CN206557391U - A kind of portable electric UAS - Google Patents
A kind of portable electric UAS Download PDFInfo
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- CN206557391U CN206557391U CN201720235333.1U CN201720235333U CN206557391U CN 206557391 U CN206557391 U CN 206557391U CN 201720235333 U CN201720235333 U CN 201720235333U CN 206557391 U CN206557391 U CN 206557391U
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- aircraft
- portable electric
- fuselage
- module
- ground station
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- 238000007726 management method Methods 0.000 claims abstract description 8
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 23
- 238000004891 communication Methods 0.000 claims description 9
- 239000002131 composite material Substances 0.000 claims description 7
- 229920000271 Kevlar® Polymers 0.000 claims description 6
- 230000003750 conditioning effect Effects 0.000 claims description 6
- 239000004761 kevlar Substances 0.000 claims description 6
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 5
- 229910052744 lithium Inorganic materials 0.000 claims description 5
- 229920006231 aramid fiber Polymers 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000011835 investigation Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
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Abstract
The utility model provides a kind of portable electric unmanned plane, including aircraft and hand-held control earth station；Wherein, the hand-held control earth station is used for mission planning, aircraft control and mission payload manipulation；The aircraft is built-in with avionics system, and the avionics system is used for control and the power management of airborne equipment of the aircraft and its mission payload；The aircraft is detachable flight carrier, including fuselage, the detachable wing positioned at the fuselage both sides and the detachable horizontal tail positioned at afterbody.The utility model single-person portable Drones for surveillance is easy to carry, it is not necessary to extra support vehicles and equipment, greatly reduces use cost.The utility model can realize quick assembling simultaneously, take off rapidly, and hand-held control earth station can carry out trajectory planning in real time according to field conditions, and much sooner, accurately live information is collected.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a portable electric unmanned aerial vehicle system.
Background
Conventional unmanned aerial vehicle carries inconveniently when carrying out tasks such as mountain region patrol, city anti-terrorism, needs extra guarantee vehicle and equipment, greatly increased use cost, when actual work, often can't satisfy the operation requirement.
Therefore, the prior art is in need of further improvement.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model aims at providing a portable investigation unmanned aerial vehicle system that can fast assembly, convenient to carry, concrete scheme is as follows:
the utility model discloses portable electric unmanned aerial vehicle system includes: the system comprises an aircraft and a handheld control ground station; wherein the hand-held control ground station is used for mission planning, aircraft maneuvering, and mission load maneuvering; an avionic system is arranged in the aircraft and is used for controlling the aircraft and the task load of the aircraft and managing the power supply of airborne equipment; the aircraft is a detachable flight carrier and comprises a fuselage, detachable wings positioned on two sides of the fuselage and a detachable horizontal tail positioned at the tail part of the fuselage.
Further, in the above-mentioned portable electric unmanned aerial vehicle system, the avionics system includes: the system comprises a flight control computer, an avionics system battery, a GPS antenna and a connector; the flight control computer is used for controlling the aircraft according to the mission planning, the aircraft operation and the mission load operation of the handheld control ground station; the avionics system battery is used for supplying power to the flight control computer, the GPS antenna and the connector; the GPS antenna is used for positioning the aircraft; the connector is used for connecting the flight control computer with the communication link of the handheld control ground station.
Further, in the above-mentioned portable electric unmanned aerial vehicle system, the flight control computer includes: the system comprises an air pressure height sensor module, an IMU module, a GPS/Beidou satellite positioning module, a digital signal processor module, an I/O signal conditioning module and a power management module; the air pressure height sensor module, the IMU module, the GPS/Beidou satellite positioning module, the I/O signal conditioning module and the power supply management module are all in communication connection with the digital signal processor module.
Further, in the above-mentioned portable electric unmanned aerial vehicle system, the handheld control ground station includes: the system comprises a control device, two rocker potentiometers electrically connected with the control device, a plurality of physical keys, a display lamp, a display screen and a battery for a handheld ground control ground station; the control device is used for collecting the position information of the rocker potentiometer and the values of the physical keys, telemetering data and displaying, decoding and displaying network image information, configuring flight control parameters, navigating a map, and recording and storing data and images.
Further, in the above-mentioned portable electronic unmanned aerial vehicle system, the display screen is capacitive touch display screen.
Further, in the above-mentioned portable electric unmanned aerial vehicle system, the battery for handheld ground control ground station is the lithium cell.
Further, in the above-mentioned portable electronic unmanned aerial vehicle system, the fuselage is the fuselage that combined material made.
Further, in the portable electric unmanned aerial vehicle system, the body is made of Kevlar aramid fiber composite material.
Further, in the portable electric unmanned aerial vehicle system, the body is made of Kevlar aramid fiber composite material.
Further, in the above-mentioned portable electric unmanned aerial vehicle system, the aircraft is a single portable unmanned reconnaissance aircraft
Compared with the prior art, the utility model discloses an independent aircraft, avionics system and handheld control ground station constitute portable investigation unmanned aerial vehicle to, the aircraft is detachable flight carrier, that is to say, parts such as wing, horizontal tail all can be dismantled as required and put into the knapsack, and, the fuselage main part of aircraft adopts combined material to make (for example, Kevlar aramid fiber combined material), and the system gross weight is only five kilograms, and single bear can carry out the task. Moreover, the single portable investigation unmanned aerial vehicle is convenient to carry, does not need extra guarantee vehicles and equipment, and greatly reduces the use cost.
Furthermore, because the utility model discloses quick assembly can be realized to aircraft, avionics system and these discrete structures of handheld control ground station, takes off rapidly to, handheld control ground station can carry out the flight path planning according to the site conditions in real time, and more timely, accurate collects the on-the-spot information.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
fig. 1 is a schematic structural view of an embodiment of the portable electric unmanned aerial vehicle system of the present invention;
fig. 2 is a system block diagram of the flight control computer in the embodiment of the portable electric unmanned aerial vehicle system of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
Referring to fig. 1, fig. 1 is the utility model discloses portable electric unmanned aerial vehicle embodiment's schematic structure diagram.
In this embodiment, a portable electric drone system embodiment includes an aircraft 1 and a handheld control ground station 2; the hand-held control ground station 2 is used for mission planning, aircraft maneuvering and mission load maneuvering; the aircraft 1 has built in it an avionics system 3, which avionics system 3 is used for control of the aircraft 1 and its mission load and for power management of the onboard equipment.
The aircraft 1 is a detachable flight carrier and comprises a composite material fuselage 11, detachable wings 12 positioned on two sides of the fuselage, a detachable horizontal tail 13 positioned at the tail part of the fuselage 11, a motor 14, an electric speed regulator 15, a propeller 16 and a steering engine 17. The avionics system 3 includes a flight control computer 31, an avionics battery 32, a GPS antenna 33 and a connector 34. The flight control computer 31 is used for controlling the aircraft 1 according to the mission planning, the aircraft operation and the mission load operation of the handheld control ground station 3; the avionics system battery 32 is used for supplying power to the flight control computer 31, the GPS antenna 33 and the connector 34; the GPS antenna 33 is used to locate the aircraft 1; connector 34 is used to connect flight control computer 31 to the hand-held control ground station 3 communication link.
More specifically, as shown in fig. 2, the flight control computer 31 is a hardware carrier required for providing flight control, and includes: the system comprises an air pressure height sensor module 311, an IMU module 312, a GPS/Beidou satellite positioning module 313, a digital signal processor module 314, an I/O signal conditioning module 315 and a power management module 316; the barometric altitude sensor module 311, the IMU module 312, the GPS/Beidou satellite positioning module 313, the I/O signal conditioning module 314 and the power management module 316 are in signal connection with the digital signal processor module 314.
The hand-held control ground station 2 comprises a hardware circuit 21, two rocker potentiometers 22, a touch display screen 23, a system shell 24, a 12V high-density lithium battery 25, a control device 26, a plurality of physical keys 27 and a high-brightness LED display lamp 28. The control device 26 is used for collecting position information of the rocker potentiometer 22 and values of the physical keys 27, telemetering and displaying data, decoding and displaying network image information, configuring flight control parameters, navigating a map, and recording and storing data and images. In this embodiment, the touch display screen 23 is a seven-inch capacitive touch display screen, but the size of the display screen is not limited, and may be selected according to actual situations. The type of display screen is also not restricted, and the display screen outside the capacitive touch screen is also in the protection scope of the utility model. In this embodiment, the battery for the handheld ground control ground station is a lithium battery, but the utility model discloses do not limit this. Other batteries besides the lithium battery are also within the protection scope of the utility model.
Preferably, in the present embodiment, the composite fuselage 11 may be a fuselage of kevlar composite.
The utility model discloses the aircraft main part adopts Kevlar aramid fiber combined material, and it is good to have a pliability, light in weight, anti extrusion, characteristics such as anti falling. The flight control system adopts a flight control system of a small high-performance unmanned aerial vehicle based on a double ARM framework, a communication link adopts a ten-kilometer single-board digital-graph integrated communication link based on time division multiplexing, the communication link is arranged above a flight control board through an inter-board connector, the overall size is smaller than 14cm multiplied by 7cm, and the height is not more than 2 cm. The unmanned aerial vehicle adopts full-process control flight, a mission air line and a landing air line are planned through ground station software before flight, the unmanned aerial vehicle is thrown to take off by hands, the unmanned aerial vehicle automatically shifts to fixed-height flight when reaching a certain height after taking off, an air line flight task is executed, the unmanned aerial vehicle automatically lands according to a preset landing air line after the execution is finished, and the flight task is automatically completed without any human intervention in the full process. The hand-held control ground station is communicated with the ground end of the external ground digital map integrated communication link through the RS422 and a network interface, ground station software is arranged in the hand-held controller, an uploading air route can be planned, data and images returned by the flight controller through the link can be displayed, recorded and stored, the total weight of the whole system is only five kilograms, all the equipment can be placed into a backpack after being disassembled, and a person can carry the backpack to carry out a task.
Preferably, the portable spy drone is a single-person portable unmanned spy drone.
It will be apparent to those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (9)
1. A portable electric unmanned aerial vehicle system is characterized by comprising an aircraft and a handheld control ground station; wherein,
the handheld control ground station is used for mission planning, aircraft maneuvering and mission load maneuvering;
an avionic system is arranged in the aircraft and is used for controlling the aircraft and the task load of the aircraft and managing the power supply of airborne equipment;
the aircraft is a detachable flight carrier and comprises a fuselage, detachable wings positioned on two sides of the fuselage and a detachable horizontal tail positioned at the tail part of the fuselage.
2. The portable electric drone system of claim 1, wherein the avionics system comprises: the system comprises a flight control computer, an avionics system battery, a GPS antenna and a connector;
the flight control computer is used for controlling the aircraft according to the mission planning, the aircraft operation and the mission load operation of the handheld control ground station;
the avionics system battery is used for supplying power to the flight control computer, the GPS antenna and the connector;
the GPS antenna is used for positioning the aircraft;
the connector is used for connecting the flight control computer with the communication link of the handheld control ground station.
3. The portable electric drone system of claim 2, wherein the flight control computer comprises: the system comprises an air pressure height sensor module, an IMU module, a GPS/Beidou satellite positioning module, a digital signal processor module, an I/O signal conditioning module and a power management module;
the air pressure height sensor module, the IMU module, the GPS/Beidou satellite positioning module, the I/O signal conditioning module and the power supply management module are all in communication connection with the digital signal processor module.
4. The portable electric drone system of claim 3, wherein the hand-held control ground station comprises: the system comprises a control device, two rocker potentiometers electrically connected with the control device, a plurality of physical keys, a display lamp, a display screen and a battery for a handheld ground control ground station;
the control device is used for collecting the position information of the rocker potentiometer and the values of the physical keys, telemetering data and displaying, decoding and displaying network image information, configuring flight control parameters, navigating a map, and recording and storing data and images.
5. The portable electric drone system of claim 4, wherein the display screen is a capacitive touch display screen.
6. The portable electric unmanned aerial vehicle system of claim 4, wherein the battery for the handheld ground control ground station is a lithium battery.
7. The portable electric drone system of claim 1, wherein the fuselage is a composite fuselage.
8. The portable electric drone system of claim 7, wherein the fuselage is a Kevlar composite fuselage.
9. The portable electric drone system of claim 1, wherein the aerial vehicle is a single-person portable unmanned scout.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720235333.1U CN206557391U (en) | 2017-03-13 | 2017-03-13 | A kind of portable electric UAS |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720235333.1U CN206557391U (en) | 2017-03-13 | 2017-03-13 | A kind of portable electric UAS |
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| Publication Number | Publication Date |
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| CN206557391U true CN206557391U (en) | 2017-10-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720235333.1U Expired - Fee Related CN206557391U (en) | 2017-03-13 | 2017-03-13 | A kind of portable electric UAS |
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| CN (1) | CN206557391U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111077899A (en) * | 2019-10-25 | 2020-04-28 | 中国航空无线电电子研究所 | Carrier-borne unmanned aerial vehicle wrist strap type handheld control system |
| CN111176322A (en) * | 2019-12-27 | 2020-05-19 | 西安羚控电子科技有限公司 | Outdoor swarm unmanned aerial vehicle confrontation test system |
-
2017
- 2017-03-13 CN CN201720235333.1U patent/CN206557391U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111077899A (en) * | 2019-10-25 | 2020-04-28 | 中国航空无线电电子研究所 | Carrier-borne unmanned aerial vehicle wrist strap type handheld control system |
| CN111176322A (en) * | 2019-12-27 | 2020-05-19 | 西安羚控电子科技有限公司 | Outdoor swarm unmanned aerial vehicle confrontation test system |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
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Granted publication date: 20171013 Termination date: 20210313 |