CN109850171A - A kind of measurement of small drone air speed and safety switch integrated apparatus - Google Patents
A kind of measurement of small drone air speed and safety switch integrated apparatus Download PDFInfo
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- CN109850171A CN109850171A CN201711212055.9A CN201711212055A CN109850171A CN 109850171 A CN109850171 A CN 109850171A CN 201711212055 A CN201711212055 A CN 201711212055A CN 109850171 A CN109850171 A CN 109850171A
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- air speed
- speed measurement
- pressure pipeline
- static pressure
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Abstract
The present invention provides a kind of measurement of small drone air speed and safety switch integrated apparatus, including air speed measurement portion and positioned at the safety switch portion of air speed measurement portion rear end face, the inside of air speed measurement portion is equipped with static pressure pipeline and dynamic pressure pipeline, be connected there are two setting relatively on the side wall of air speed measurement portion with the upper end of static pressure pipeline static pressure aperture, dynamic pressure pipeline includes horizontal part and vertical portion, the front end of air speed measurement portion is equipped with the dynamic pressure aperture that is connected with the horizontal part, the lower end of air speed measurement portion is equipped with the first annular boss being connected with dynamic pressure pipeline and the second annular convex platform being connected with static pressure pipeline, safety switch portion includes hollow shell, pressing lever and the electronic switch opened and closed for unmanned plane motor, red LED lamp patch and green LED lamp patch are fixed on the side wall of electronic switch, red LED lamp patch and green LED light patch is electrically connected with electronic switch, and the present invention has many advantages, such as safety, measures convenient for air speed.
Description
Technical field
The invention belongs to air vehicle technique fields, more particularly, to a kind of measurement of small drone air speed and safety switch one
Body makeup is set.
Background technique
Under normal conditions the flying speed of unmanned plane by airspeed sensor provide, conventional airspeed sensor by diameter not
Same concentric steel pipe composition, the front end of pitot is long straight and sharp, is not easy to be mounted on the lesser unmanned plane of size, Er Qie
It is easily damaged pitot when UAV Landing, and is easy to damage ground staff or other objects, in addition, in unmanned plane
It being easy after energization because artificial touching Oil Switch reason causes motor to start suddenly, aircraft is out of control to hide some dangers for for safety, because
How this can obtain the starting of the control aircrafts electric machinery of accurate air speed data and safety, facilitate air speed to survey to reach
The problem of amount, the effect for realizing self security protection of operator are urgent need to resolve.
Summary of the invention
The problem to be solved in the present invention is to provide a kind of safety, convenient for the small drone air speed measurement of air speed measurement and peace
Full switch integrated apparatus.
In order to solve the above technical problems, the technical solution adopted by the present invention is that: a kind of measurement of small drone air speed and peace
Full switch integrated apparatus, including air speed measurement portion and positioned at the safety switch portion of the air speed measurement portion rear end face, the sky
The inside of fast measurement portion is equipped with static pressure pipeline and dynamic pressure pipeline, and the static pressure pipeline is set close to the front end of the air speed measurement portion
Set, it is opposite on the side wall of the air speed measurement portion to set there are two static pressure aperture, two static pressure apertures with the static tube
The upper end in road is connected, and the dynamic pressure pipeline includes horizontal part and vertical portion, and the horizontal position is upper in the static pressure pipeline
Side, the vertical portion are arranged in parallel with the static pressure pipeline, and the front end of the air speed measurement portion is equipped with dynamic pressure aperture, the dynamic pressure
Aperture is connected with the horizontal part, and the lower end of the air speed measurement portion is first annular equipped with being connected with the dynamic pressure pipeline
Boss and the second annular convex platform being connected with the static pressure pipeline, the internal diameter of the first annular boss and the second annular convex platform
Equal with the internal diameter of the dynamic pressure pipeline and static pressure pipeline respectively, the first annular boss passes through respectively with the second annular convex platform
Hose is connected with the pitot aperture and static port for flying control end measurement module, and the safety switch portion includes hollow shell, pressing
Bar and for unmanned plane motor opening and closing electronic switch, one end of the pressing lever be located at the shell inside and the electronics
The press-side of switch is connected, the other end of the pressing lever be located at the outside of the shell and with the air speed measurement portion
Upper surface is flush, the shell and air speed measurement portion integrated molding and the shell and air speed measurement portion homogeneous transparent
Material is fixed with red LED lamp patch and green LED lamp patch, the red LED lamp patch on the side wall of the electronic switch
Piece and green LED lamp patch are electrically connected with the electronic switch.
Further, the front end of the air speed measurement portion is in semi-cylindrical.
Further, the diameter of the static pressure aperture is 0.5mm.
Further, the first groove is provided along its length on the pressing lever, the lower end of first groove is run through
The lower end surface of the pressing lever, the side wall lower ends of first groove are opposite to be equipped with convex block, the convex block and first groove
Side wall be vertically arranged, the press-side of the electronic switch is equipped with the second groove to match with the convex block, the electronic cutting
Pass is flexibly connected with the pressing lever by second groove and convex block.
Further, the electronic switch is six foot self-lock switch, and the six feet self-lock switch includes for being red LED
The first contact and the second contact of lamp patch and the power supply of green LED lamp patch, the be electrically connected with the red LED lamp patch
Three contacts and the 4th contact and the 5th contact and the 6th contact being electrically connected with the green LED lamp patch, the unmanned plane
The signal wire of motor is electrically connected with the 5th contact and the 6th contact.
Further, the winged control end measurement module is the high-altitude ADM airspeed module.
Compared with prior art, the present invention has the advantage that is with beneficial effect:
1, the safety switch portion of unmanned plane and air speed measurement portion are carried out integrated design by the present invention, are effectively reduced and are being flown
The opening on machine surface increases the complete appearance of aircraft, meanwhile, static pressure pipeline and dynamic pressure pipeline use in air speed measurement portion
Twin flue setting has effectively abandoned the long straight and sharp structure in traditional pitot front end, has avoided air speed during aircraft landing
Damage of the pipe to ground handling operator and other objects, in addition, setting safety switch passes through control unmanned plane motor signal line
It disconnects and the starting of control unmanned plane motor, unmanned plane generation the accidental activation of ground the case where can be effectively prevent.
2, air speed measurement portion of the present invention and shell are disposed as transparent material, and red LED is arranged on electronic switch
The light of lamp patch and green LED lamp patch, LED light patch is cast out by the air speed measurement portion and shell of transparent material,
The color that LED light patch is shown is confirmed convenient for operator, also, by the judgement to display color, can help operator
Member judges the working condition of unmanned plane motor, improves the safety of unmanned plane.
Detailed description of the invention
Fig. 1 is that a kind of small drone air speed measurement of the present invention and the overall structure of safety switch integrated apparatus are illustrated
Figure.
Fig. 2 is the left view structural representation of Fig. 1.
Fig. 3 is the present invention a kind of pressing lever and electronic cutting of small drone air speed measurement and safety switch integrated apparatus
The connection structure diagram of pass.
Fig. 4 is a kind of structure of small drone air speed measurement and the electronic switch of safety switch integrated apparatus of the present invention
Schematic diagram.
Fig. 5 is a kind of LED light two states of small drone air speed measurement and safety switch integrated apparatus of the present invention
Under electric operation control circuit figure.
Fig. 6 is that a kind of small drone air speed measurement of the present invention and the assembling structure of safety switch integrated apparatus are illustrated
Figure.
In figure: 1- air speed measurement portion；2- safety switch portion；3- static pressure pipeline；4- dynamic pressure pipeline；5- static pressure aperture；6- is dynamic
Press off hole；The first annular boss of 7-；The second annular convex platform of 8-；9- red LED lamp patch；10- green LED lamp patch；11- first
Groove；12- convex block；The second groove of 13-；The first contact 14-；The second contact 15-；16- third contact；The 4th contact 17-；18-
5th contact；The 6th contact 19-；201- shell；202- pressing lever；203- electronic switch；401- horizontal part；The vertical portion 402-.
Specific embodiment
It elaborates with reference to the accompanying drawing to a specific embodiment of the invention.
A kind of measurement of small drone air speed and safety switch integrated apparatus, as shown in fig. 6, the device is arranged at nobody
The upside of machine fuselage, exposed portion 30mm are located on the upside of fuselage, and the structure that the point for having abandoned traditional pitot is long, safety
Property higher, pitot and ground face contact the case where damaging when avoiding unmanned plane landing.
As Figure 1-Figure 5, a kind of small drone air speed measurement is measured with safety switch integrated apparatus, including air speed
Portion 1 and positioned at the safety switch portion 2 of 1 rear end face of air speed measurement portion, the inside of the air speed measurement portion 1 is equipped with static pressure pipeline
3 and dynamic pressure pipeline 4, the static pressure pipeline 3 is arranged close to the front end of the air speed measurement portion 1, the side wall of the air speed measurement portion 1
Upper to be set relatively there are two static pressure aperture 5, two static pressure apertures 5 are connected with the upper end of the static pressure pipeline 3, described dynamic
Pressure pipeline 4 includes horizontal part 401 and vertical portion 402, and the horizontal part 401 is located at the top of the static pressure pipeline 3, described vertical
Portion 402 is arranged in parallel with the static pressure pipeline 3, and the front end of the air speed measurement portion 1 is equipped with dynamic pressure aperture 6, the dynamic pressure aperture 6
It is connected with the horizontal part 401, the lower end of the air speed measurement portion 1 is equipped with the first ring being connected with the dynamic pressure pipeline 4
Shape boss 7 and the second annular convex platform 8 being connected with the static pressure pipeline 3, the first annular boss 7 and the second annular convex platform
8 internal diameter is equal with the internal diameter of the dynamic pressure pipeline 4 and static pressure pipeline 3 respectively, the first annular boss 7 and the second convex annular
Platform 8 is connected by hose with the pitot aperture and static port for flying control end measurement module respectively, is flown control end measurement module and is passed hose
The air pressure passed is converted to electricity data, is then resolved by flying control processing unit analysis, the winged control end measurement module is the high-altitude ADM
Airspeed module, the hose generally use soft silicone tube, durable, long service life, and the safety switch portion 2 includes hollow
Shell 201, pressing lever 202 and for unmanned plane motor opening and closing electronic switch 203, one end of the pressing lever 202 is located at
The inside of the shell 201 is connected with the press-side of the electronic switch 203, and the other end of the pressing lever 202 is located at institute
It states the outside of shell 201 and is flush with the upper surface of the air speed measurement portion 1, the shell 201 is measured with the air speed
Portion 1 is integrally formed and the shell 201 and 1 homogeneous transparent material of air speed measurement portion, solid on the side wall of the electronic switch 203
Surely be equipped with red LED lamp patch 9 and green LED lamp patch 10, the red LED lamp patch 9 and green LED lamp patch 10 with
The electronic switch 203 is electrically connected, and the electronic switch 203 is six foot self-lock switch, and the six feet self-lock switch includes using
In the first contact 14 and the second contact 15 that power for red LED lamp patch 9 and green LED lamp patch 10 and the red LED
Third contact 16 and the 4th contact 17 that lamp patch 9 is electrically connected and the with the green LED lamp patch 10 electric connection the 5th
Contact 18 and the 6th contact 19, the signal wire of the unmanned plane motor are electrically connected with the 5th contact 18 and the 6th contact 19,
When third contact 16 and the 4th contact 17 are in connected state, red LED lamp patch 9 is lighted, at this point, 185 He of the 5th contact
6th contact 19 is in an off state, and motor signal line is also at off-state, and motor is in working condition, presses when pressing
When bar 202, pressing lever 202 drives electronic switch 203, and the 5th contact 18 is connected to the 6th contact 19, green LED lamp patch downwards
10 light, and motor is also switched on, in running order, by the operation to electronic switch 203, to control the work shape of motor
State can effectively prevent unmanned plane generation the accidental activation of ground the case where, while electronic switch 203 is opened using six feet are self-locking
It closes, is pressed and resetted by the included elastic force of switch, it is easy to operate, it is at low cost.
Further, the front end of the air speed measurement portion 1 is in semi-cylindrical, is not only convenient for adding using this round and smooth design
Work, while the resistance of air is reduced, improve the accuracy of air speed measurement and the performance of aircraft entirety.
Further, the diameter of the static pressure aperture 5 is 0.5mm.
Further, the first groove 11 is provided along its length on the pressing lever 202, under first groove 11
The lower end surface of the pressing lever 202 is run through at end, and the side wall lower ends of first groove 11 are opposite to be equipped with convex block 12, the convex block 12
It is vertically arranged with the side wall of first groove 11, the press-side of the electronic switch 203 is equipped with to match with the convex block 12
The second groove 13, the electronic switch 203 and the pressing lever 202 by second groove 13 and 12 activity of convex block even
It connects, facilitates the connection and disassembly between pressing lever 202 and electronic switch 203.
The course of work of the invention are as follows: air speed measurement of the invention and safety switch integrated apparatus are installed to nothing first
The upside of man-machine fuselage makes the present apparatus expose the length 30mm of fuselage, the machine of the front end direction and unmanned plane of air speed measurement portion 1
Head direction is consistent, and electronic switch 203 can be carried out using six foot self-locking type switchs of included spring by switching the elastic force of itself
It presses and resets, it is easy to operate, it is red when the third contact 16 of electronic switch 203 and the 4th contact 17 are in connected state
LED light patch 9 lights, at this point, the 5th contact 18 and the 6th contact 19 are in an off state, motor signal line is also at disconnection shape
State, motor is in working condition, and when pressing pressing lever 202, pressing lever 202 drives electronic switch 203 downwards, the 5th contact
18 are connected to the 6th contact 19, and green LED lamp patch 10 lights, and motor is also switched on, in running order, LED light patch
Light is cast out by the air speed measurement portion 1 and shell 201 of transparent material, confirms that LED light patch is shown convenient for operator
Color operator can be helped to sentence the working condition of unmanned plane motor also, by the judgement to display color
It is disconnected, the safety of unmanned plane is improved, in addition, the first annular boss 7 of 1 lower end of air speed measurement portion and the second annular convex platform 8 are divided
It is not connect with one end of hose, the other end of the hose on first annular boss 7 is connected with the pitot aperture for flying control end measurement module
Logical, the other end of the hose on the second annular convex platform 8 is connected with the static port for flying control end measurement module, in unmanned plane during flying mistake
Cheng Zhong is passed through the barometric information in high-altitude by dynamic pressure pipeline 3 and static pressure pipeline 4 by dynamic pressure aperture 6 and static pressure aperture 5 respectively
Air pressure is transmitted in the pitot aperture and static port for flying control end measurement module by hose, and then is flown control end and be converted to the air pressure of transmitting
Electricity data carries out analysis resolving by flying control processing unit.
One embodiment of the present invention has been described in detail above, but the content is only preferable implementation of the invention
Example, should not be considered as limiting the scope of the invention.It is all according to all the changes and improvements made by the present patent application range
Deng should still be within the scope of the patent of the present invention.
Claims (6)
1. a kind of measurement of small drone air speed and safety switch integrated apparatus, it is characterised in that: including air speed measurement portion and
Positioned at the safety switch portion of the air speed measurement portion rear end face, the inside of the air speed measurement portion is equipped with static pressure pipeline and dynamic pressure tube
Road, the static pressure pipeline are arranged close to the front end of the air speed measurement portion, opposite on the side wall of the air speed measurement portion to be equipped with two
A static pressure aperture, two static pressure apertures are connected with the upper end of the static pressure pipeline, and the dynamic pressure pipeline includes level
Portion and vertical portion, the horizontal position are arranged in parallel in the top of the static pressure pipeline, the vertical portion with the static pressure pipeline,
The front end of the air speed measurement portion is equipped with dynamic pressure aperture, and the dynamic pressure aperture is connected with the horizontal part, the air speed measurement
The lower end in portion is equipped with the first annular boss being connected with the dynamic pressure pipeline and the second ring being connected with the static pressure pipeline
The internal diameter of shape boss, the first annular boss and the second annular convex platform internal diameter with the dynamic pressure pipeline and static pressure pipeline respectively
Equal, the first annular boss and the second annular convex platform pass through hose respectively and fly the pitot aperture and static pressure of control end measurement module
Mouth is connected, and the safety switch portion includes hollow shell, pressing lever and the electronic switch for the opening and closing of unmanned plane motor, institute
The one end for stating pressing lever is located at the inside of the shell and is connected with the press-side of the electronic switch, the pressing lever it is another
End is located at the outside of the shell and is flush with the upper surface of the air speed measurement portion, and the shell and the air speed measure
Portion is integrally formed and the shell and air speed measurement portion homogeneous transparent material, is fixed on the side wall of the electronic switch red
Color LED light patch and green LED lamp patch, the red LED lamp patch and green LED lamp patch are powered-down with the electronic cutting
Property connection.
2. a kind of small drone air speed measurement according to claim 1 and safety switch integrated apparatus, feature exist
In: the front end of the air speed measurement portion is in semi-cylindrical.
3. a kind of small drone air speed measurement according to claim 1 and safety switch integrated apparatus, feature exist
In: the diameter of the static pressure aperture is 0.5mm.
4. a kind of small drone air speed measurement according to claim 1 and safety switch integrated apparatus, feature exist
In: the first groove is provided along its length on the pressing lever, the lower end of first groove is under the pressing lever
End face, the side wall lower ends of first groove are opposite to be equipped with convex block, and the side wall of the convex block and first groove is vertically arranged,
The press-side of the electronic switch is equipped with the second groove to match with the convex block, and the electronic switch and the pressing lever are logical
It crosses second groove and convex block is flexibly connected.
5. a kind of small drone air speed measurement according to claim 4 and safety switch integrated apparatus, feature exist
In: the electronic switch is six foot self-lock switch, and the six feet self-lock switch includes for being red LED lamp patch and green
The first contact and the second contact of the power supply of LED light patch, the third contact and the 4th being electrically connected with the red LED lamp patch
Contact and the 5th contact and the 6th contact being electrically connected with the green LED lamp patch, the signal wire of the unmanned plane motor
It is electrically connected with the 5th contact and the 6th contact.
6. a kind of miniature self-service man air speed measurement according to claim 1 and safety switch integrated apparatus, feature exist
In: the winged control end measurement module is the high-altitude ADM airspeed module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711212055.9A CN109850171B (en) | 2017-11-28 | 2017-11-28 | Airspeed measurement and safety switch integrated device for small unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711212055.9A CN109850171B (en) | 2017-11-28 | 2017-11-28 | Airspeed measurement and safety switch integrated device for small unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109850171A true CN109850171A (en) | 2019-06-07 |
| CN109850171B CN109850171B (en) | 2023-09-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711212055.9A Active CN109850171B (en) | 2017-11-28 | 2017-11-28 | Airspeed measurement and safety switch integrated device for small unmanned aerial vehicle |
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| US20120046792A1 (en) * | 2010-08-11 | 2012-02-23 | Secor Russell P | Wireless sensors system and method of using same |
| US20120089362A1 (en) * | 2010-10-08 | 2012-04-12 | Thales | System for Determining the Airspeed of an Aircraft |
| US20150360794A1 (en) * | 2014-05-12 | 2015-12-17 | Airbus Helicopters | Rotorcraft having an airspeed sensor located at the top of a tail fin of the rotorcraft |
| CN106092665A (en) * | 2016-06-24 | 2016-11-09 | 华中科技大学 | A kind of pitot aerator |
| CN206068178U (en) * | 2016-09-20 | 2017-04-05 | 北京韦加无人机科技股份有限公司 | A kind of pitot and unmanned plane |
| CN207670674U (en) * | 2017-11-28 | 2018-07-31 | 天津天航智远科技有限公司 | A kind of small drone air speed measures and safety switch integrated apparatus |
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2017
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Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0510961A (en) * | 1991-07-02 | 1993-01-19 | Mitsubishi Heavy Ind Ltd | Pitot static pressure tube with cap |
| CN1303479A (en) * | 1998-05-26 | 2001-07-11 | N·E·朱可夫斯基教授中央航空流体力学学院 | Pitot-static tube |
| US20030140704A1 (en) * | 2002-01-31 | 2003-07-31 | Kurtz Anthony D. | Static pitot transducer |
| CN101551402A (en) * | 2009-03-20 | 2009-10-07 | 南京吉纳波环境测控有限公司 | Pitot tube used for fixing continuous and automatic monitoring system of pollution source fume |
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| US20120089362A1 (en) * | 2010-10-08 | 2012-04-12 | Thales | System for Determining the Airspeed of an Aircraft |
| US20150360794A1 (en) * | 2014-05-12 | 2015-12-17 | Airbus Helicopters | Rotorcraft having an airspeed sensor located at the top of a tail fin of the rotorcraft |
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| CN207670674U (en) * | 2017-11-28 | 2018-07-31 | 天津天航智远科技有限公司 | A kind of small drone air speed measures and safety switch integrated apparatus |
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| CN109850171B (en) | 2023-09-29 |
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