CN214608109U - Automatic control system of aircraft - Google Patents
Automatic control system of aircraft Download PDFInfo
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- CN214608109U CN214608109U CN202120725630.0U CN202120725630U CN214608109U CN 214608109 U CN214608109 U CN 214608109U CN 202120725630 U CN202120725630 U CN 202120725630U CN 214608109 U CN214608109 U CN 214608109U
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- fuselage
- control system
- control mechanism
- automatic control
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Abstract
The utility model provides an automatic control system of aircraft, manage through automatic control system including fuselage, the support that falls to the ground, annular vacuum jar and gasbag, the fuselage bottom is equipped with the support that falls to the ground, the fuselage upper surface is equipped with circular opening, the fuselage upper surface is equipped with the foam disc, foam disc bottom is equipped with the cover shell, the inside annular vacuum jar that is equipped with of fuselage, annular vacuum jar upper surface is equipped with the fixed column, the fixed column upper surface is equipped with the gasbag, compare with prior art, the utility model discloses following beneficial effect has: through foam disc and control mechanism cooperation, realize the automatic switching of circular open-ended, the gasbag of being convenient for pops out, through singlechip and acceleration sensor cooperation, realizes the real time monitoring to fuselage falling speed, and when aircraft is inside to appear unusually or meet the strong wind, when handstand the ground that falls, the gasbag can play fine buffering effect, and has improved the protective effect of fuselage.
Description
Technical Field
The utility model belongs to the aircraft field, in particular to automatic control system of aircraft.
Background
At present, comparatively common have unmanned aerial vehicle in the aircraft, unmanned aerial vehicle, commonly known: unmanned planes, unmanned aerial vehicles, unmanned combat airplanes, and bee-type machines; the airplane is a wide range of remote control aircrafts without the need of a pilot to board and pilot, and is generally in particular to an unmanned reconnaissance airplane of the military. The unmanned aerial vehicle is provided with no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar.
However, the existing unmanned aerial vehicle needs to be driven by wireless signals, and when the unmanned aerial vehicle runs into the bad weather, the aircraft cannot receive the signals, or the aircraft is damaged by blades or motors, and the aircraft falls rapidly to cause damage, which often happens.
Accordingly, there is a need for an automatic control system for an aircraft.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an automatic control system of aircraft, through increasing the fuselage, falling to the ground support, annular vacuum cylinder and gasbag, manage through automatic control system to solve the problem that proposes among the above-mentioned background art.
The technical scheme of the utility model is realized like this: an automatic control system of an aircraft comprises a fuselage, a landing support, an annular vacuum cylinder and an air bag, wherein the automatic control system is used for managing the aircraft, a cargo carrying box is arranged at the bottom of the fuselage, a containing tank is arranged inside the cargo carrying box, a box door is arranged on the front surface of the cargo carrying box, the landing support is arranged at the bottom of the fuselage, a circular opening is formed in the upper surface of the fuselage, a foam disc is arranged on the upper surface of the fuselage, a sleeve shell is arranged at the bottom of the foam disc, an annular clamping groove is formed in the side surface of the sleeve shell, a control mechanism is arranged inside the fuselage and comprises a rectangular opening, a hinge block, a hinge rod, a clamping block, a circular groove, a circular magnet, a limiting rod, a spring, a coil and an iron core, a rectangular opening is formed in the upper surface of the control mechanism, the hinge block is arranged on the front surface of the hinge block, the hinge rod is arranged on the front surface of the hinge block, the utility model discloses a fuse box, including articulated rod, fuselage, hinge bar, limiting rod, control mechanism, coil, solenoid valve, power distribution box, hinge bar top is equipped with the fixture block, the hinge bar left side is equipped with circular recess, the inside circular magnet that is equipped with of circular recess, the hinge bar right side is equipped with the gag lever post, the gag lever post outside is equipped with the spring, the inside iron core that is equipped with of control mechanism, the iron core outside is equipped with the coil, the fuselage bottom is equipped with the check valve, the inside annular vacuum jar that is equipped with of fuselage, annular vacuum jar upper surface is equipped with the fixed column, the fixed column upper surface is equipped with the gasbag, the gasbag bottom is equipped with the trachea, the trachea middle-end is equipped with the solenoid valve, annular vacuum jar upper surface is equipped with the power distribution box, inside acceleration sensor, singlechip, relay and the power of being equipped with of power distribution box.
As a preferred embodiment, the inside diameter of the circular opening is larger than the outside diameter of the casing, the foam disc is made of foam material, the casing is made of plastic material, and the foam disc is connected with the casing through gluing.
As a preferred embodiment, control mechanism is equipped with two, two control mechanism is located the cover shell left and right sides respectively, articulated piece and control mechanism connection structure as an organic whole, articulated piece is located control mechanism upper surface rear end position, articulated piece is connected through articulated with the hinge bar, circular magnet is fixed inside circular recess through splicing, hinge bar, fixture block and gag lever post connection structure as an organic whole.
In a preferred embodiment, the one-way valve, the annular vacuum cylinder and the interior of the air pipe are communicated.
As a preferred embodiment, the output end of the acceleration sensor is connected with the input end of the single chip microcomputer, the output end of the single chip microcomputer is connected with the input end of the relay, the output end of the relay is connected with the input end of the power supply, the output end of the power supply is connected with the input end of the coil, and the output end of the power supply is connected with the input end of the electromagnetic valve.
In a preferred embodiment, the cargo box is connected with the box door through a hinge, and a manned chamber is arranged on the left side in the machine body.
After the technical scheme is adopted, the beneficial effects of the utility model are that: through foam disc and control mechanism cooperation, realize that the gasbag of being convenient for of the automatic switching of circular opening pops out, through singlechip and acceleration sensor cooperation, realize the real time monitoring to fuselage falling speed, when aircraft is inside to appear unusually or meet the strong wind, when handstand the ground that falls, the gasbag can play fine buffering effect, and has improved the protective effect of fuselage.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.
Fig. 1 is a schematic diagram of the overall structure of an automatic control system of an aircraft according to the present invention;
fig. 2 is a cross-sectional view of the automatic control system of the aircraft according to the present invention;
FIG. 3 is an enlarged view of the automatic control system of the present invention at the A position;
fig. 4 is a schematic diagram of a circuit framework of an automatic control system of an aircraft according to the present invention;
fig. 5 is a working schematic diagram of an automatic control system of an aircraft according to the present invention;
in the figure, 1-machine body, 101-circular opening, 102-container carrying body, 1021-box door, 2-floor bracket, 3-foam disc, 301-casing, 302-annular clamping groove, 4-control mechanism, 401-rectangular opening, 402-hinge block, 403-hinge rod, 404-fixture block, 405-circular groove, 506-circular magnet, 407-limiting rod, 408-spring, 409-coil, 410-iron core, 5-one-way valve, 6-annular vacuum cylinder, 601-fixed column, 602-distribution box, 603-air pipe, 604-electromagnetic valve, 605-air bag, 7-acceleration sensor, 8-single chip microcomputer, 9-relay and 10-power supply.
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 efforts belong to the protection scope of the present invention.
Referring to fig. 1 to 5, the present invention provides a technical solution: an automatic control system of an aircraft comprises a fuselage 1, a landing support 2, an annular vacuum cylinder 6 and an airbag 605, wherein a cargo carrying box 102 is arranged at the bottom of the fuselage 1, a containing groove is formed inside the cargo carrying box 102, a box door 1021 is arranged on the front surface of the cargo carrying box 102, the landing support 2 is arranged at the bottom of the fuselage 1, a circular opening 101 is formed in the upper surface of the fuselage 1, a foam disc 3 is arranged on the upper surface of the fuselage 1, an annular casing 301 is arranged at the bottom of the foam disc 3, an annular clamping groove 302 is formed in the side surface of the annular casing 301, a control mechanism 4 is arranged inside the fuselage 1, the control mechanism 4 comprises a rectangular opening 401, a hinging block 402, a hinging rod 404, a clamping block 404, a circular groove 405, a circular magnet 406, a limiting rod 407, a spring 408, a coil 409 and an iron core 410, the rectangular opening 401 is formed in the upper surface of the control mechanism 4, the hinging block 402 is arranged on the upper surface of the hinging block 402, the hinging rod 404 is arranged on the front surface of the hinging block 402, the top of hinge rod 404 is equipped with fixture block 404, hinge rod 404 left side is equipped with circular recess 405, the inside circular magnet 406 that is equipped with of circular recess 405, hinge rod 404 right side is equipped with gag lever post 407, the gag lever post 407 outside is equipped with spring 408, the inside iron core 410 that is equipped with of control mechanism 4, the outside coil 409 that is equipped with of iron core 410, 1 bottom of fuselage is equipped with check valve 5, 1 inside annular vacuum cylinder 6 that is equipped with of fuselage, the 6 upper surfaces of annular vacuum cylinder are equipped with fixed column 601, the fixed column 601 upper surface is equipped with gasbag 605, gasbag 605 bottom is equipped with trachea 603, the trachea 603 middle-end is equipped with solenoid valve 604, the 6 upper surface of annular vacuum cylinder is equipped with block terminal 602, the inside acceleration sensor 7 that is equipped with of block terminal 602, singlechip 8, relay 9 and power 10.
The one-way valve 5, the annular vacuum cylinder 6 and the air pipe 603 are communicated with each other, and the annular vacuum cylinder 6 is convenient to inflate through the arranged one-way valve 5.
The output end of the acceleration sensor 7 is connected with the input end of the single chip microcomputer 8, the output end of the single chip microcomputer 8 is connected with the input end of the relay 9, the output end of the relay 9 is connected with the input end of the power supply 10, the output end of the power supply 10 is connected with the input end of the coil 409, the output end of the power supply 10 is connected with the input end of the electromagnetic valve 604, and the real-time monitoring of the descending speed of the machine body 1 is achieved through the cooperation of the single chip microcomputer 8 and the acceleration sensor 7.
The cargo carrying box 102 is connected with the box door 1021 through a hinge, cargo is convenient to transport through the arranged cargo carrying box 102, a manned room is arranged on the left side inside the aircraft body 1, and an aircraft can carry cargo and also can carry people, and the management is carried out through an automatic control system.
As an embodiment of the present invention: in the actual use process, goods are put into the cargo carrying box 102 by opening the box door 1021, when the aircraft cannot receive signals due to severe weather or the aircraft falls rapidly due to the damage of blades of the aircraft, the damage of a motor and the like in the flying process of the aircraft, the descending speed of the aircraft is detected by the acceleration sensor 7 and is transmitted to the singlechip 8, after the singlechip 8 is further calculated and processed, the relay 9 controls the power supply 10 to supply power to the coil 409 through controlling the relay 9, the coil 409 is matched with the iron core 410, the iron core 410 generates magnetism, because the opposite magnetic poles of the iron core 410 and the circular magnet 406 are opposite, the iron core 410 pushes the circular magnet 406 to move rightwards, the circular magnet 406 drives the hinge rod 404 to deflect rightwards and compress the spring 408, and at the moment, the fixture block 404 of the hinge rod 404 is separated from the annular clamping groove 302 of the annular casing 301, meanwhile, the relay 9 controls the power supply 10 to supply power to the electromagnetic valve 604, since the high-pressure gas is added into the annular vacuum cylinder 6 in advance through the one-way valve 5, the electromagnetic valve 604 is opened, the gas in the annular vacuum cylinder 6 is discharged into the air bag 605 through the gas pipe 603, the air bag 605 is rapidly inflated and jacks up the foam disc 3, the top of the air bag 605 is higher than the blades of the aircraft at the moment, when the aircraft stands upside down and falls on the ground, the air bag 605 can play a good buffering effect, and the protection effect of the aircraft body 1 is improved.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The utility model provides an automatic control system of aircraft, includes fuselage, falls to the ground support, annular vacuum cylinder and gasbag, manages its characterized in that through automatic control system: the portable wagon is characterized in that a cargo carrying box is arranged at the bottom of the machine body, a containing tank is arranged inside the cargo carrying box, a box door is arranged on the front surface of the cargo carrying box, a floor stand is arranged at the bottom of the machine body, a circular opening is formed in the upper surface of the machine body, a foam disc is arranged on the upper surface of the machine body, a casing is arranged at the bottom of the foam disc, an annular clamping groove is formed in the side surface of the casing, a control mechanism is arranged inside the machine body and comprises a rectangular opening, a hinge block, a hinge rod, a clamping block, a circular groove, a circular magnet, a limiting rod, a spring, a coil and an iron core, the rectangular opening is formed in the upper surface of the control mechanism, the hinge block is arranged on the front surface of the hinge block, the clamping block is arranged at the top of the hinge rod, the circular groove is formed in the left side of the hinge rod, the circular magnet is arranged inside the circular groove, and the limiting rod is arranged on the right side of the hinge rod, the utility model discloses a safety device, including gag lever post, control mechanism, air bag, air pipe, solenoid valve, air bag, limiting rod, control mechanism, coil, air bag, power distribution box, inside acceleration sensor, singlechip, relay and the power of being equipped with of gag lever post outside being equipped with the spring, the inside iron core that is equipped with of control mechanism, the iron core outside is equipped with the coil, the fuselage bottom is equipped with the check valve, the inside annular vacuum jar that is equipped with of fuselage, annular vacuum jar upper surface is equipped with the fixed column, the fixed column upper surface is equipped with the gasbag, the gasbag bottom is equipped with the trachea, the trachea middle-end is equipped with the solenoid valve, annular vacuum jar upper surface is equipped with the power distribution box, inside acceleration sensor, singlechip, relay and the power of being equipped with of power distribution box.
2. An automatic control system for an aircraft according to claim 1, characterized in that: the inside diameter of circular opening is greater than the external diameter of cover shell, the foam disc is made for foam material, the cover shell is the plastics material, the foam disc is connected through the cementing with the cover shell.
3. An automatic control system for an aircraft according to claim 1, characterized in that: control mechanism is equipped with two, two control mechanism is located the cover shell left and right sides respectively, articulated piece and control mechanism connection structure as an organic whole, articulated piece is located control mechanism upper surface rear end position, articulated piece is connected through articulated with the hinge bar, circular magnet is fixed inside circular recess through splicing, hinge bar, fixture block and gag lever post connection structure as an organic whole.
4. An automatic control system for an aircraft according to claim 1, characterized in that: the one-way valve, the annular vacuum cylinder and the air pipe are communicated with each other.
5. An automatic control system for an aircraft according to claim 1, characterized in that: the output end of the acceleration sensor is connected with the input end of the single chip microcomputer, the output end of the single chip microcomputer is connected with the input end of the relay, the output end of the relay is connected with the input end of the power supply, the output end of the power supply is connected with the input end of the coil, and the output end of the power supply is connected with the input end of the electromagnetic valve.
6. An automatic control system for an aircraft according to claim 1, characterized in that: the cargo carrying box is connected with the box door through a hinge, and a manned chamber is arranged on the left side in the machine body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120725630.0U CN214608109U (en) | 2021-04-09 | 2021-04-09 | Automatic control system of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120725630.0U CN214608109U (en) | 2021-04-09 | 2021-04-09 | Automatic control system of aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN214608109U true CN214608109U (en) | 2021-11-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120725630.0U Active CN214608109U (en) | 2021-04-09 | 2021-04-09 | Automatic control system of aircraft |
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| CN (1) | CN214608109U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136294A (en) * | 2021-11-26 | 2022-03-04 | 山东省物化探勘查院 | Intelligent three-dimensional topographic surveying and mapping device |
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2021
- 2021-04-09 CN CN202120725630.0U patent/CN214608109U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136294A (en) * | 2021-11-26 | 2022-03-04 | 山东省物化探勘查院 | Intelligent three-dimensional topographic surveying and mapping device |
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