CN209600797U - A kind of unmanned plane crash protection - Google Patents
A kind of unmanned plane crash protection Download PDFInfo
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- CN209600797U CN209600797U CN201920232779.8U CN201920232779U CN209600797U CN 209600797 U CN209600797 U CN 209600797U CN 201920232779 U CN201920232779 U CN 201920232779U CN 209600797 U CN209600797 U CN 209600797U
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- unmanned plane
- main body
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- crash
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Abstract
The utility model discloses a kind of unmanned plane crash protections, including main body and flight control system, four sides of the main body are welded with fixing head, the fixing head is welded with wing plate far from the side of main body, the inner cavity of the wing plate is fixedly installed with main motor, and the output end of the main motor is rotatably equipped with host paddle.The utility model relates to air vehicle technique fields, the unmanned plane crash protection, by the way that anti-crash detection system is arranged, the flight condition of unmanned plane (all kinds of flying qualities) can be detected in advance, analysis, to there is the adequately anticipation time, it can ensure before unmanned plane crashes, it can timely respond, pass through regulation, it is set to restore normal flight, it is popped up simultaneously by built-in air bag, to protect unmanned plane, reduce air crash probability, even if anti-crash system in effective, the unmanned plane is also equipped with shock-absorbing anti-collision mechanism, loss can be reduced to greatest extent.
Description
Technical field
The utility model relates to air vehicle technique field, specially a kind of unmanned plane crash protection.
Background technique
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned vehicle.Unmanned plane is actually the general designation of unmanned vehicle, can be divided into from technical standpoint definition: nobody
This several major class of helicopter, unmanned fixed-wing aircraft, unmanned multi-rotor aerocraft, unmanned airship, unmanned parasol.With manned aircraft phase
Than it has many advantages, such as that small in size, low cost, easy to use, low to operational environment requirement, battlefield survival is stronger.Due to
UAV has great significance to Future Air Combat, and each main military country, the world all is stepping up to carry out unmanned fly
The development work of machine.
Existing unmanned plane, after engine failure, it is easy to the tragedy of air crash occur, cope with unmanned plane pendant at present
The mode of machine usually installs safe umbrella on unmanned plane, but safe umbrella is not opened even there is also opening not in time
Phenomenon, to still there is the phenomenon that leading to unmanned plane air crash.
Utility model content
(1) the technical issues of solving
In view of the deficiencies of the prior art, the utility model provides a kind of unmanned plane crash protection, solves existing nothing
The problem of man-machine safety safeguard procedures are short of.
(2) technical solution
To achieve the above object, the utility model provides the following technical solutions: a kind of unmanned plane crash protection, including master
Body and flight control system, four sides of the main body are welded with fixing head, the fixing head far from main body one
Side is welded with wing plate, and the inner cavity of the wing plate is fixedly installed with main motor, and the output end of the main motor is rotatably equipped with
Host paddle is extended to outside the top of wing plate at the top of the host paddle, is fixedly installed in the middle part of the host intracoelomic cavity spare
Motor, the output end of the spare motor are rotatably equipped with slave paddle, the top of main body are extended at the top of the slave paddle
Outside, the inner cavity of the main body is symmetrically installed with air bag, and solenoid valve, the host are equipped at the top of the air bag
Safety head is connected at the top of body, the bottom of the main body welds organic box, is separately installed with height detection on the machine box
Instrument, speed detector and damping detector, are fixedly installed with video camera, the bottom of the main body immediately below the machine box
It is symmetrically welded organic frame, the bottom of the rack is fixedly installed with damper cylinder, and angled inspection is fixedly mounted in the inner cavity of the wing plate
Survey instrument.
The flight control system includes information detecting module, and the information detecting module includes height testing instrument, speed
Detector, angle detector and damping detector, the output end of the information detecting module and the input terminal of central processing unit
Electrical connection, the two-way electrical connection information contrast module of central processing unit, the output end of the central processing unit respectively with control
The electrical connection of the input terminal of node unit and feedback module, the information contrast module include the first contrast module, the second comparison
Module, third contrast module and the 4th contrast module, the control node unit include the first control node, the second control section
Point, third control node and the 4th control node, first control node, the second control node, third control node with
And the 4th the output end of control node be electrically connected respectively with the input terminal of solenoid valve, main motor, spare motor and warning lamp,
The output end of the feedback module is electrically connected with the input terminal of angle modification module, and the central processing unit two-way signaling connects nothing
Line communication module, the wireless communication module two-way signaling connect control panel.
Preferably, the control panel includes display screen, host switch, guest machine switch and alarm modules.
Preferably, the warning lamp is fixedly mounted on the bottom of wing plate.
Preferably, be respectively welded the first fixed link and the second fixed link between the rack, first fixed link with
It is fixedly connected with the first damping spring between second fixed link, is connected with the second damping between second fixed link and damper cylinder
Spring.
(3) beneficial effect
The utility model provides a kind of unmanned plane crash protection.Have it is following the utility model has the advantages that
The unmanned plane crash protection can be in advance to the flight condition of unmanned plane by the way that anti-crash detection system is arranged
(all kinds of flying qualities) is detected, is analyzed, to there is the adequately anticipation time, it can be ensured that before unmanned plane crashes,
It can timely respond, by regulation, so that it is restored normal flight, while popping up by built-in air bag, to protect
Unmanned plane reduces air crash probability, even if anti-crash system in effective, which, can be maximum also equipped with shock-absorbing anti-collision mechanism
The reduction of limit is lost, and opens main motor by the host switch on control panel, to drive host paddle to rotate, to make
Unmanned plane lift-off detects unmanned plane by height testing instrument, speed detector, angle detector and damping detector respectively
Highly, speed, flight angle and flight damping size, and pass through the first contrast module, the second contrast module, third pair respectively
(critical value is built in central processing unit) is compared with respective critical value than module and the 4th contrast module, such as
When actual height value is lower than critical value, show that unmanned plane height is insufficient, it may occur however that actual speed is worked as in aviation accident for another example
When value is greater than critical value, show that unmanned plane is in rapidly crash course, or by comparing damping value, when practical damping value is big
When critical value, also indicate that unmanned plane is likely to be at the state that rapidly drops, central processing unit module by wireless communication, makes at this time
Alarm modules early warning prompts operator, further, spare motor is driven by control node unit, to drive slave paddle
Rotation, can also manually opened guest machine switch, make spare electric motor starting, so that unmanned plane is returned to normal flight height rapidly
Degree, prevents air crash, if the measure is still invalid, further, then passes through control node unit drive magnetic valve and police
Show lamp, after solenoid valve starting, air bag automatic spring breaks through safety head, the outside of main body is extend out to, thus to unmanned plane
It is protected, makes its safe landing, practical flight angle and critical angle are compared by third contrast module, when actual value is big
When, by feedback module driving angle correction module, so that angle modification is carried out, in case its air crash, thus greatly reduces pendant
Machine probability, if after the above measure is failed, unmanned plane continues to air crash, at this time in order to reduce air crash loss, first by subtracting
Shake cylinder contacts ground of falling, and carries out first run damping by damper cylinder, then passes through the first damping spring and the second damping spring
Secondary shock-absorbing is carried out, to reduce air crash loss to greatest extent.
Detailed description of the invention
Fig. 1 is the utility model structural profile illustration；
Fig. 2 is the utility model structure top view；
Fig. 3 is the utility model rack construction side view；
Fig. 4 is the utility model block diagram representation.
In figure: 1, main body；2, flight control system；3, fixing head；4, wing plate；5, main motor；6, host paddle；7, standby
Use motor；8, slave paddle；9, air bag；10, solenoid valve；11, safety head；12, machine box；13, height testing instrument；14, speed
Detector；15, detector is damped；16, video camera；17, rack；18, damper cylinder；19, angle detector；20, infomation detection mould
Block；21, central processing unit；22, information contrast module；23, control node unit；24, the first contrast module；25, the second comparison
Module；26, third contrast module；27, the 4th contrast module；28, feedback module；29, angle modification module；30, the first control
Node；31, the second control node；32, third control node；33, the 4th control node；34, control panel；35, display screen；
36, host switch；37, guest machine switchs；38, alarm modules；39, wireless communication module；40, warning lamp；41, first is fixed
Bar；42, the second fixed link；43, the first damping spring；44, the second damping spring.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
As shown in Figs 1-4, the utility model provides a kind of technical solution: a kind of unmanned plane crash protection passes through setting
Anti- crash detection system can in advance detect the flight condition of unmanned plane (all kinds of flying qualities), be analyzed, be filled to have
The anticipation time divided, it can be ensured that before unmanned plane crashes, can timely respond, by regulation, it be made to restore normal
Flight, while being popped up by built-in air bag 9, to protect unmanned plane, reduces air crash probability, though anti-crash system without
Effect, the unmanned plane also equipped with shock-absorbing anti-collision mechanism, can reduce loss, including main body 1 and flight control to greatest extent
System 2 processed, four sides of main body 1 are welded with fixing head 3, and fixing head 3 is welded with wing plate 4, wing plate far from the side of main body 1
4 inner cavity is fixedly installed with main motor 5, and the output end of main motor 5 is rotatably equipped with host paddle 6, and the top of host paddle 6 is prolonged
Outside the top for extending to wing plate 4, spare motor 7, the output end rotation of spare motor 7 are fixedly installed in the middle part of 1 inner cavity of main body
Slave paddle 8 is installed, the top of slave paddle 8 extends to outside the top of main body 1, and the inner cavity of main body 1 is symmetrically installed with safety
Air bag 9, the top of air bag 9 are equipped with solenoid valve 10, and the top of main body 1 is connected with safety head 11, the bottom of main body 1
Organic box 12 is welded, height testing instrument 13, speed detector 14 and damping detector 15 are separately installed on machine box 12, is passed through
Host switch 36 on control panel 34 opens main motor 5, so that host paddle 6 be driven to rotate, so that unmanned plane be made to go up to the air, leads to
Cross height testing instrument 13, speed detector 14, angle detector 19 and damping detector 15 detect respectively unmanned plane height,
Speed, flight angle and flight damping size, the underface of machine box 12 is fixedly installed with video camera 16, the bottom of main body 1
It is symmetrically welded organic frame 17, the bottom of rack 17 is fixedly installed with damper cylinder 18, and it is fixed that first is respectively welded between rack 17
Bar 41 and the second fixed link 42 are fixedly connected with the first damping spring 43 between first fixed link 41 and the second fixed link 42, the
The second damping spring 44 is connected between two fixed links 42 and damper cylinder 18, if after the above measure is failed, unmanned plane still after
Continuous air crash contacts ground of falling by damper cylinder 18 first, passes through damper cylinder 18 and carry out the first run at this time in order to reduce air crash loss
Damping then carries out secondary shock-absorbing by the first damping spring 43 and the second damping spring 44, to reduce to greatest extent
Air crash loss, the inner cavity of wing plate 4 is fixedly installed with angle detector 19；Flight control system 2 includes information detecting module 20, letter
Ceasing detection module 20 includes height testing instrument 13, speed detector 14, angle detector 19 and damping detector 15, information inspection
The output end for surveying module 20 is electrically connected with the input terminal of central processing unit 21, and the two-way electrical connection information of central processing unit 21 compares mould
Block 22, the output end of central processing unit 21 are electrically connected with the input terminal of control node unit 23 and feedback module 28 respectively, letter
Ceasing contrast module 22 includes the first contrast module 24, the second contrast module 25, third contrast module 26 and the 4th contrast module
27, and respectively by the first contrast module 24, the second contrast module 25, third contrast module 26 and the 4th contrast module 27 with
Respective critical value is compared (critical value is built in central processing unit 21), such as when actual height value is lower than critical value
When, show that unmanned plane height is insufficient, it may occur however that aviation accident shows nothing for another example when values for actual speed is greater than critical value
It is man-machine to also indicate that nobody when practical damping value is greater than critical value in rapidly crash course, or by comparing damping value
Machine is likely to be at the state that rapidly drops, and module 39 by wireless communication of central processing unit 21, make 38 early warning of alarm modules, mention at this time
Show operator, control node unit 23 includes the first control node 30, the second control node 31, third control node 32 and the
Four control nodes 33, the first control node 30, the second control node 31, third control node 32 and the 4th control node 33
Output end is electrically connected with the input terminal of solenoid valve 10, main motor 5, spare motor 7 and warning lamp 40 respectively, further,
Drive spare motor 7 by control node unit 23, thus drive slave paddle 8 rotate, can also manually opened guest machine switch 37,
Start spare motor 7, so that unmanned plane is returned to normal flight height rapidly, prevents air crash, if the measure is still invalid,
Further, then pass through 23 drive magnetic valve 10 of control node unit and warning lamp 40, after solenoid valve 10 starts, safety
9 automatic spring of air bag, breaks through safety head 11, extend out to the outside of main body 1, to protect to unmanned plane, makes its safety
It lands, warning lamp 40 is fixedly mounted on the bottom of wing plate 4, the output end of feedback module 28 and the input terminal of angle modification module 29
Electrical connection compares practical flight angle by third contrast module 26 and critical angle passes through feedback module when actual value is big
28 driving angle correction modules 29, so that angle modification is carried out, in case its air crash, thus greatly reduces air crash probability, center
21 two-way signaling of processor connects wireless communication module 39, and 39 two-way signaling of wireless communication module connects control panel 34, control
Panel 34 includes display screen 35, host switch 36, guest machine switch 37 and alarm modules 38.
In use, main motor 5 is opened by the host switch 36 on control panel 34, so that host paddle 6 is driven to rotate,
To make unmanned plane go up to the air, divided by height testing instrument 13, speed detector 14, angle detector 19 and damping detector 15
Not Jian Ce the height of unmanned plane, speed, flight angle and flight damping size, and pass through the first contrast module 24, the respectively
(the critical value is compared with respective critical value for two contrast modules 25, third contrast module 26 and the 4th contrast module 27
It is built in central processing unit 21), for example when actual height value is lower than critical value, show that unmanned plane height is insufficient, Ke Nengfa
Raw aviation accident shows that unmanned plane is in rapidly crash course, Huo Zhetong for another example when values for actual speed is greater than critical value
Cross and compare damping value, when practical damping value be greater than critical value when, also indicate that unmanned plane is likely to be at the state that rapidly drops, at this time in
Module 39 by wireless communication of central processor 21 make 38 early warning of alarm modules, prompt operator, further, pass through control section
Dot element 23 drives spare motor 7, thus drive slave paddle 8 rotate, can also manually opened guest machine switch 37, make spare motor
7 startings, so that unmanned plane is returned to normal flight height rapidly, prevent air crash, if the measure is still invalid, further
, then by 23 drive magnetic valve 10 of control node unit and warning lamp 40, after solenoid valve 10 starts, air bag 9 is certainly
It moves out, breaks through safety head 11, extend out to the outside of main body 1, to protect to unmanned plane, make its safe landing, lead to
It crosses third contrast module 26 and compares practical flight angle and critical angle, when actual value is big, angle is driven by feedback module 28
Correction module 29 is spent, so that angle modification is carried out, in case its air crash, thus greatly reduces air crash probability, if the above measure is equal
After failure, unmanned plane continues to air crash, at this time in order to reduce air crash loss, passes through damper cylinder 18 first and contacts ground of falling,
First run damping is carried out by damper cylinder 18, secondary subtract then is carried out by the first damping spring 43 and the second damping spring 44
Shake, to reduce air crash loss to greatest extent.
In conclusion the unmanned plane crash protection can be in advance to unmanned plane by the way that anti-crash detection system is arranged
Flight condition (all kinds of flying qualities) is detected, is analyzed, to there is the adequately anticipation time, it can be ensured that occur in unmanned plane
It before crash, can timely respond, by regulation, so that it is restored normal flight, while popping up by built-in air bag 9,
To protect unmanned plane, reduce air crash probability, even if anti-crash system in effective, the unmanned plane also equipped with shock-absorbing anti-collision mechanism,
Loss can be reduced to greatest extent.
It should be noted that the electric elements occurred in this article are electrically connected with extraneous main controller and 220V alternating current, and
And main controller can play the conventionally known equipment of control, control principle, internal structure and control switch side for computer etc.
Formula etc. is the conventional means of the prior art, directly quotes, does not repeat them here herein, herein, the first and second grades
The relational terms of class are only used to distinguish one entity or operation from another entity or operation, and are not necessarily required
Or imply that there are any actual relationship or orders between these entities or operation.Moreover, term " includes ", " packet
Containing " or any other variant thereof is intended to cover non-exclusive inclusion, so that including the process of a series of elements, side
Method, article or equipment not only include those elements, but also including other elements that are not explicitly listed, or further include
For elements inherent to such a process, method, article, or device.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (4)
1. a kind of unmanned plane crash protection, including main body (1) and flight control system (2), it is characterised in that: the master
Four sides of body (1) are welded with fixing head (3), and the fixing head (3) is welded with wing plate (4) far from the side of main body (1),
The inner cavity of the wing plate (4) is fixedly installed with main motor (5), and the output end of the main motor (5) is rotatably equipped with host
Paddle (6) extends to outside the top of wing plate (4) at the top of the host paddle (6), the fixed peace in the middle part of main body (1) inner cavity
Equipped with spare motor (7), the output end of the spare motor (7) is rotatably equipped with slave paddle (8), the top of the slave paddle (8)
Portion extends to outside the top of main body (1), and the inner cavity of the main body (1) is symmetrically installed with air bag (9), the substitute
It is equipped at the top of capsule (9) solenoid valve (10), is connected with safety head (11) at the top of the main body (1), the main body (1)
Bottom weld organic box (12), be separately installed on the machine box (12) height testing instrument (13), speed detector (14) with
And detector (15) are damped, it is fixedly installed with video camera (16) immediately below the machine box (12), the bottom of the main body (1)
It is symmetrically welded organic frame (17), the bottom of the rack (17) is fixedly installed with damper cylinder (18), and the inner cavity of the wing plate (4) is solid
Dingan County is equipped with angle detector (19)；
The flight control system (2) includes information detecting module (20), and the information detecting module (20) includes height detection
Instrument (13), speed detector (14), angle detector (19) and damping detector (15), the information detecting module (20)
Output end is electrically connected with the input terminal of central processing unit (21), the two-way electrical connection information contrast module of central processing unit (21)
(22), the output end of the central processing unit (21) input terminal with control node unit (23) and feedback module (28) respectively
Electrical connection, the information contrast module (22) include the first contrast module (24), the second contrast module (25), third contrast module
(26) and the 4th contrast module (27), the control node unit (23) include the first control node (30), the second control section
Point (31), third control node (32) and the 4th control node (33), first control node (30), the second control node
(31), the output end of third control node (32) and the 4th control node (33) respectively with solenoid valve (10), main motor
(5), the input terminal of spare motor (7) and warning lamp (40) is electrically connected, and the output end of the feedback module (28) is repaired with angle
The input terminal electrical connection of positive module (29), central processing unit (21) two-way signaling connects wireless communication module (39), described
Wireless communication module (39) two-way signaling connects control panel (34).
2. a kind of unmanned plane crash protection according to claim 1, it is characterised in that: the control panel (34) includes
Display screen (35), host switch (36), guest machine switch (37) and alarm modules (38).
3. a kind of unmanned plane crash protection according to claim 1, it is characterised in that: the fixed peace of the warning lamp (40)
Mounted in the bottom of wing plate (4).
4. a kind of unmanned plane crash protection according to claim 1, it is characterised in that: between the rack (17) respectively
The first fixed link (41) and the second fixed link (42) are welded with, it is solid between first fixed link (41) and the second fixed link (42)
Surely it is connected with the first damping spring (43), is connected with the second damping spring between second fixed link (42) and damper cylinder (18)
(44).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920232779.8U CN209600797U (en) | 2019-02-23 | 2019-02-23 | A kind of unmanned plane crash protection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920232779.8U CN209600797U (en) | 2019-02-23 | 2019-02-23 | A kind of unmanned plane crash protection |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209600797U true CN209600797U (en) | 2019-11-08 |
Family
ID=68402983
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920232779.8U Expired - Fee Related CN209600797U (en) | 2019-02-23 | 2019-02-23 | A kind of unmanned plane crash protection |
Country Status (1)
| Country | Link |
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| CN (1) | CN209600797U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111524396A (en) * | 2020-04-30 | 2020-08-11 | 成都民航空管科技发展有限公司 | Low altitude warning method, system, data processing terminal and medium for terminal area |
| WO2022143764A1 (en) * | 2020-12-31 | 2022-07-07 | 江苏数字鹰科技股份有限公司 | Police unmanned aerial vehicle having crash protection function |
-
2019
- 2019-02-23 CN CN201920232779.8U patent/CN209600797U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111524396A (en) * | 2020-04-30 | 2020-08-11 | 成都民航空管科技发展有限公司 | Low altitude warning method, system, data processing terminal and medium for terminal area |
| CN111524396B (en) * | 2020-04-30 | 2022-06-28 | 成都民航空管科技发展有限公司 | Low altitude warning method, system, data processing terminal and medium for terminal area |
| WO2022143764A1 (en) * | 2020-12-31 | 2022-07-07 | 江苏数字鹰科技股份有限公司 | Police unmanned aerial vehicle having crash protection function |
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Granted publication date: 20191108 |