CN206857010U - A kind of rotor wing unmanned aerial vehicle fall safety control system - Google Patents
A kind of rotor wing unmanned aerial vehicle fall safety control system Download PDFInfo
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- CN206857010U CN206857010U CN201720596911.4U CN201720596911U CN206857010U CN 206857010 U CN206857010 U CN 206857010U CN 201720596911 U CN201720596911 U CN 201720596911U CN 206857010 U CN206857010 U CN 206857010U
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- comparator
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- logic circuit
- parachute
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Abstract
A kind of rotor wing unmanned aerial vehicle fall safety control system, the trigger device opened including parachute and control parachute, the trigger device is controlled by remote signal end and automatic triggering system, the automatic triggering system includes height sensor and velocity sensor, and the height sensor output end is connected with first comparator input, the velocity sensor output end is connected with the second comparator input terminal;The first comparator, another input of the second comparator connect a multichannel D/A converter output end；The first comparator and the output end of the second comparator connect the input of one and logic circuit respectively, described to be connected one or logic circuit input respectively with the output end at logic circuit output end and remote signal end, described or logic circuit connects with trigger device control.The utility model can automatically turn on parachute by the height and speed for detecting unmanned plane, so as to avoid personnel and property loss caused by unmanned plane directly falls.
Description
Technical field
The utility model belongs to mechanical field, is related to unmanned air vehicle technique, especially a kind of rotor wing unmanned aerial vehicle fall safety control
System processed.
Background technology
UAV is not carried people to fly using what radio robot or the presetting apparatus provided for oneself manipulated
Device.Unmanned plane is actually the general designation of unmanned vehicle, can be divided into from technical standpoint definition：Depopulated helicopter, nobody
This several major class of fixed-wing aircraft, unmanned multi-rotor aerocraft, unmanned airship, unmanned parasol.Compared with manned aircraft, it has body
The small, low cost of product, it is easy to use the advantages that, find broad application.
But when there are various failures in flight course in rotor wing unmanned aerial vehicle, particularly be remotely controlled failure or to stall when,
Rotor wing unmanned aerial vehicle is in uncontrolled or engine failure, it is impossible to dead-stick landing is utilized as fixed-wing unmanned plane, under direct
Pendant not only causes unmanned plane itself infringement to scrap, it is often more important that in the uncontrolled unmanned plane tenesmus in dense population areas, pounds to ground
Face may also result in casualties and ground property loss, and CN2016107663955 Chinese patent discloses a kind of unmanned plane
Parachute automatic open device, but open for parachute of the parachute when being remotely controlled out of control or disengaging remote control region and do not control then
Means processed.
Utility model content
To overcome technological deficiency present in existing rotor wing unmanned aerial vehicle parachute opening process, the utility model discloses one
Kind rotor wing unmanned aerial vehicle fall safety control system.
Rotor wing unmanned aerial vehicle fall safety control system described in the utility model, including parachute and control parachute opening
Trigger device, it is characterised in that the trigger device is controlled by remote signal end and automatic triggering system, the automatic triggering system
System includes height sensor and velocity sensor, and the height sensor output end is connected with first comparator input, is described
Velocity sensor output end is connected with the second comparator input terminal;Another input of the first comparator, the second comparator
A multichannel D/A converter output end is connected, the D/A converter signal input part is connected with a memory, and the memory is also
It is connected with input control apparatus；
The first comparator and the output end of the second comparator connect the input of one and logic circuit respectively, it is described with
The output end at logic circuit output end and remote signal end connects one or logic circuit input respectively, described or logic circuit with
Trigger device control connection.
Preferably, it is characterised in that the trigger device is the electronic controller of electromagnet, relay or parachute.
Preferably, the input control apparatus is hardware data interface.
, can in the case where being remotely controlled failure using rotor wing unmanned aerial vehicle fall safety control system described in the utility model
With by detect unmanned plane height and speed automatically turn on parachute, so as to avoid personnel caused by unmanned plane directly falls and
Property loss.
Brief description of the drawings
Fig. 1 is that a kind of embodiment structure of rotor wing unmanned aerial vehicle fall safety control system described in the utility model is shown
It is intended to, the entitled DAC- multichannels D/A converter of reference in figure, COMP1- first comparators, the comparators of COMP2- second,
AND- and logic circuit, OR- or logic circuit.
Embodiment
Below in conjunction with the accompanying drawings, specific embodiment of the present utility model is described in further detail.
Rotor wing unmanned aerial vehicle fall safety control system described in the utility model, including parachute and control parachute opening
Trigger device, the trigger device are controlled by remote signal end and automatic triggering system, and the automatic triggering system includes height
Sensor and velocity sensor, the height sensor output end is connected with first comparator COMP1 inputs, the speed passes
Sensor output end is connected with the second comparator COMP2 inputs;The first comparator, another input of the second comparator connect
A multichannel D/A converter DAC output ends are connect, the D/A converter signal input part is connected with a memory, and the memory is also
It is connected with input control apparatus；
The first comparator and the output end of the second comparator connect the input of one and logic circuit AND, institute respectively
State and be connected one or logic circuit OR inputs, described or logic respectively with the output end at logic circuit output end and remote signal end
Circuit connects with trigger device control.
The trigger device of parachute can be the various devices that can be controlled by electric signal, such as electromagnet, relay or electricity
Sub-controller.Controlled under trigger device general state by remote signal end, remote signal end is used to receive remote signal, unmanned plane
When can receive remote signal, trigger device can be remotely-controlled startup, and remote signal end priority level is generally greater than automatic touch
Hair system.
When remote signal end can not receive remote signal, remote signal end is arranged to export low level signal, now
The signal of automatic triggering system can by or logic circuit transmit.
Automatic triggering system decides whether to open parachute, height biography by the height and velocity sensor that detect unmanned plane
The height and speed of sensor and velocity sensor detection unmanned plane, when the height for finding unmanned plane is less than preset value, and speed
During higher than preset value, now general unmanned plane is in relatively low spatial domain, and speed is still higher, because rotor wing unmanned aerial vehicle power has
Limit, is all not easy to reach fair speed in the horizontal direction, only during free fall with ascent direction, after some time it is possible to reach tenesmus shape at a high speed
State；If still departing from remote state, the state, which is believed that, to be in extreme danger, and first comparator and the second comparator are by sensor
Compared with the analog voltage that multi-channel digital and analogue converter exports, output high level signal arrives electric with logic the analog voltage of output
Road, with logic circuit judge now unmanned plane be in low clearance, high speed precarious position, then output a control signal to triggering fill
Put, because now remote signal has not worked, therefore trigger device is only controlled by automatic triggering system.
The preset value and speed preset value of unmanned plane height can be characterized by one digital value of memory storage, by more
Road DAC outputs be converted into Sensor Analog Relay System voltage ratio that analog voltage and two comparators receive compared with.The number of memory storage
Word value can be inputted by input control apparatus, and input control apparatus is usually a hardware data interface, such as USB interface,
RS485 interfaces etc., data input is carried out using external equipment such as notebook computer etc..
, can in the case where being remotely controlled failure using rotor wing unmanned aerial vehicle fall safety control system described in the utility model
With by detect unmanned plane height and speed automatically turn on parachute, so as to avoid personnel caused by unmanned plane directly falls and
Property loss.
Previously described is each preferred embodiment of the present utility model, the preferred embodiment in each preferred embodiment
If not obvious contradictory or premised on a certain preferred embodiment, each preferred embodiment can be arbitrarily superimposed
It is applied in combination, the design parameter in the embodiment and embodiment is merely to clearly state the utility model of utility model people
Verification process, and be not used to limit scope of patent protection of the present utility model, scope of patent protection of the present utility model still with
Its claims is defined, every equivalent structure change made with specification of the present utility model and accompanying drawing content, similarly
It should be included in the scope of protection of the utility model.
Claims (3)
1. a kind of rotor wing unmanned aerial vehicle fall safety control system, including the trigger device that parachute and control parachute are opened, its
It is characterised by, the trigger device is controlled by remote signal end and automatic triggering system, and the automatic triggering system includes height
Sensor and velocity sensor, the height sensor output end is connected with first comparator input, the velocity sensor
Output end is connected with the second comparator input terminal;The first comparator, another input connection more than one of the second comparator are logical
Road D/A converter output end, the D/A converter signal input part are connected with a memory, and the memory is also associated with inputting
Control device；
The first comparator and the output end of the second comparator connect the input of one and logic circuit, described and logic respectively
The output end at circuit output end and remote signal end connects one or logic circuit input, described or logic circuit and triggering respectively
Device control connection.
2. rotor wing unmanned aerial vehicle fall safety control system as claimed in claim 1, it is characterised in that the trigger device is electricity
The electronic controller of magnet, relay or parachute.
3. rotor wing unmanned aerial vehicle fall safety control system as claimed in claim 1, it is characterised in that the input control apparatus
For hardware data interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720596911.4U CN206857010U (en) | 2017-05-26 | 2017-05-26 | A kind of rotor wing unmanned aerial vehicle fall safety control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720596911.4U CN206857010U (en) | 2017-05-26 | 2017-05-26 | A kind of rotor wing unmanned aerial vehicle fall safety control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206857010U true CN206857010U (en) | 2018-01-09 |
Family
ID=60825103
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720596911.4U Expired - Fee Related CN206857010U (en) | 2017-05-26 | 2017-05-26 | A kind of rotor wing unmanned aerial vehicle fall safety control system |
Country Status (1)
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108238266A (en) * | 2018-01-15 | 2018-07-03 | 天津聚飞创新科技有限公司 | Unmanned plane safe falling method, apparatus and unmanned plane |
| CN108298093A (en) * | 2018-01-26 | 2018-07-20 | 大连理工大学 | Parachute rope draw off gear |
| CN108313312A (en) * | 2018-01-25 | 2018-07-24 | 芜湖应天光电科技有限责任公司 | A kind of unmanned plane drop preventer |
| CN109050940A (en) * | 2018-07-20 | 2018-12-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Plane umbrella cabin hood jettison gear and aircraft |
| CN111655581A (en) * | 2018-03-27 | 2020-09-11 | 株式会社尼罗沃克 | Unmanned aerial vehicle, and control system and control program thereof |
| CN113184197A (en) * | 2021-05-27 | 2021-07-30 | 江苏航空职业技术学院 | Unmanned aerial vehicle parachute device detonating circuit based on PX4 flight control |
-
2017
- 2017-05-26 CN CN201720596911.4U patent/CN206857010U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108238266A (en) * | 2018-01-15 | 2018-07-03 | 天津聚飞创新科技有限公司 | Unmanned plane safe falling method, apparatus and unmanned plane |
| CN108313312A (en) * | 2018-01-25 | 2018-07-24 | 芜湖应天光电科技有限责任公司 | A kind of unmanned plane drop preventer |
| CN108298093A (en) * | 2018-01-26 | 2018-07-20 | 大连理工大学 | Parachute rope draw off gear |
| CN111655581A (en) * | 2018-03-27 | 2020-09-11 | 株式会社尼罗沃克 | Unmanned aerial vehicle, and control system and control program thereof |
| CN111655581B (en) * | 2018-03-27 | 2024-03-19 | 株式会社尼罗沃克 | Unmanned aerial vehicle, control system thereof, and computer-readable recording medium |
| CN109050940A (en) * | 2018-07-20 | 2018-12-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Plane umbrella cabin hood jettison gear and aircraft |
| CN109050940B (en) * | 2018-07-20 | 2022-06-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft parachute bay cover throwing device and aircraft |
| CN113184197A (en) * | 2021-05-27 | 2021-07-30 | 江苏航空职业技术学院 | Unmanned aerial vehicle parachute device detonating circuit based on PX4 flight control |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180109 Termination date: 20180526 |