CN206096945U - Flight measurement control module reaches unmanned vehicles who contains it - Google Patents
Flight measurement control module reaches unmanned vehicles who contains it Download PDFInfo
- Publication number
- CN206096945U CN206096945U CN201620558472.3U CN201620558472U CN206096945U CN 206096945 U CN206096945 U CN 206096945U CN 201620558472 U CN201620558472 U CN 201620558472U CN 206096945 U CN206096945 U CN 206096945U
- Authority
- CN
- China
- Prior art keywords
- control module
- measurement control
- flight measurement
- circuit board
- module according
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Abstract
The utility model relates to an unmanned vehicles technical field, concretely relates to flight measurement control module reaches unmanned vehicles who contains it, including main control board, damping assembly, balancing weight and the circuit board that connects gradually, the circuit board with the main control board is connected, be provided with the connector on the main control board, be provided with the fluting on the circuit board, work as the fluting is two when above, and is a plurality of the fluting is the axial symmetry and distributes. The utility model provides a flight measurement control module reaches unmanned vehicles who contains it, the measurement control module structural design that wherein flies is equitable, and whole highly integrated is convenient for and the integration of other equipment systems. The flight measurement control module who uses with the conventionality compares, the utility model discloses an install simply easy realization of small, light in weight, compatible good, overall structure, reduced unmanned vehicles's cost, improved detection and control's accuracy.
Description
Technical field
This utility model is related to unmanned vehicle technical field, and in particular to a kind of flight measurement control module and containing which
Unmanned vehicle.
Background technology
Unmanned plane is a kind of unmanned vehicle manipulated by radio robot or itself presetting apparatus.Mesh
Before, with the development of science and technology, unmanned air vehicle technique reaches its maturity, unmanned plane is so that its speed is fast, flexible operation the characteristics of extensively should
With.In civil area, ground mapping unmanned plane, geological exploration unmanned plane, disaster monitoring unmanned plane, meteorological detection unmanned plane, sky
Middle traffic control unmanned plane, border control unmanned plane, communication relay unmanned plane, pesticide spraying unmanned plane, rescue unmanned plane grind
Study carefully and apply at home and abroad all in constantly developing.
Used as the control axis of unmanned vehicle, flight measurement control module is mainly used in the control and navigation of aircraft.
By the data that inertia measuring module is measured are calculated and analyzed, flight measurement control module can control the appearance of aircraft
State, feeds back the position that aircraft is located.For flight measurement control module, stability is extremely important.
With the development of technology, the application of small-sized unmanned aircraft is more and more extensive.For small-sized unmanned aircraft,
Flight measurement control module will not only accomplish good stability, also lightweight, small volume.Existing flight measurement controls mould at present
Block common configuration is complicated, and external interface is more, and volume is big, difficult with other systems integration of equipments.Accordingly, it would be desirable to one kind can be steady
Fixed, it is adapted to the flight measurement control module used on small-sized unmanned aircraft.
Utility model content
This utility model is in order to solve above-mentioned technical problem, there is provided a kind of flight measurement control mould for unmanned vehicle
Block, effectively reduces the output noise of Mierotubule-associated proteins, and eliminates impact of the mixed and disorderly air-flow to baroceptor, and permanent use should
Device, still is able in optimum Working.
In order to reach above-mentioned technique effect, this utility model includes technical scheme below：
A kind of flight measurement control module, including the master control borad, damping assembly, balancing weight and the circuit board that are sequentially connected, institute
State circuit board to be connected with the master control borad, adapter is provided with the master control borad, fluting on the circuit board, is provided with, works as institute
State fluting for two or more when, it is multiple it is described fluting axisymmetricly arrange.
Further, the fluting is slotted for right angle.
This utility model flight measurement control module reasonable in design, compared to existing technology in the module, this practicality
It is new to have the advantages that simple structure, interface be single and small volume, it is integrated more convenient compared with other flight measurement control modules,
During use, stability is higher, is adapted to use on small-sized unmanned aircraft.Otherwise for the setting of right angle fluting, which can be effective
The resonance of unmanned vehicle is reduced, the accuracy of measurement data is improved, so that master control borad is done to unmanned vehicle further more
Work is indicated accurately.
Further, described master control borad and circuit board are connected by soft arranging wire.By soft arranging wire by master control borad and circuit
Plate connection compatibility is more preferably.
Further, the adapter is bus bar connector.This utility model master control borad pair is used as by bus bar connector
Outer connecting interface, the interface required in its quantity are less, reduce the volume of this utility model flight measurement control module.
Further, monitoring device is connected with described master control borad and/or circuit board.Nothing is detected by monitoring device
Whether each parameter attribute of people's aircraft is normal, such as abnormal further to be carried out accordingly automatically by master control borad transmission cue
Adjust or adjust manually.
Further, the monitoring device includes that inertial sensor, baroceptor, GPS navigator, engine temperature are passed
At least one of sensor, current sensor, main thruster rotating speed, torque sensor and fuel liquid level sensor.By above-mentioned biography
Sensor can realize the overall monitor to unmanned vehicle, with most when unmanned vehicle works abnormal or abnormal certain part
Adjust soon and repair.The conventional use of biography in flight measurement control module such as the inertial sensor, pressure transducer
The signal of sensor is sent in other equipment system by soft arranging wire.Constitute the various sensory packages of many sets to integrate, can realize
The multiple Data Fusion of Sensor of data of the same race, can realize various multiple sensor cluster Data Integrations again, it is possible to increase measurement number
According to reliability, effectiveness, stability and accuracy.
Further, the inertial sensor includes gyroscope and accelerometer.
Further, described damping assembly includes the first vibration-damped component and the second vibration-damped component, first vibration-damped component and
Two vibration-damped components are located at same level, and are connected to relative two edge of circuit board.The damping assembly structure sets
Put, effectively reduce the resonant frequency of this utility model flight measurement control module, realize the effect of vibration damping.
Further, groove is provided with the damping assembly and circuit board, the adapter sequentially passes through described recessed
Groove.
Preferably, the groove is separately positioned on relative two edge part of damping assembly and circuit board, by edge
The setting of portion's groove, when being assembled, the volume of the flight measurement control module of reduction improves flight measurement control module
Integrated level, be easy to used in other devices are connected to.
Further, be provided with installing hole on the diagonal of the circuit board, the balancing weight by installing hole with it is described
Circuit board is fixedly connected.Make balancing weight be connected with circuit board more to consolidate.
A kind of unmanned vehicle, including above-mentioned flight measurement control module.
Using above-mentioned technical proposal, including following beneficial effect：This utility model provides a kind of flight measurement control module
And the unmanned vehicle containing which, wherein flight measurement control module reasonable in design, whole height be integrated, is easy to and other
Device systems it is integrated.Compared with conventional use of flight measurement control module, device volume of the present utility model is little, weight
Gently, compatibility it is good, overall structure is simply easily realized, reduces the cost of unmanned vehicle, improve detection and control it is accurate
Property.
Description of the drawings
Fig. 1 is this utility model embodiment flight measurement control module detonation configuration figure；
Fig. 2 is flight measurement control module front view shown in this utility model Fig. 1；
Fig. 3 is this utility model circuit board upward view.
In figure,
1st, master control borad；11st, adapter；2nd, damping assembly；3rd, balancing weight；4th, circuit board；41st, inertial sensor；42nd, air pressure
Sensor；43rd, right angle fluting；44th, installing hole.
Specific embodiment
Below by specific embodiment and combine accompanying drawing this utility model is described in further detail.
Embodiment：
The present embodiment provides a kind of flight measurement control module, as shown in Figure 1, Figure 2 and Figure 3, including the master being sequentially connected
Control plate 1, damping assembly 2, balancing weight 3 and circuit board 4, the circuit board are connected with the master control borad, are arranged on the master control borad
There is adapter 11, on the circuit board, be provided with fluting 43, when the fluting is two or more, multiple flutings are in axle pair
Claim to arrange.
In the present embodiment, as shown in figure 3, described fluting is slotted for right angle.
The quantity of the right angle fluting can be 1,2,3,4,5 or 6 etc., and preferably, can be according to this reality
With new flight measurement control module or the weight of unmanned vehicle, carry out effectively secondary experiment screening and obtain optimal quantity
Value.It is highly preferred that the quantity of the right angle fluting is two, and two right angle fluting right angle portions are axisymmetricly arranged relatively.
If the circuit board is square or rectangle, leg fluting is separately positioned on two relative angles of surface-mounted integrated circuit.
The adapter is to realize all attainable adapter that master control borad is connected with external equipment.The circuit
Plate and the connected mode of the master control borad are to realize all electric connection modes that circuit board is connected with master control borad.
In the present embodiment, further, as shown in Fig. 2 described master control borad and circuit board are connected by soft arranging wire.
To press embodiment in order at this, compatibility can be effectively improved by soft arranging wire connection.
In the present embodiment, further, the adapter is bus bar connector.It is above-mentioned for preferred embodiment, wherein
Device that master control borad is connected with external device is that by the protection domain of above-mentioned embodiment for adapter is all.
In the present embodiment, further, monitoring device is connected with described master control borad and/or circuit board.Supervise at this
It is for can be used in detecting unmanned vehicle each side operational factor in unmanned vehicle, to guarantee unmanned vehicle to survey device
The device of normal work.
In the present embodiment, further, the monitoring device includes that inertial sensor 41, baroceptor 42, GPS are led
Boat instrument, engine temperature sensing unit, current sensor, in main thruster rotating speed, torque sensor and fuel liquid level sensor extremely
Few one kind.Above-mentioned monitoring device needs to measure the relevant apparatus of monitoring in being unmanned vehicle, and obtains corresponding prison
Parameter is surveyed, wherein also including conventional use of other monitoring devices of institute in unmanned vehicle.Those skilled in the art are according to routine
Technological means, are screened based on demand and are matched, and the monitoring of respective combination can be directly obtained according to routine techniquess means
Device.
Preferably, as shown in figure 3, the monitoring device includes inertial sensor and baroceptor, and the monitoring dress
Put on connection side relative with the side of balancing weight connection on circuit boards.
In the present embodiment, further, the inertial sensor includes gyroscope and accelerometer.
In the present embodiment, further, described damping assembly includes the first vibration-damped component and the second vibration-damped component, described
One vibration-damped component and the second vibration-damped component are located at same level, and are connected to relative two edge of circuit board.
The damping assembly is not limited to above-mentioned technical proposal, above are only preferred embodiment.For this practicality
The damping assembly of new flight measurement control module, can include multiple vibration-damped components, can be based on the volume of unmanned vehicle and weight
Amount, is accordingly selected based on this area routine techniquess.
In the present embodiment, further, be provided with groove on the damping assembly and circuit board, the adapter according to
It is secondary through the groove.Adapter is sequentially passed through groove and is connected with other equipment again, makes this utility model flight measurement control mould
The integrated level of block is higher, for preferred embodiment at this.
In the present embodiment, further, installing hole 44 is provided with the diagonal of the circuit board, the balancing weight leads to
Cross installing hole to be fixedly connected with the circuit board.Simultaneously every mode such as screw that circuit board and balancing weight can be connected
Connection, bonding etc., also in protection domain of the present utility model.
The present embodiment also provides a kind of unmanned vehicle, including above-mentioned flight measurement control module, while also including this
For conventional use of device and part in unmanned vehicle in art.Those skilled in the art are based on above-mentioned technical proposal
The shape and structure of this utility model unmanned vehicle can be directly obtained with routine techniquess means.
Preferred embodiment of the present utility model is the foregoing is only, this utility model is not limited to, for this
For the technical staff in field, this utility model can have various modifications and variations.It is all it is of the present utility model spirit and principle
Within, any modification, equivalent substitution and improvements made etc. are should be included within protection domain of the present utility model.
Claims (10)
1. a kind of flight measurement control module, it is characterised in that including the master control borad (1), damping assembly (2) being sequentially connected, match somebody with somebody
Pouring weight (3) and circuit board (4), the circuit board are connected with the master control borad, and adapter (11), institute are provided with the master control borad
State, when the quantity of the fluting is two or more, multiple flutings axisymmetricly set
Put.
2. flight measurement control module according to claim 1, it is characterised in that the fluting is right angle fluting, described
Master control borad and circuit board by soft arranging wire connect.
3. flight measurement control module according to claim 1, it is characterised in that the adapter is bus bar connector.
4. flight measurement control module according to claim 1, it is characterised in that described master control borad and/or circuit board
On be connected with monitoring device.
5. flight measurement control module according to claim 4, it is characterised in that the monitoring device includes inertia sensing
Device (41), baroceptor (42), GPS navigator, engine temperature sensing unit, current sensor, main thruster rotating speed, torque
At least one of sensor and fuel liquid level sensor.
6. flight measurement control module according to claim 5, it is characterised in that the inertial sensor includes gyroscope
And accelerometer.
7. flight measurement control module according to claim 1, it is characterised in that described damping assembly includes that first subtracts
Shake part and the second vibration-damped component, and first vibration-damped component and the second vibration-damped component are located at same level, and are connected to circuit board
Relative two edge.
8. flight measurement control module according to claim 1, it is characterised in that on the damping assembly and circuit board
Arrange fluted, the adapter sequentially passes through the groove.
9. flight measurement control module according to claim 1, it is characterised in that arrange on the diagonal of the circuit board
There is installing hole (44), the balancing weight is fixedly connected with the circuit board by installing hole.
10. a kind of unmanned vehicle, it is characterised in that including the flight measurement control mould described in any one of claim 1～9
Block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620558472.3U CN206096945U (en) | 2016-06-08 | 2016-06-08 | Flight measurement control module reaches unmanned vehicles who contains it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620558472.3U CN206096945U (en) | 2016-06-08 | 2016-06-08 | Flight measurement control module reaches unmanned vehicles who contains it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206096945U true CN206096945U (en) | 2017-04-12 |
Family
ID=58471902
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620558472.3U Active CN206096945U (en) | 2016-06-08 | 2016-06-08 | Flight measurement control module reaches unmanned vehicles who contains it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206096945U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108957513A (en) * | 2018-05-17 | 2018-12-07 | 北京航空航天大学 | A kind of microminiature position attitude measurement system |
| WO2019047236A1 (en) * | 2017-09-11 | 2019-03-14 | 深圳市大疆创新科技有限公司 | Pan-tilt camera and unmanned aerial vehicle having said pan-tilt camera |
| CN110876267A (en) * | 2018-12-03 | 2020-03-10 | 深圳市大疆创新科技有限公司 | Control assembly and aircraft |
-
2016
- 2016-06-08 CN CN201620558472.3U patent/CN206096945U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019047236A1 (en) * | 2017-09-11 | 2019-03-14 | 深圳市大疆创新科技有限公司 | Pan-tilt camera and unmanned aerial vehicle having said pan-tilt camera |
| CN108957513A (en) * | 2018-05-17 | 2018-12-07 | 北京航空航天大学 | A kind of microminiature position attitude measurement system |
| CN110876267A (en) * | 2018-12-03 | 2020-03-10 | 深圳市大疆创新科技有限公司 | Control assembly and aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102879793B (en) | Super-miniature GPS (global positioning system), INS (inertial navigation system), magnetometer and barometer integrated navigation system | |
| CN206096945U (en) | Flight measurement control module reaches unmanned vehicles who contains it | |
| CN102707725B (en) | Fixed-wing automatic navigation flight control system and using method thereof | |
| CN102628249B (en) | Full-automatic inertial sensing pavement evenness detection system and detection method | |
| CN106767805A (en) | High accuracy inertia measuring method and measuring system based on MEMS sensor array | |
| CN206514864U (en) | A kind of unmanned plane inertial measuring unit and the unmanned plane containing it | |
| CN105629995B (en) | One kind is tethered at system for tracking and method | |
| CN103606206B (en) | A kind of motoring condition cognitive method using motoring condition sensing device | |
| CN202771262U (en) | Fixed-wing automatic navigation flight control system | |
| CN105915899B (en) | A kind of unmanned aerial vehicle onboard multiaxis head debugging apparatus | |
| CN1669874A (en) | Automatic pilot for aircraft | |
| CN110007354A (en) | Half aviation transient electromagnetic receiving coil flight parameter measurement device and method of unmanned plane | |
| CN106789499A (en) | A kind of integrated avionic system for light-small aircraft | |
| CN204128560U (en) | A kind of quadrotor inertial measurement system | |
| CN2681997Y (en) | Aircraft automatic pilot with double processors | |
| CN207008070U (en) | A kind of attitude transducer of new structure | |
| CN114993263A (en) | High accuracy building unmanned aerial vehicle survey and drawing system based on leveling point location | |
| CN203012513U (en) | Wireless model airplane control system | |
| CN207850389U (en) | It is tethered at the flight control system and its attitude angle device of ship | |
| CN205983225U (en) | Four rotor unmanned vehicles | |
| CN209290673U (en) | A kind of unmanned plane device that stability is strong | |
| CN210666065U (en) | Calibration device of seismic intensity instrument | |
| CN102419168B (en) | Device for measuring and displaying horizontal angle of inclination of airplane and measurement and display method thereof | |
| CN107702692A (en) | A kind of unmanned unit mapping method based on AGV matrixes | |
| CN206038016U (en) | Inertia measurement assembly reaches unmanned vehicles who contains it |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |