered mode, and the two sides of each rubber strip (6) are designed into arc-shaped concave structures.
3. The real-time aircraft information monitoring device according to claim 1, wherein: the mounting columns (9) form an elastic sliding structure with the shell (1) through the first springs (8), and the number of the mounting columns (9) is 4 in symmetry with the central axis of the shell (1).
4. The real-time aircraft information monitoring device according to claim 1, wherein: the flexible sheet (15) is designed to be of an arc-shaped structure, and 2 flexible sheets (15) are symmetrically arranged around the central axis of the shell (1).
5. The real-time aircraft information monitoring device according to claim 1, wherein: the top of the electric push rod (18) is designed to be of a spherical structure, the top of the electric push rod (18) is in sliding connection with the guide groove (19), and the diameter of the top of the electric push rod (18) is equal to the inner diameter of the guide groove (19).
6. The real-time aircraft information monitoring device according to claim 1, wherein: the magnetic blocks (20) are distributed on the inner wall of the shell (1) and the outer side of the mounting seat (2) in a staggered mode, and the cross section of each magnetic block (20) is designed to be of an isosceles trapezoid structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022442125.3U CN213628648U (en) | 2020-10-28 | 2020-10-28 | Real-time monitoring equipment for airplane information |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022442125.3U CN213628648U (en) | 2020-10-28 | 2020-10-28 | Real-time monitoring equipment for airplane information |
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| Publication Number | Publication Date |
|---|---|
| CN213628648U true CN213628648U (en) | 2021-07-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022442125.3U Active CN213628648U (en) | 2020-10-28 | 2020-10-28 | Real-time monitoring equipment for airplane information |
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| CN (1) | CN213628648U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114005377A (en) * | 2021-08-25 | 2022-02-01 | 中国民用航空飞行学院 | Novel education publicity column |
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2020
- 2020-10-28 CN CN202022442125.3U patent/CN213628648U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114005377A (en) * | 2021-08-25 | 2022-02-01 | 中国民用航空飞行学院 | Novel education publicity column |
| CN114005377B (en) * | 2021-08-25 | 2023-09-12 | 中国民用航空飞行学院 | Education publicity column |
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