CN207148641U - A kind of test system for UAV Flight Control device - Google Patents
A kind of test system for UAV Flight Control device Download PDFInfo
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- CN207148641U CN207148641U CN201720870213.9U CN201720870213U CN207148641U CN 207148641 U CN207148641 U CN 207148641U CN 201720870213 U CN201720870213 U CN 201720870213U CN 207148641 U CN207148641 U CN 207148641U
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- driving motor
- direct driving
- fixed plate
- test system
- control device
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Abstract
The utility model discloses a kind of test system for UAV Flight Control device, including the first direct driving motor, the first fixed plate, the second direct driving motor, the second fixed plate, the 3rd direct driving motor, equipment mounting frame, control unit；First direct driving motor horizontal connection is in first fixed plate one end and drives the first fixed plate to be rotated in horizontal plane；Second direct driving motor is vertically connected to the first fixed plate other end, and in the axial direction of the second direct driving motor, the second direct driving motor is connected and drives the second fixed plate to be rotated in vertical plane the second fixed plate with the second fixed plate；3rd direct driving motor is vertically connected to the free end of the second fixed plate one, equipment mounting frame is located in the axial direction of the 3rd direct driving motor, 3rd direct driving motor is connected with equipment mounting frame and driving equipment mounting bracket rotates in vertical plane, each surfaces of revolution is vertical two-by-two, and each direct driving motor electrically connects with control unit.The utility model solves the problems, such as that existing test system rotation angle accuracy is inadequate, easily produces error.
Description
Technical field
It the utility model is related to test equipment technical field, more particularly to a kind of test for UAV Flight Control device
System.
Background technology
UAV Flight Control device is to refer to stablize unmanned plane during flying posture, and unmanned plane can be controlled autonomous or semi-autonomous
The control system of flight, it is the brain of unmanned plane, mainly by gyroscope (flight attitude perception), accelerometer, earth inductor,
Baroceptor (the rough control of hovering height), ultrasonic sensor (low latitude high precision controls or avoidance), light stream sensor
(hovering horizontal level accurately determines), GPS module (horizontal level height coarse localization) and control circuit composition.
At present, the sensor in UAV Flight Control device is that the high-performance integrated based on MEMS technology measures mould mostly
Block.MEMS is microelectromechanical systems (Microelectro Mechanical Systems) abbreviation, and it is to utilize microelectronics
Process technology manufactures micron-sized mechanical part, along with parts groups such as signal processor, control circuit, communication interface and power supplys
Into integrated, the microdevice system that is integrated in discrete component, its is far more precise and fragile.Although MEMS sensor
Producer can do response test and detection to the sensor chip to dispatch from the factory, but can be through when being applied to UAV Flight Control device
The processes such as transport, paster, backflow are gone through, it is careless slightly to will result in damage, it is therefore desirable to which that special test system flies to unmanned plane
The main performance (angle, acceleration magnitude) of line control unit is tested and analyzed.
Existing UAV Flight Control device test system is made up of stepper motor and reductor substantially, although it being capable of mould
Intend multi-motion state, but because its is complicated, therefore many errors are still suffered from practical application, for example backlass misses
Difference and backhaul gap error, cause anglec of rotation during test system work not accurate enough, and then influence follow-up producer to nothing
The debugging of man-machine flight controller.Therefore, develop it is a kind of can simulate multi-motion state, there is high-precision rotary angle
, the UAV Flight Control device test system for being not likely to produce error just seem very necessary.
Utility model content
The utility model is makes up the deficiencies in the prior art, there is provided a kind of for UAV Flight Control device
Test system, it can not only simulate multi-motion state, and perfect can solve traditional UAV Flight Control device test
System rotation angle accuracy not enough, easily produces the problem of error.
For the utility model to reach its purpose, the technical scheme of use is as follows：
A kind of test system for UAV Flight Control device, it is characterised in that：
Also include the first direct driving motor, the first fixed plate, the second direct driving motor, the second fixed plate, the 3rd direct driving motor,
Equipment mounting frame and control unit；
First direct driving motor is connected to one end of first fixed plate with horizontal, and first direct driving motor drives
First fixed plate is moved to rotate in horizontal plane；
Second direct driving motor is vertically connected to the other end of first fixed plate, and second fixed plate is located at
It is connected in the axial direction of second direct driving motor and with second direct driving motor, the second direct driving motor driving described second
Fixed plate rotates in vertical plane；
3rd direct driving motor is vertically connected to a free end of second fixed plate, the equipment mounting frame position
It is connected in the axial direction of the 3rd direct driving motor and with the 3rd direct driving motor, is set described in the 3rd direct driving motor driving
Standby mounting bracket rotates in vertical plane；
First fixed plate, second fixed plate, the respective surfaces of revolution of the equipment mounting frame are vertical two-by-two；
First direct driving motor, second direct driving motor, the 3rd direct driving motor are electric with described control unit
Connection.
Further, in addition to pedestal；First direct driving motor is on the pedestal.
Further, first direct driving motor, the second direct driving motor, the 3rd direct driving motor are coated with shielding shell,
To shield the interference of electromagnetic field caused by itself.
Further, the shielding shell is made of aluminum alloy materials, can be saved while effectively shielding electromagnetic interference
Cost.
Further, the equipment mounting frame is provided with multiple equipment bayonet socket, for fixing multiple UAV Flight Controls
Device.
Further, first fixed plate is L-shaped.
Further, second fixed plate takes the shape of the letter U；Second direct driving motor in the middle part of second fixed plate with connecting
Connect.
Further, the equipment mounting frame takes the shape of the letter U, and it is located in the bayonet socket of second fixed plate；Described 3rd is straight
Drive motor to be connected with a free end of the equipment mounting frame, another free end of the equipment mounting frame is fixed with described second
The free end of plate is flexibly connected.
Further, first fixed plate, second fixed plate are made of stainless steel.
Further, described control unit is supervisory controller, for controlling first direct driving motor, described second
Direct driving motor, the 3rd direct driving motor rotate to special angle and collect comparison data, with examine be devices under whether
In error range.
Relative to prior art, the utility model has following advantageous effects：
(1) a kind of test system for UAV Flight Control device provided by the utility model, not only realizes nobody
The simulation of machine multi-motion state, and the complicated mechanical structure of existing UAV Flight Control device test system has been abandoned, directly
Connect and be connected using direct driving motor with fixed plate, structure is extremely simple, so as to solve existing UAV Flight Control device test system
The problem of rotation angle accuracy of uniting not enough, easily produces error, in addition, it can be worked without interruption for a long time, effectively improves
Operating efficiency.
(2) a kind of test system for UAV Flight Control device provided by the utility model, coat on direct driving motor
There is shielding shell, influence of the electromagnetic field of direct driving motor itself to being devices under can be efficiently reduced, by largely repeatedly
Test determines that compared with traditional UAV Flight Control device test system, electromagnetic interference, which reduces, to be connect nearly a hundred times for it.
Brief description of the drawings
Specific embodiment of the present utility model is described in further detail below in conjunction with the accompanying drawings, wherein：
Fig. 1 is the axonometric drawing of the test system provided by the utility model for UAV Flight Control device；
Fig. 2 is the left view of the test system provided by the utility model for UAV Flight Control device；
Fig. 3 is the workflow block diagram of the test system provided by the utility model for UAV Flight Control device.
Description of symbols：
1st, pedestal；2nd, the first direct driving motor；3rd, the first fixed plate；4th, the second direct driving motor；5th, the second fixed plate；6th, the 3rd
Direct driving motor；7th, equipment mounting frame；8th, equipment bayonet socket；9th, shell is shielded；10 control units；11st, it is devices under.
Embodiment
Preferred embodiment of the present utility model is illustrated below in conjunction with accompanying drawing, it will be appreciated that described herein excellent
Select embodiment to be merely to illustrate and explain the utility model, be not used to limit the utility model.
The utility model discloses a kind of test system for UAV Flight Control device, as shown in Figures 1 to 3, including
There are the first direct driving motor 2, the first fixed plate 3, the second direct driving motor 4, the second fixed plate 5, the 3rd direct driving motor 6, equipment installation
Frame 7 and control unit 10.
Wherein, the first direct driving motor 2 is connected to one end of the first fixed plate 3 with horizontal, the first direct driving motor 2 driving the
One fixed plate 3 rotates in horizontal plane；
Second direct driving motor 4 is vertically connected to the other end of the first fixed plate 3, and the second fixed plate 5 is positioned at the second straight drive
It is connected in the axial direction of motor 4 and with the second direct driving motor 4, the second direct driving motor 4 drives the second fixed plate 5 to be rotated in vertical plane；
3rd direct driving motor 6 is vertically connected to a free end of the second fixed plate 5, and equipment mounting frame 7 is straight positioned at the 3rd
Drive in the axial direction of motor 6 and be connected with the 3rd direct driving motor 6, the driving equipment mounting bracket 7 of the 3rd direct driving motor 6 revolves in vertical plane
Turn；
First fixed plate 3, the second fixed plate 5, the respective surfaces of revolution of equipment mounting frame 7 are vertical two-by-two；
First direct driving motor 2, the second direct driving motor 4, the 3rd direct driving motor 6 electrically connect with control unit 10.
Test system described in the utility model, on the one hand, used direct driving motor, there is higher running accuracy；Separately
On the one hand, its each surfaces of revolution is vertical two-by-two, can simulate any angle.Therefore, it is described in the utility model to be used for unmanned plane during flying
The test system of controller can not only realize the simulation of unmanned plane multi-motion state, and solve existing unmanned plane and fly
Line control unit test system rotation angle accuracy not enough, easily produces the problem of error.
As a kind of embodiment, as shown in Fig. 1~2, the test system also includes pedestal 1, and the first direct driving motor 2 is located at base
On seat.
In the above-described embodiments, as shown in Fig. 1~2, the first direct driving motor 2, the second direct driving motor 4, the 3rd direct driving motor 6
Shielding shell 9 is coated with, to shield itself caused interference of electromagnetic field, prevents the electricity damaged in UAV Flight Control device
Sub- compass etc..
Specifically, shielding shell 9 be made of aluminum alloy materials, effectively shield electromagnetic interference while can be with cost-effective.
Certainly, in the utility model, the material for preparing of shielding shell 9 is not limited to this, for example it can also use magnesium alloy materials
It is made, such as similar change belongs to equivalent protection scope of the present utility model.
In the above-described embodiments, as shown in Fig. 1~2, equipment mounting frame 7 is provided with multiple equipment bayonet socket 8, more for fixation
Individual UAV Flight Control device, be advantageous to improve testing efficiency.
In the above-described embodiments, more specifically, as shown in Fig. 1~2, the first fixed plate 3 is L-shaped；Second fixed plate 5 is in U
Shape, the second direct driving motor 4 are connected with the middle part of the second fixed plate 5；Equipment mounting frame 7 takes the shape of the letter U, and it is located at the second fixed plate 5
In bayonet socket；3rd direct driving motor 6 is connected with a free end of equipment mounting frame 7, another free end and second of equipment mounting frame 7
The free end of fixed plate 5 is flexibly connected.
In the above-described embodiments, the first fixed plate 3, the second fixed plate 5 are made of stainless steel, are advantageous to avoid corroding.
In the above-described embodiments, as shown in figure 3, control unit 10 is supervisory controller, for controlling first directly to drive electricity
Machine 2, the second direct driving motor 4 and the 3rd direct driving motor 6 rotate to special angle and collect comparison data, are devices under with examining
Whether 11 in error range.
For ease of more fully understanding the utility model, next UAV Flight Control device described in the utility model is surveyed
The operation principle of test system illustrates：
As shown in Figures 1 to 3, equipment 11 to be tested is installed on equipment mounting frame 7 first, then (the tool of control unit 10
Body is supervisory controller) one special angle/acceleration magnitude is arbitrarily provided, control signal is sent to the first direct driving motor 2, second
The direct driving motor 6 of direct driving motor 4 and the 3rd makes its rotation be rotated to special angle or at a given speed, now to be tested to set
Standby 11 can obtain one angle/acceleration magnitude, and by corresponding data feedback to control unit 10, control unit 10 is again by these
Whether data compare with providing value, so as to judge equipment 12 to be tested in error range.
A kind of other structures of test system for UAV Flight Control device disclosed in the utility model are referring to existing
Technology.
It is described above, only it is preferred embodiment of the present utility model, not the utility model is made any formal
Limitation, it is therefore every without departing from the content of the technical scheme of the utility model, implement according to the technical essence of the utility model to more than
Example any modification, equivalent variations and the modification made, in the range of still falling within technical solutions of the utility model.
Claims (10)
- A kind of 1. test system for UAV Flight Control device, it is characterised in that：Also include the first direct driving motor, the first fixed plate, the second direct driving motor, the second fixed plate, the 3rd direct driving motor, equipment Mounting bracket and control unit；First direct driving motor is connected to one end of first fixed plate with horizontal, and first direct driving motor drives institute The first fixed plate is stated to rotate in horizontal plane；Second direct driving motor is vertically connected to the other end of first fixed plate, and second fixed plate is positioned at described It is connected in the axial direction of second direct driving motor and with second direct driving motor, the second direct driving motor driving described second is fixed Plate rotates in vertical plane；3rd direct driving motor is vertically connected to a free end of second fixed plate, and the equipment mounting frame is located at institute State in the axial direction of the 3rd direct driving motor and be connected with the 3rd direct driving motor, the 3rd direct driving motor drives the equipment peace Shelve and rotated in vertical plane；First fixed plate, second fixed plate, the respective surfaces of revolution of the equipment mounting frame are vertical two-by-two；First direct driving motor, second direct driving motor, the 3rd direct driving motor electrically connect with described control unit.
- 2. the test system according to claim 1 for UAV Flight Control device, it is characterised in that：Also include base Seat；First direct driving motor is on the pedestal.
- 3. the test system according to claim 1 for UAV Flight Control device, it is characterised in that：Described first is straight Drive motor, the second direct driving motor, the 3rd direct driving motor and be coated with shielding shell.
- 4. the test system according to claim 3 for UAV Flight Control device, it is characterised in that：Outside the shielding Shell is made of aluminum alloy materials.
- 5. the test system according to claim 1 for UAV Flight Control device, it is characterised in that：The equipment peace Shelve and be provided with multiple equipment bayonet socket.
- 6. the test system according to claim 1 for UAV Flight Control device, it is characterised in that：Described first is solid Fixed board is L-shaped.
- 7. the test system according to claim 1 for UAV Flight Control device, it is characterised in that：Described second is solid Fixed board takes the shape of the letter U；Second direct driving motor is connected with the middle part of second fixed plate.
- 8. the test system according to claim 7 for UAV Flight Control device, it is characterised in that：The equipment peace Shelve and take the shape of the letter U, it is located in the bayonet socket of second fixed plate；The one of 3rd direct driving motor and the equipment mounting frame from Connected by end, another free end of the equipment mounting frame is flexibly connected with the free end of second fixed plate.
- 9. the test system according to claim 1 for UAV Flight Control device, it is characterised in that：Described first is solid Fixed board, second fixed plate are made of stainless steel.
- 10. the test system according to claim 1 for UAV Flight Control device, it is characterised in that：The control Unit is supervisory controller, for controlling first direct driving motor, second direct driving motor, the 3rd direct driving motor Rotation is to special angle and collects comparison data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720870213.9U CN207148641U (en) | 2017-07-18 | 2017-07-18 | A kind of test system for UAV Flight Control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720870213.9U CN207148641U (en) | 2017-07-18 | 2017-07-18 | A kind of test system for UAV Flight Control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207148641U true CN207148641U (en) | 2018-03-27 |
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ID=61675592
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720870213.9U Active CN207148641U (en) | 2017-07-18 | 2017-07-18 | A kind of test system for UAV Flight Control device |
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| Country | Link |
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| CN (1) | CN207148641U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2799166C1 (en) * | 2023-02-27 | 2023-07-04 | Акционерное общество "ЭЙРБУРГ" | Aircraft motion simulation device for flight controller software and hardware training |
-
2017
- 2017-07-18 CN CN201720870213.9U patent/CN207148641U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2799166C1 (en) * | 2023-02-27 | 2023-07-04 | Акционерное общество "ЭЙРБУРГ" | Aircraft motion simulation device for flight controller software and hardware training |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 511457 Nansha, Guangdong, Guangzhou, Nansha District, 2 South Road, Nansha, information technology software building, North 203B room Patentee after: Guangzhou ray sun Creative Technology Limited Address before: 511457 North third gate, 203B, information technology park, Nansha District, Guangzhou, Guangdong Patentee before: Guangzhou Lei Chuang Electronics Co., Ltd. |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: Room 203b, software building north, Nansha it park, No. 2, Huanshi Avenue South, Nansha District, Guangzhou City, Guangdong Province Patentee after: Guangzhou Leixun Innovation Technology Co., Ltd Address before: 511457 Nansha, Guangdong, Guangzhou, Nansha District, 2 South Road, Nansha, information technology software building, North 203B room Patentee before: Guangzhou ray sun Creative Technology Limited |