CN109850171B - Airspeed measurement and safety switch integrated device for small unmanned aerial vehicle - Google Patents
Airspeed measurement and safety switch integrated device for small unmanned aerial vehicle Download PDFInfo
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- CN109850171B CN109850171B CN201711212055.9A CN201711212055A CN109850171B CN 109850171 B CN109850171 B CN 109850171B CN 201711212055 A CN201711212055 A CN 201711212055A CN 109850171 B CN109850171 B CN 109850171B
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Abstract
The invention provides an integrated device for airspeed measurement and safety switch of a small unmanned aerial vehicle, which comprises an airspeed measurement part and a safety switch part positioned on the rear end face of the airspeed measurement part, wherein a static pressure pipeline and a dynamic pressure pipeline are arranged in the airspeed measurement part, two static pressure holes communicated with the upper end of the static pressure pipeline are oppositely arranged on the side wall of the airspeed measurement part, the dynamic pressure pipeline comprises a horizontal part and a vertical part, the front end of the airspeed measurement part is provided with a dynamic pressure hole communicated with the horizontal part, the lower end of the airspeed measurement part is provided with a first annular boss communicated with the dynamic pressure pipeline and a second annular boss communicated with the static pressure pipeline, the safety switch part comprises a hollow shell, a pressing rod and an electronic switch for opening and closing a motor of the unmanned aerial vehicle, and a red LED lamp patch and a green LED lamp patch are fixedly arranged on the side wall of the electronic switch, and are electrically connected with the electronic switch.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an integrated device for airspeed measurement and safety switch of a small unmanned aerial vehicle.
Background
Under the normal condition, the flying speed of the unmanned aerial vehicle is provided by virtue of an airspeed sensor, the conventional airspeed sensor consists of concentric steel pipes with different diameters, the front end of the airspeed pipe is long and straight and sharp, the airspeed pipe is inconvenient to install on the unmanned aerial vehicle with smaller size, the airspeed pipe is easy to damage when the unmanned aerial vehicle lands, ground personnel or other objects are easy to damage, in addition, the motor is easy to start suddenly due to the fact that an accelerator switch is touched by people after the unmanned aerial vehicle is electrified, and the aircraft is out of control and buried in a safe way, so that the aircraft can obtain accurate airspeed data, and the starting of the aircraft motor can be safely controlled, so that the effects of facilitating airspeed measurement and realizing self-safety protection of operators are the problems to be solved urgently.
Disclosure of Invention
The invention aims to solve the problem of providing a small unmanned aerial vehicle airspeed measurement and safety switch integrated device which is safe and convenient for airspeed measurement.
In order to solve the technical problems, the invention adopts the following technical scheme: the utility model provides a small-size unmanned aerial vehicle airspeed measurement and safety switch integrated device, includes airspeed measurement portion and is located airspeed measurement portion rear end face's safety switch portion, airspeed measurement portion's inside is equipped with static pressure pipeline and dynamic pressure pipeline, static pressure pipeline is close to airspeed measurement portion's front end setting, be equipped with two static pressure trompils relatively on airspeed measurement portion's the lateral wall, two static pressure trompil all with static pressure pipeline's upper end is linked together, dynamic pressure pipeline includes horizontal part and vertical portion, horizontal part is located static pressure pipeline's top, vertical portion with static pressure pipeline parallel arrangement, airspeed measurement portion's front end is equipped with dynamic pressure trompil, dynamic pressure trompil with horizontal part is linked together, airspeed measurement portion's lower extreme be equipped with dynamic pressure pipeline be linked together first annular boss and with static pressure pipeline's second annular boss is linked together, the inner diameters of the first annular boss and the second annular boss are equal to the inner diameters of the dynamic pressure pipeline and the static pressure pipeline respectively, the first annular boss and the second annular boss are connected with a dynamic pressure port and a static pressure port of the flight control end measuring module respectively through hoses, the safety switch part comprises a hollow shell, a pressing rod and an electronic switch for opening and closing an unmanned aerial vehicle motor, one end of the pressing rod is positioned in the shell and connected with the pressing end of the electronic switch, the other end of the pressing rod is positioned on the outer side of the shell and is flush with the upper end face of the airspeed measuring part, the shell and the airspeed measuring part are integrally formed, the shell and the airspeed measuring part are made of uniform transparent materials, a red LED lamp patch and a green LED lamp patch are fixedly arranged on the side wall of the electronic switch, the red LED lamp patch and the green LED lamp patch are electrically connected with the electronic switch.
Further, the front end of the airspeed measurement part is semi-cylindrical.
Further, the hydrostatic aperture has a diameter of 0.5mm.
Further, the pressing rod is provided with a first groove along the length direction of the pressing rod, the lower end of the first groove penetrates through the lower end face of the pressing rod, a bump is arranged at the lower end of the side wall of the first groove relatively, the bump is perpendicular to the side wall of the first groove, the pressing end of the electronic switch is provided with a second groove matched with the bump, and the electronic switch is movably connected with the pressing rod through the second groove and the bump.
Further, the electronic switch is a six-pin self-locking switch, the six-pin self-locking switch comprises a first contact and a second contact for supplying power to the red LED lamp patch and the green LED lamp patch, a third contact and a fourth contact which are electrically connected with the red LED lamp patch, and a fifth contact and a sixth contact which are electrically connected with the green LED lamp patch, and a signal wire of the unmanned aerial vehicle is electrically connected with the fifth contact and the sixth contact.
Further, the flight control end measurement module is an ADM altitude airspeed module.
Compared with the prior art, the invention has the advantages and beneficial effects that:
1. according to the invention, the safety switch part and the airspeed measurement part of the unmanned aerial vehicle are integrally designed, so that the opening on the surface of the aircraft is effectively reduced, the appearance integrity of the aircraft is improved, meanwhile, the static pressure pipeline and the dynamic pressure pipeline in the airspeed measurement part are arranged in a double pipeline manner, the structure that the front end of the traditional airspeed tube is long and straight and sharp is effectively abandoned, the damage of the airspeed tube to ground operators and other objects in the landing process of the aircraft is avoided, and in addition, the safety switch is arranged to control the disconnection of the unmanned aerial vehicle motor signal line and the starting of the unmanned aerial vehicle motor, so that the situation that the unmanned aerial vehicle is started accidentally on the ground can be effectively prevented.
2. According to the unmanned aerial vehicle, the airspeed measuring part and the shell are both made of transparent materials, the red LED lamp patch and the green LED lamp patch are arranged on the electronic switch, the light of the LED lamp patch is projected out through the airspeed measuring part and the shell made of the transparent materials, an operator can conveniently confirm the color displayed by the LED lamp patch, and the operator can be helped to judge the working state of the unmanned aerial vehicle motor through judging the display color, so that the safety of the unmanned aerial vehicle is improved.
Drawings
Fig. 1 is a schematic diagram of the overall structure of an integrated device for airspeed measurement and safety switch of a small unmanned aerial vehicle.
Fig. 2 is a left-hand structural schematic diagram of fig. 1.
Fig. 3 is a connection structure diagram of a pressing rod and an electronic switch of the integrated device for airspeed measurement and safety switch of the small unmanned aerial vehicle.
Fig. 4 is a schematic structural diagram of an electronic switch of the unmanned aerial vehicle airspeed measurement and safety switch integrated device.
Fig. 5 is a control circuit diagram of the unmanned aerial vehicle airspeed measurement and safety switch integrated device in two states of the LED lamp.
Fig. 6 is a schematic diagram of an assembly structure of an integrated device for airspeed measurement and safety switch of a small unmanned aerial vehicle.
In the figure: 1-airspeed measurement section; 2-a safety switch part; 3-static pressure pipeline; 4-dynamic pressure pipeline; 5-hydrostatic tapping; 6-dynamic pressure tapping; 7-a first annular boss; 8-a second annular boss; 9-red LED lamp patches; 10-green LED lamp patches; 11-a first groove; 12-bump; 13-a second groove; 14-a first contact; 15-a second contact; 16-third contact; 17-fourth contacts; 18-fifth contact; 19-sixth contact; 201-a housing; 202-pressing a rod; 203-an electronic switch; 401-horizontal section; 402-vertical.
Examples
The following detailed description of specific embodiments of the invention refers to the accompanying drawings.
The utility model provides a small-size unmanned aerial vehicle airspeed measurement and safety switch integrated device, as shown in fig. 6, the device sets up in the upside of unmanned aerial vehicle fuselage, and the exposure part is 30mm, is located the fuselage upside to abandoned the long structure of point of traditional airspeed tube, the security is higher, has avoided unmanned aerial vehicle to descend the condition emergence that airspeed tube and ground contact damaged.
As shown in fig. 1-5, the utility model relates to an integrated device for airspeed measurement and safety switch of a small unmanned aerial vehicle, which comprises an airspeed measurement part 1 and a safety switch part 2 positioned on the rear end face of the airspeed measurement part 1, wherein a static pressure pipeline 3 and a dynamic pressure pipeline 4 are arranged in the airspeed measurement part 1, the static pressure pipeline 3 is close to the front end of the airspeed measurement part 1, two static pressure open holes 5 are oppositely arranged on the side wall of the airspeed measurement part 1, the two static pressure open holes 5 are communicated with the upper end of the static pressure pipeline 3, the dynamic pressure pipeline 4 comprises a horizontal part 401 and a vertical part 402, the horizontal part 401 is positioned above the static pressure pipeline 3, the vertical part 402 is arranged in parallel with the static pressure pipeline 3, a dynamic pressure open hole 6 is arranged at the front end of the airspeed measurement part 1, the dynamic pressure open hole 6 is communicated with the horizontal part 401, the lower end of the airspeed measurement part 1 is provided with a first annular boss 7 communicated with the dynamic pressure pipeline 4 and a second annular boss 8 communicated with the static pressure pipeline 3, the inner diameters of the first annular boss 7 and the second annular boss 8 are respectively equal to the inner diameters of the dynamic pressure pipeline 4 and the static pressure pipeline 3, the first annular boss 7 and the second annular boss 8 are respectively connected with a dynamic pressure port and a static pressure port of a flight control end measurement module through a hose, the flight control end measurement module converts air pressure transmitted by the hose into electric quantity data, and then the electric quantity data is analyzed and calculated by a flight control processing unit, the flight control end measurement module is an ADM height airspeed module, the hose is generally a soft silica gel tube, is durable and long in service life, the safety switch part 2 comprises a hollow shell 201, a pressing rod 202 and an electronic switch 203 for opening and closing a unmanned aerial vehicle motor, one end of the pressing rod 202 is located inside the housing 201 and connected to the pressing end of the electronic switch 203, the other end of the pressing rod 202 is located outside the housing 201 and is flush with the upper end surface of the airspeed measurement portion 1, the housing 201 and the airspeed measurement portion 1 are integrally formed, the housing 201 and the airspeed measurement portion 1 are made of transparent materials uniformly, a red LED lamp patch 9 and a green LED lamp patch 10 are fixedly arranged on the side wall of the electronic switch 203, the red LED lamp patch 9 and the green LED lamp patch 10 are electrically connected to the electronic switch 203, the electronic switch 203 is a six-pin self-locking switch, the six-pin self-locking switch comprises a first contact 14 and a second contact 15 for supplying power to the red LED lamp patch 9 and the green LED lamp patch 10, a third contact 16 and a fourth contact 17 electrically connected to the red LED lamp patch 9, and a fifth contact 18 and a sixth contact 19 electrically connected to the green LED lamp patch 10, the signal wire of the unmanned aerial vehicle motor is electrically connected with the fifth contact 18 and the sixth contact 19, when the third contact 16 and the fourth contact 17 are in a communication state, the red LED lamp patch 9 is turned on, at the moment, the fifth contact 185 and the sixth contact 19 are in an off state, the motor signal wire is also in an off state, the motor is in a to-be-operated state, when the pressing rod 202 is pressed down, the pressing rod 202 drives the electronic switch 203 to be downwards, the fifth contact 18 and the sixth contact 19 are communicated, the green LED lamp patch 10 is turned on, the motor is also turned on and is in an operating state, the operating state of the motor is controlled through the operation of the electronic switch 203, the situation that the unmanned aerial vehicle is started accidentally on the ground can be effectively prevented, meanwhile, the electronic switch 203 adopts a six-foot self-locking switch, the switch is pressed down and reset by the self-contained elasticity, so that the operation is convenient and the cost is low.
Furthermore, the front end of the airspeed measuring part 1 is semi-cylindrical, and the smooth design is adopted, so that the processing is convenient, the air resistance is reduced, and the airspeed measuring accuracy and the performance of the whole aircraft are improved.
Further, the hydrostatic aperture 5 has a diameter of 0.5mm.
Further, the pressing rod 202 is provided with a first groove 11 along the length direction thereof, the lower end of the first groove 11 penetrates through the lower end face of the pressing rod 202, the lower end of the side wall of the first groove 11 is provided with a protruding block 12 relatively, the protruding block 12 is perpendicular to the side wall of the first groove 11, the pressing end of the electronic switch 203 is provided with a second groove 13 matched with the protruding block 12, and the electronic switch 203 is movably connected with the pressing rod 202 through the second groove 13 and the protruding block 12, so that connection and disassembly between the pressing rod 202 and the electronic switch 203 are facilitated.
The working process of the invention is as follows: firstly, the airspeed measurement and safety switch integrated device is arranged on the upper side of the unmanned aerial vehicle body, the length of the device exposed out of the unmanned aerial vehicle body is 30mm, the front end of the airspeed measurement part 1 is consistent with the direction of the aircraft nose of the unmanned aerial vehicle, the electronic switch 203 adopts a six-foot self-locking switch with a spring, the electronic switch can be pressed down and reset by the self elastic force of the switch, the operation is convenient, when the third contact 16 and the fourth contact 17 of the electronic switch 203 are in a communicating state, the red LED lamp patch 9 is lightened, at the moment, the fifth contact 18 and the sixth contact 19 are in an off state, a motor signal wire is also in an off state, when the pressing rod 202 is pressed down, the pressing rod 202 drives the electronic switch 203 to be downwards, the fifth contact 18 and the sixth contact 19 are communicated, the green LED lamp patch 10 is lightened, the motor is also turned on, and is in an on state, the brightness of the LED lamp patch is projected out through the airspeed measurement part 1 and the shell 201 which are made of transparent materials, so that an operator can confirm the color displayed by the LED lamp patch, and through judging the display color, the operation state of an unmanned aerial vehicle motor can be helped by the operator, the safety of the unmanned aerial vehicle is improved, in addition, the first annular boss 7 and the second annular boss 8 at the lower end of the airspeed measurement part 1 are respectively connected with one end of a hose, the other end of the hose on the first annular boss 7 is communicated with the dynamic pressure port of the flight control end measurement module, the other end of the hose on the second annular boss 8 is communicated with the static pressure port of the flight control end measurement module, in the flight process of the unmanned aerial vehicle, the air pressure condition of the high altitude is transmitted to the dynamic pressure port and the static pressure port of the flight control end measurement module through the dynamic pressure pipeline 3 and the static pressure pipeline 4 respectively through the hose, and the flight control terminal converts the transmitted air pressure into electric quantity data, and the flight control processing unit analyzes and calculates the electric quantity data.
The foregoing describes one embodiment of the present invention in detail, but the description is only a preferred embodiment of the present invention and should not be construed as limiting the scope of the invention. All equivalent changes and modifications within the scope of the present invention are intended to be covered by the present invention.
Claims (6)
1. Airspeed measurement and safety switch integrated device of unmanned aerial vehicle, its characterized in that: comprises an airspeed measuring part and a safety switch part positioned on the rear end face of the airspeed measuring part, wherein a static pressure pipeline and a dynamic pressure pipeline are arranged in the airspeed measuring part, the static pressure pipeline is arranged close to the front end of the airspeed measuring part, two static pressure open holes are oppositely arranged on the side wall of the airspeed measuring part and are communicated with the upper end of the static pressure pipeline, the dynamic pressure pipeline comprises a horizontal part and a vertical part, the horizontal part is positioned above the static pressure pipeline, the vertical part is arranged in parallel with the static pressure pipeline, the front end of the airspeed measuring part is provided with a dynamic pressure open hole, the dynamic pressure open hole is communicated with the horizontal part, the lower end of the airspeed measuring part is provided with a first annular boss communicated with the dynamic pressure pipeline and a second annular boss communicated with the static pressure pipeline, the inner diameters of the first annular boss and the second annular boss are equal to the inner diameters of the dynamic pressure pipeline and the static pressure pipeline respectively, the first annular boss and the second annular boss are connected with a dynamic pressure port and a static pressure port of the flight control end measuring module respectively through hoses, the safety switch part comprises a hollow shell, a pressing rod and an electronic switch for opening and closing an unmanned aerial vehicle motor, one end of the pressing rod is positioned in the shell and connected with the pressing end of the electronic switch, the other end of the pressing rod is positioned on the outer side of the shell and is flush with the upper end face of the airspeed measuring part, the shell and the airspeed measuring part are integrally formed, the shell and the airspeed measuring part are made of uniform transparent materials, a red LED lamp patch and a green LED lamp patch are fixedly arranged on the side wall of the electronic switch, the red LED lamp patch and the green LED lamp patch are electrically connected with the electronic switch.
2. The unmanned aerial vehicle airspeed measurement and safety switch integrated device according to claim 1, wherein: the front end of the airspeed measurement part is semi-cylindrical.
3. The unmanned aerial vehicle airspeed measurement and safety switch integrated device according to claim 1, wherein: the hydrostatic aperture has a diameter of 0.5mm.
4. The unmanned aerial vehicle airspeed measurement and safety switch integrated device according to claim 1, wherein: the electronic switch is characterized in that a first groove is formed in the pressing rod along the length direction of the pressing rod, the lower end of the first groove penetrates through the lower end face of the pressing rod, a protruding block is arranged at the lower end of the side wall of the first groove relatively, the protruding block is perpendicular to the side wall of the first groove, a second groove matched with the protruding block is formed in the pressing end of the electronic switch, and the electronic switch is movably connected with the pressing rod through the second groove and the protruding block.
5. The unmanned aerial vehicle airspeed measurement and safety switch integrated device of claim 4, wherein: the electronic switch is a six-pin self-locking switch, the six-pin self-locking switch comprises a first contact and a second contact for supplying power to the red LED lamp patch and the green LED lamp patch, a third contact and a fourth contact which are electrically connected with the red LED lamp patch, and a fifth contact and a sixth contact which are electrically connected with the green LED lamp patch, and a signal wire of the unmanned aerial vehicle is electrically connected with the fifth contact and the sixth contact.
6. The unmanned aerial vehicle airspeed measurement and safety switch integrated device according to claim 1, wherein: the flight control end measuring module is an ADM height 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 CN109850171A (en) | 2019-06-07 |
| CN109850171B true 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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| CN (1) | CN109850171B (en) |
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| JPH0510961A (en) * | 1991-07-02 | 1993-01-19 | Mitsubishi Heavy Ind Ltd | Pitot static pressure tube with cap |
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| 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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| 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 |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6688182B2 (en) * | 2002-01-31 | 2004-02-10 | Kulite Semiconductor Products, Inc. | Static pitot transducer |
| US9605857B2 (en) * | 2010-08-11 | 2017-03-28 | Evergreen Telemetry Llc | Wireless sensors system and method of using same |
| FR2965928B1 (en) * | 2010-10-08 | 2013-05-31 | Thales Sa | SYSTEM FOR DETERMINING THE AIR SPEED OF AN AIRCRAFT |
| FR3020799B1 (en) * | 2014-05-12 | 2016-06-03 | Airbus Helicopters | GIRAVION EQUIPPED WITH ANEMOMETER PLACED AT THE TOP OF A REAR DRIFT OF THE GIRAVION |
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Patent Citations (6)
| 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 |
| 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 |
| 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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| CN109850171A (en) | 2019-06-07 |
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