CN207482198U - Unmanned plane stall protection system - Google Patents
Unmanned plane stall protection system Download PDFInfo
- Publication number
- CN207482198U CN207482198U CN201721598546.7U CN201721598546U CN207482198U CN 207482198 U CN207482198 U CN 207482198U CN 201721598546 U CN201721598546 U CN 201721598546U CN 207482198 U CN207482198 U CN 207482198U
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- CN
- China
- Prior art keywords
- unmanned plane
- injection apparatus
- induction controller
- gas cylinder
- compressed gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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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
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model discloses a kind of unmanned plane stall protection system, including power supply, falling protecting device, induction controller and electromagnetic relay；Power supply is electrically connected respectively with falling protecting device, induction controller, and induction controller is electrically connected respectively with falling protecting device and electromagnetic relay；Falling protecting device includes compressed gas cylinder, two-position two-way solenoid valve, injection apparatus and pack；Compressed gas cylinder is connected with injection apparatus；Two-position two-way solenoid valve is controlled by induction controller, and is connected between the pipeline that compressed gas cylinder and injection apparatus are connected, and parachute pack is in injection apparatus.Advantage is when system monitoring to stall signal, dynamical system power supply can be automatically cut off, it can avoid the propeller of unmanned plane and parachute twisted wire, also avoid short circuit, parachute is opened by the way of blast injection, it is connected with induction controller using a two-position two-way solenoid valve and is automatically controlled to realize, avoid the insecure drawback of traditional unfolding mode.
Description
Technical field
The utility model is related to unmanned vehicle field, more particularly to a kind of unmanned plane stall protection system.
Background technology
With the development of Intelligent hardware and Computer Control Technology, unmanned plane starts widely to be made in many fields
With, but since unmanned plane is other than the intelligence of small part height can realize autonomous flight, remaining is substantially needs and leans on
Artificial radio operation, therefore many problems also occur, for example, unmanned plane in flight course due to hardware problem lose it is dynamic
There is radio operation failure etc. in power and regular flight condition or software issue etc..Just need aircraft that can realize self at this time
Protection, existing unmanned plane protection system only takes into account protection hardware, but does not cut off the power, and part unmanned plane
Engine is still working on after out of control or failure, and when parachute ejects, propeller can be twisted with parachute
Line, the unfolding mode of traditional parachute is not very reliable.
Utility model content
The technical problem to be solved by the present invention is to provide flying power can be automatically cut off during a kind of unmanned plane stall,
The reliable unmanned plane stall protection system of parachute unfolding mode.
In order to solve the above-mentioned technical problem, the technical solution of the utility model is：
A kind of unmanned plane stall protection system, including power supply, falling protecting device, induction controller and electromagnetism relay
Device；Power supply is electrically connected respectively with falling protecting device, induction controller, induction controller respectively with falling protecting device and
Electromagnetic relay is electrically connected；Falling protecting device includes compressed gas cylinder, two-position two-way solenoid valve, injection apparatus and pack；It is described
Compressed gas cylinder is connected with injection apparatus；Two-position two-way solenoid valve is controlled by induction controller, and is connected on compressed gas cylinder and spray
Between the pipeline that injection device is connected, parachute pack is in injection apparatus.
Further, injection apparatus includes sealing cover, tracheae and injection road, and tracheae one end is connected with compressed gas cylinder, another
End is connected with injection road, is equipped with sealing cover in the outlet of injection road, two-position two-way solenoid valve is located between tracheae.
Further, the canopy of pack is connected with sealing cover with filament.
Further, induction controller includes gyroscope, PLC battery plates and acceleration transducer；Gyroscope and acceleration
Sensor is electrically connected with PLC battery plates.
Further, electromagnetic relay is mounted in the supply line between power supply and unmanned plane dynamical system.
The utility model is beneficial in that：
(1) after unmanned plane stall is fallen, this system can monitor stall signal, control electricity automatically by induction controller
Magnetic relay automatically cuts off the dynamical system power supply of unmanned plane, can be stirred to avoid the propeller of unmanned plane and the umbrella line of parachute
Together, while the short circuit of unmanned plane internal circuit is also avoided.
(2) parachute is opened by the way of blast injection, utilizes a two-position two-way solenoid valve and sensing
Control device connection automatically controls to realize, avoids the insecure drawback of traditional unfolding mode.
Description of the drawings
Fig. 1 is the utility model structural schematic block diagram；
Fig. 2 is falling protecting device structure diagram；
In figure：1- power supplys, 2- falling protecting devices, 21- packs, 22- injection apparatus, 220- sealing covers, 221- tracheaes,
222- sprays road, 23- two-position two-way solenoid valves, 24- compressed gas cylinders, 3- induction controllers, 31- acceleration transducers, 32-
PLC battery plates, 33- gyroscopes, 4- unmanned plane dynamical systems, 5- electromagnetic relays, 6- cabins.
Specific embodiment
Specific embodiment of the present utility model is described further below in conjunction with the accompanying drawings.It should be noted that
The explanation of these embodiments is used to help to understand the utility model, but do not form the restriction to the utility model.This
Outside, technical characteristic involved in the various embodiments of the present invention described below is as long as they do not conflict with each other
It can be combined with each other.
As shown in Figs. 1-2：
A kind of unmanned plane stall protection system, including power supply 1, falling protecting device 2, induction controller 3 and electromagnetism after
Electric appliance 5；Power supply 1 is electrically connected respectively with falling protecting device 2, induction controller 3, and induction controller 3 is protected respectively with falling
Protection unit 2 and electromagnetic relay 5 are electrically connected；Falling protecting device 2 includes compressed gas cylinder 24, two-position two-way solenoid valve 23, injection
Device 22 and pack 21；Compressed gas cylinder 24 is connected with injection apparatus 22；Two-position two-way solenoid valve 23 is controlled by induction controller
3, and be connected between the pipeline that compressed gas cylinder 24 and injection apparatus 22 are connected, the pack 21 is in injection apparatus 22.
As preference, injection apparatus 22 includes sealing cover 220, tracheae 221 and injection road 222, described 221 one end of tracheae
It is connected with compressed gas cylinder 24, the other end is connected with injection road 222, and sealing cover 220, bi-bit bi-pass are equipped in the outlet of injection road 222
Solenoid valve 23 is located between tracheae 221, and injection apparatus 22 is located at the middle part of cabin 6.
As preference, in order to further ensure the smooth opening of pack 21, canopy and the sealing cover 220 of pack 21 are used carefully
Line is connected, and when sealing cover 220 is sprayed by compressed gas, can pull out pack 21.
As preference, induction controller 3 includes gyroscope 33, PLC battery plates 32 and acceleration transducer 31；The top
Spiral shell instrument 33 and acceleration transducer 31 are electrically connected with PLC battery plates 32, the acceleration and side that such inductor can be according to unmanned plane
Judge unmanned plane state in which to rotation etc., then relevant executive device is controlled to perform protection act by PLC circuit plate.
As preference, in view of circuit protection and avoiding propeller and parachute twisted wire, electromagnetic relay 5 is mounted on electricity
In supply line between source 1 and unmanned plane dynamical system 4, electricity can be controlled when induction controller 3 judges unmanned plane stall
Magnetic relay 5 cuts off the supply of electric power of unmanned plane.
This system principle is the state of flight judged by induction controller 3 where unmanned plane, at judgement unmanned plane
When stall conditions, induction controller 3 can control electromagnetic relay 5 to cut off the power supply of unmanned plane, avoid unmanned plane
Engine works in the case of out of control, propeller is caused to be twisted with the parachute that ejects together with, while also avoid
Unmanned plane internal short circuits after born cause circuit burnout.After cutting off unmanned electro-mechanical force, induction controller 3 can control
Two-position two-way solenoid valve 23 opens the pipeline between compressed gas cylinder 24 and injection apparatus 22, and then high pressure gas can spray parachute
It projects in injection apparatus 22 so as to fulfill the opening action of parachute.
The utility model advantage is that parachute can cut off the power supply of unmanned plane before opening, and twisted wire and circuit is avoided to burn
It ruins, while parachute unfolding mode ensure that the reliability that parachute is opened using spraying high-pressure gas.
The embodiment of the utility model is explained in detail, but the utility model is not limited to be retouched above in association with attached drawing
The embodiment stated.For a person skilled in the art, it is right in the case where not departing from the utility model principle and spirit
These embodiments carry out a variety of change, modification, replacement and modification, still fall in the scope of protection of the utility model.
Claims (5)
1. a kind of unmanned plane stall protection system, it is characterised in that：Including power supply (1), falling protecting device (2), sensing control
Device (3) and electromagnetic relay (5)；The power supply (1) is electrically connected respectively with falling protecting device (2), induction controller (3)
It connects, the induction controller (3) is electrically connected respectively with falling protecting device (2) and electromagnetic relay (5)；The guarantor that falls
Protection unit (2) includes compressed gas cylinder (24), two-position two-way solenoid valve (23), injection apparatus (22) and pack (21)；The compression
Gas cylinder (24) is connected with injection apparatus (22)；The two-position two-way solenoid valve (23) controls (3), and connect by induction controller
Between the connected pipeline of compressed gas cylinder (24) and injection apparatus (22), the pack (21) is in injection apparatus (22).
2. unmanned plane stall protection system according to claim 1, it is characterised in that：The injection apparatus (22) is including close
Cover (220), tracheae (221) and injection road (222), described tracheae (221) one end is connected with compressed gas cylinder (24), the other end and
It sprays road (222) to be connected, is equipped with sealing cover (220) in injection road (222) outlet, the two-position two-way solenoid valve (23) is located at gas
Between pipe (221).
3. unmanned plane stall protection system according to claim 2, it is characterised in that：The canopy of the pack (21) with it is close
Capping (220) is connected with filament.
4. according to claim 1-3 any one of them unmanned plane stall protection systems, it is characterised in that：The sensing control dress
It puts (3) and includes gyroscope (33), PLC battery plates (32) and acceleration transducer (31)；The gyroscope (33) and acceleration sensing
Device (31) is electrically connected with PLC battery plates (32).
5. according to claim 1-3 any one of them unmanned plane stall protection systems, it is characterised in that：The electromagnetic relay
(5) in the supply line between power supply (1) and unmanned plane dynamical system (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721598546.7U CN207482198U (en) | 2017-11-27 | 2017-11-27 | Unmanned plane stall protection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721598546.7U CN207482198U (en) | 2017-11-27 | 2017-11-27 | Unmanned plane stall protection system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207482198U true CN207482198U (en) | 2018-06-12 |
Family
ID=62471405
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721598546.7U Expired - Fee Related CN207482198U (en) | 2017-11-27 | 2017-11-27 | Unmanned plane stall protection system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207482198U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979647A (en) * | 2019-12-24 | 2020-04-10 | 广东电网有限责任公司 | Air fault protection device and method suitable for multi-rotor unmanned aerial vehicle |
| CN112389640A (en) * | 2020-11-27 | 2021-02-23 | 东莞火萤科技有限公司 | Unmanned aerial vehicle control system that stalls |
-
2017
- 2017-11-27 CN CN201721598546.7U patent/CN207482198U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979647A (en) * | 2019-12-24 | 2020-04-10 | 广东电网有限责任公司 | Air fault protection device and method suitable for multi-rotor unmanned aerial vehicle |
| CN112389640A (en) * | 2020-11-27 | 2021-02-23 | 东莞火萤科技有限公司 | Unmanned aerial vehicle control system that stalls |
| CN112389640B (en) * | 2020-11-27 | 2022-07-19 | 东莞火萤科技有限公司 | Unmanned aerial vehicle control system that stalls |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180612 Termination date: 20211127 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |