CN205015666U - Unmanned aerial vehicle flight controller - Google Patents
Unmanned aerial vehicle flight controller Download PDFInfo
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- CN205015666U CN205015666U CN201520746464.7U CN201520746464U CN205015666U CN 205015666 U CN205015666 U CN 205015666U CN 201520746464 U CN201520746464 U CN 201520746464U CN 205015666 U CN205015666 U CN 205015666U
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- 238000012545 processing Methods 0.000 claims abstract description 36
- 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 34
- 238000005259 measurement Methods 0.000 abstract description 3
- 239000002184 metal Substances 0.000 abstract 2
- 230000010354 integration Effects 0.000 abstract 1
- 238000010030 laminating Methods 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 5
- 230000003028 elevating effect Effects 0.000 description 5
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008280 blood Substances 0.000 description 1
- 210000004369 blood Anatomy 0.000 description 1
- 230000000739 chaotic effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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Abstract
The utility model discloses an unmanned aerial vehicle flight controller, including the casing and locating casing inside central processing unit, GPS device, inertia measurement assembly, GPS device, inertia measurement assembly are connected with central processing unit respectively, the casing includes that laminating department of upper and lower casing is enclosed and is had the metal mesh through screw fixed connection's last casing and lower casing, the other wall of casing is opened and is had the through -hole down, and the through -hole internal fixation has input/output joint, barometer to connect and the GPS antenna terminal, input/output articulate central processing unit, and the barometer of barometer articulate integration on central processing unit, the GPS device is connected to the GPS antenna terminal. The utility model discloses reduced unmanned aerial vehicle flight controller's interface, simplified unmanned aerial vehicle flight controller's structure, had that simple structure, interface are few, a simple to operate, the convenient advantage of dismantlement, through setting up the metal mesh, the utility model discloses can avoid the interference of external electromagnetic signal to the unmanned aerial vehicle flight controller internal part effectively.
Description
Technical field
The utility model relates to unmanned vehicle technical field, specifically, is UAV Flight Control device.
Background technology
UAV Flight Control device is the center-control parts of unmanned plane, is the control center of unmanned plane, and its normal work for unmanned plane plays conclusive effect.Due to the importance of UAV Flight Control device in whole UAS, therefore, the structural design of UAV Flight Control device seems most important.
But in order to meet the needs of each function of unmanned plane, existing UAV Flight Control device complex structure, each parts arrange irregular, be embodied in that UAV Flight Control device structural outer interface is many, functional reliability is low, maintenance difficult.
Therefore, under the prerequisite that can ensure UAV Flight Control device normal function, how to simplify the structure of unmanned vehicle, rationally all parts is set, become the emphasis of those skilled in the art's research.
Utility model content
For overcoming the defects such as existing UAV Flight Control device complex structure, interface is many, the utility model provides a kind of UAV Flight Control device, under the prerequisite completing UAV Flight Control device normal function, decrease the interface that UAV Flight Control device is connected with unmanned plane miscellaneous part, simplify the structure of UAV Flight Control device.
For achieving the above object, the utility model discloses UAV Flight Control device, comprise housing and be located at central processing unit, GPS device, the inertial measuring unit of enclosure interior, GPS device, inertial measuring unit are connected with central processing unit respectively; Housing comprises the upper shell and lower house that are fixedly connected with by screw, and the joint place of upper and lower casing is with wire netting; The other wall of lower house has through hole, through hole internal fixtion has input and output joint, barometer joint and gps antenna joint, input and output joint connects central processing unit, and barometer joint connects the barometer be integrated on central processing unit, and gps antenna joint connects GPS device.
The utility model avoids external electromagnetic signal to the interference of controller internal components by wire netting, and meanwhile, the utility model decreases interface quantity, and interface layout is reasonable.
Further, the other wall of lower house has three through holes, be inserted with input and output joint, barometer joint and gps antenna joint respectively.
Be divided into by all joints three parts to arrange, be conducive to the connection of each joint, avoid wiring chaotic, reduce setting up time.
Further, input and output joint comprises the power interface, PWM interface and the serial ports that are connected with central processing unit respectively, and power interface, PWM interface and serial ports are fixed in stripe board side by side, and stripe board is stuck in through hole.
Power interface, PWM interface and serial ports are arranged side by side, distribute each interface systematically, there is the technique effect of conserve space, rational deployment.
Further, central processing unit, GPS device are fixedly connected with lower house, and inertial measuring unit is fixedly connected with upper shell, and the upside of central processing unit and GPS device is located at by inertial measuring unit.
Further, central processing unit connected storage.
Further, upper shell height is the half of lower house height.
Further, wire netting is fixed on upper and lower casing outer wall surface.
Further, wire netting is fixed on upper and lower casing inner wall surface.
The beneficial effects of the utility model are: the utility model decreases the interface of UAV Flight Control device, simplify the structure of UAV Flight Control device, have that structure is simple, interface is few, an advantage of easy for installation, convenient disassembly; By arranging wire netting, the utility model can avoid external electromagnetic signal to the interference of UAV Flight Control device internal part effectively.
Accompanying drawing explanation
Fig. 1 is the explosive view of UAV Flight Control device.
In figure,
1, upper shell; 2, input and output joint; 3, barometer joint; 4, lower house; 5, GPS device; 6, inertial measuring unit; 7, central processing unit; 8, gps antenna joint.
Embodiment
Below in conjunction with accompanying drawing, explanation is explained in detail to structure of the present utility model.
Embodiment one:
UAV Flight Control device as shown in Figure 1, comprise housing and be located at central processing unit 7, GPS device 5, the inertial measuring unit 6 of enclosure interior, GPS device 5, inertial measuring unit 6 are connected with central processing unit 7 respectively, housing can be metal material, comprise upper shell 1 and lower house 4, upper shell 1, lower house 4 are fixedly connected with by screw, as shown in Figure 1, screw through penetrating in lower house 4 after upper shell 1, realize upper shell 1, lower house 4 fixing, central processing unit 7, GPS device 5 are fixedly connected with lower house 4, inertial measuring unit 6 is fixedly connected with upper shell 1, and the upside of central processing unit 7 and GPS device 5 is located at by inertial measuring unit 6, the joint place of upper shell 1, lower house 4 is with wire netting, and to avoid the interference of extraneous electromagnetic signal, in the present embodiment, wire netting is arranged on potted line place, junction, is fixed on upper shell 1, lower house 4 outer wall surface, the other wall of lower house 4 has through hole, through hole internal fixtion has input and output joint 2, barometer joint 3 and gps antenna joint 8, input and output joint 2 connects central processing unit 7, barometer joint 3 connects the barometer be integrated on central processing unit 7, barometer gathers external air flow by barometer joint 3, gps antenna joint 8 connects GPS device 5, GPS device 5 is connected with external antenna by gps antenna joint 8, the other wall of lower house 4 has three through holes, be inserted with input and output joint 2 respectively, barometer joint 3 and gps antenna joint 8, input and output joint 2 in the present embodiment, barometer joint 3 is arranged on lower house 4 with on the wall of one side, gps antenna joint 8 is arranged on another other wall of lower house 4, central processing unit 7 connected storage, the present embodiment is Flash memory chip.In the utility model, input and output joint 2 comprises the power interface, PWM interface and the serial ports that are connected with central processing unit 7 respectively, power interface connects external power supply, for the central processing unit 7 of UAV Flight Control device and whole UAV Flight Control device are powered, central processing unit 7 exports control signal by PWM interface and does various action to control unmanned plane body, serial ports is for connecting the external radio station communicated with ground based terminal, power interface, PWM interface and serial ports are fixed in stripe board side by side, and stripe board is stuck in through hole.
In the present embodiment, taking up space to reduce UAV Flight Control device, upper shell 1 height is the half of lower house 4 height, and can ensure like this to place all necessary parts, necessary parts comprises each circuit board, again can conserve space.
By the control of the utility model UAV Flight Control device, can realize controlling the actions such as unmanned plane realizes rolling, climb, dive, accelerate, turning.The present embodiment is described for the elevating rudder of flight control assemblies control unmanned plane and throttle.
The effect of elevating rudder is the pitch control subsystem of carrying out aircraft, comprises that pull bar comes back, push rod bows, and during pull bar, aircraft comes back and climbs, and kinetic energy can make speed reduce towards the conversion of potential energy, therefore will monitor flying speed, avoids causing stall because of undue pull bar; The effect of throttle rudder is the rotating speed controlling aircraft engine, and open the throttle and aircraft can be made to increase power, unmanned vehicle accelerates or climbs, otherwise then unmanned vehicle slows down or reduces flying height.
Flight control assemblies controls elevating rudder and throttle by PWM interface output signal, before unmanned plane takes off, can set what a target flight speed v and flying height h as required, and after unmanned plane takes off, barometer detects unmanned plane during flying speed and height in real time.The aircraft of the present embodiment is in flight course, need to keep certain height and speed, if barometer detects that the height h1 of aircraft flight is lower than object height h, then CPU (central processing unit) sends signal by PWM interface and controls throttle increase, make aircraft improve flying speed, simultaneously CPU (central processing unit) sends pwm signal and controls elevating rudder and make aircraft increase; When the flying height h2 of the aircraft detected higher than object height h time, then CPU (central processing unit) sends pwm signal and controls throttle reduction, cause speed to reduce, control elevating rudder push rod simultaneously and make height reduction, so to ensure that the flying height of aircraft is consistent with the desired value of setting with speed.
Flight control assemblies in this programme, wherein Inertial Measurement Unit and GPS unit form strapdown inertial navitation system (SINS), just can extrapolate the flight parameter such as roll angle, the angle of pitch, coordinate figure of unmanned plane through respective algorithms, the radio station also by being connected with serial ports in the Flash chip that flight parameter value can be stored in CPU (central processing unit) sends.In the present embodiment, CPU (central processing unit) also can control all airframe components of the unmanned plane such as aileron, wing flap by the control signal that PWM interface sends, and does roll action as controlled unmanned plane by control aileron.
Embodiment two:
The structure of embodiment two is substantially identical with the structure of embodiment one; its difference is: wire netting is fixed on upper shell 1, lower house 4 inner wall surface; before making to be screwed upper shell 1, lower house 4; wire netting is fixed on case inside; this mode is conducive to protecting wire netting, avoids wire netting to be subject to External Force Acting and causes wire netting to damage, reduce or lose the effect of shielding external electromagnetic signal.
The foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all do in the utility model flesh and blood any amendment, equivalent to replace and simple modifications etc., all should be included within protection domain of the present utility model.
Claims (8)
1. UAV Flight Control device, comprise housing and be located at central processing unit (7), GPS device (5), the inertial measuring unit (6) of enclosure interior, GPS device, inertial measuring unit are connected with central processing unit respectively; It is characterized in that: housing comprises the upper shell (1) and lower house (4) that are fixedly connected with by screw, and the joint place of upper and lower casing is with wire netting; The other wall of lower house has through hole, through hole internal fixtion has input and output joint (2), barometer joint (3) and gps antenna joint (8), input and output joint connects central processing unit, barometer joint connects the barometer be integrated on central processing unit, and gps antenna joint connects GPS device.
2. UAV Flight Control device according to claim 1, is characterized in that: the other wall of lower house has three through holes, is inserted with input and output joint, barometer joint and gps antenna joint respectively.
3. UAV Flight Control device according to claim 1 and 2, it is characterized in that: input and output joint comprises the power interface, PWM interface and the serial ports that are connected with central processing unit respectively, power interface, PWM interface and serial ports are fixed in stripe board side by side, and stripe board is stuck in through hole.
4. UAV Flight Control device according to claim 1 and 2, it is characterized in that: central processing unit, GPS device are fixedly connected with lower house, inertial measuring unit is fixedly connected with upper shell, and the upside of central processing unit and GPS device is located at by inertial measuring unit.
5. UAV Flight Control device according to claim 4, is characterized in that: central processing unit connected storage.
6. UAV Flight Control device according to claim 4, is characterized in that: upper shell height is the half of lower house height.
7. UAV Flight Control device according to claim 1, is characterized in that: wire netting is fixed on upper and lower casing outer wall surface.
8. UAV Flight Control device according to claim 1, is characterized in that: wire netting is fixed on upper and lower casing inner wall surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520746464.7U CN205015666U (en) | 2015-09-24 | 2015-09-24 | Unmanned aerial vehicle flight controller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520746464.7U CN205015666U (en) | 2015-09-24 | 2015-09-24 | Unmanned aerial vehicle flight controller |
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| Publication Number | Publication Date |
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| CN205015666U true CN205015666U (en) | 2016-02-03 |
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| CN201520746464.7U Active CN205015666U (en) | 2015-09-24 | 2015-09-24 | Unmanned aerial vehicle flight controller |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106371124A (en) * | 2016-10-11 | 2017-02-01 | 金陵科技学院 | Micro unmanned aerial vehicle positioning system based on cooperative mode |
| WO2018209770A1 (en) * | 2017-05-19 | 2018-11-22 | 深圳市大疆创新科技有限公司 | Barometer assembly and drone |
| CN110440979A (en) * | 2019-07-22 | 2019-11-12 | 北京中航智科技有限公司 | A kind of air pressure acquisition devices fly control box and unmanned plane |
-
2015
- 2015-09-24 CN CN201520746464.7U patent/CN205015666U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106371124A (en) * | 2016-10-11 | 2017-02-01 | 金陵科技学院 | Micro unmanned aerial vehicle positioning system based on cooperative mode |
| WO2018209770A1 (en) * | 2017-05-19 | 2018-11-22 | 深圳市大疆创新科技有限公司 | Barometer assembly and drone |
| CN109843717A (en) * | 2017-05-19 | 2019-06-04 | 深圳市大疆创新科技有限公司 | Barometer component and unmanned plane |
| CN109843717B (en) * | 2017-05-19 | 2021-11-26 | 深圳市大疆创新科技有限公司 | Barometer subassembly and unmanned aerial vehicle |
| CN110440979A (en) * | 2019-07-22 | 2019-11-12 | 北京中航智科技有限公司 | A kind of air pressure acquisition devices fly control box and unmanned plane |
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| C14 | Grant of patent or utility model | ||
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| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Flight control unit for parafoil type unmanned plane Effective date of registration: 20170327 Granted publication date: 20160203 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.)|Beijing Civil Aviation Heyuan Investment Center (L.P.) Pledgor: ZEROTECH (BEIJING) INTELLIGENCE TECHNOLOGY Co.,Ltd. Registration number: 2017990000242 |
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Effective date of registration: 20190906 Granted publication date: 20160203 |
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Date of cancellation: 20220406 Granted publication date: 20160203 |
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Effective date of registration: 20220406 Granted publication date: 20160203 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20221008 Granted publication date: 20160203 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.)|Beijing Civil Aviation Heyuan Investment Center (L.P.) Pledgor: ZEROTECH (BEIJING) INTELLIGENCE TECHNOLOGY Co.,Ltd. Registration number: 2017990000242 |
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Date of cancellation: 20220918 Granted publication date: 20160203 |
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Effective date of registration: 20220918 Granted publication date: 20160203 |