CN210027979U - Multi-rotor unmanned aerial vehicle power system test bench - Google Patents
Multi-rotor unmanned aerial vehicle power system test bench Download PDFInfo
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- CN210027979U CN210027979U CN201822201443.3U CN201822201443U CN210027979U CN 210027979 U CN210027979 U CN 210027979U CN 201822201443 U CN201822201443 U CN 201822201443U CN 210027979 U CN210027979 U CN 210027979U
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Abstract
The application discloses many rotor unmanned aerial vehicle driving system testboard, including the base, the base rotates and is connected with the horn mount pad, and the symmetry is provided with two transversely extending's horn on the horn mount pad, and driving motor, driving motor's output shaft screw are installed to the end portion of the cantilever end of horn. According to the technical scheme that this application provided, rotate between horn mount pad and the base and be connected, provide the driving system test bench of rocking arm formula structure to the change and the vibration condition of angle in the simulation actual flight, its structure accords with the test requirement of driving system reliability in many rotor unmanned aerial vehicle actual flights more, makes the test result more reliable.
Description
Technical Field
The application relates to many rotor unmanned aerial vehicle stability test technical field generally, especially relates to a many rotor unmanned aerial vehicle driving system testboard.
Background
The Unmanned Aerial Vehicle (UAV) can realize autonomous or remote control flight without a flight power device of an operator, and has wider application in the civil and military fields along with the deep development of relevant technologies such as microelectronics, computer communication, autonomous control and the like.
Compared with fixed wing aircrafts and flapping wing aircrafts, the multi-rotor unmanned aerial vehicle has the advantages of flexibility, simple structure, convenience in operation, vertical take-off and landing, low cost and relative complexity and diversification of executable tasks, and can be rapidly called as a popular field of academic and technical research worldwide.
At present, the reliability test of the unmanned aerial vehicle power system mainly locks the system and a fixed test bench, and provides a constantly-changing accelerator signal for long-time frequency sweep test so as to evaluate whether the reliability and performance of structures such as a motor, an electric speed regulator, a propeller and the like can meet the use requirements. However, in actual use, the power system is connected with the carbon tube horn, certain vibration exists during flying, the service life of the power system is greatly influenced, the current testing method just ignores the testing condition, and the requirement of the testing table on higher structural strength of the power system due to the fact that the testing table is fixed and the angle change of the airplane during actual flying cannot be simulated.
SUMMERY OF THE UTILITY MODEL
In view of the above-discussed deficiencies or inadequacies in the prior art, it would be desirable to provide a multi-rotor unmanned aerial vehicle power system test stand.
The utility model provides a many rotors unmanned aerial vehicle driving system testboard, which comprises a base, the base rotates and is connected with the horn mount pad, the symmetry is provided with two horizontal extension's horn on the horn mount pad, driving motor is installed to the end portion of the cantilever end of horn, driving motor's output shaft screw.
Furthermore, two coaxial mounting holes are formed in the horn mounting seat, the two mounting holes are symmetrically distributed about a rotation axis of the horn mounting seat, and the horn is mounted in each mounting hole.
Further, a pair of connecting lugs which are oppositely arranged and provided with coaxial holes are arranged on the base;
the horn mounting seat comprises a support plate and connecting seats arranged at two ends of the support plate, each connecting seat is provided with a mounting hole, the support plate is provided with a through hole corresponding to the shaft hole of the connecting lug, and the support plate is rotatably connected between the pair of connecting lugs through a rotating shaft.
Furthermore, an elastic buffer is connected between each horn and the base; the two elastic buffer parts are symmetrically distributed around the rotation axis of the horn mounting seat.
Further, the elastic buffer is connected with the end head part of the cantilever end of the machine arm.
Further, the elastic buffer comprises a spring, and a safety rope is arranged inside the spring.
Further, the elastomeric dampener includes an elastomeric cord.
Further, the driving motor comprises a motor base, a motor and an electric regulator electrically connected with a motor lead;
the motor base comprises a motor base body, a motor cover and a bottom shell connected with the bottom of the motor base body, the motor is arranged between the top of the motor base body and the motor cover, a containing cavity is formed between the motor base body and the bottom shell, and the electric regulator is arranged in the containing cavity.
Further, a step surface is arranged on the periphery of the bottom of the motor seat body, a plurality of first heat dissipation grooves are formed in the step surface, and a plurality of second heat dissipation grooves are formed in the area, right opposite to the step surface, of the top of the bottom shell.
Further, a pair of lugs are convexly arranged at the bottom of the bottom shell, and the lugs are connected with the end head part of the cantilever end of the machine arm through bolts.
According to the technical scheme that this application provided, rotate between horn mount pad and the base and be connected, provide a driving system test bench with rocking arm formula structure to the change and the vibration condition of angle in the simulation actual flight, its structure accords with the test requirement of driving system reliability in many rotor unmanned aerial vehicle actual flights more, makes the test result more reliable.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
fig. 1 is a schematic structural diagram of a multi-rotor unmanned aerial vehicle power system test board according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a multi-rotor unmanned aerial vehicle power system test board according to another embodiment of the present invention;
fig. 3 is a schematic structural diagram of a driving motor according to an embodiment of the present invention.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1, the embodiment of the utility model provides a many rotors unmanned aerial vehicle driving system testboard, including base 1, the base rotates and is connected with horn mount pad 2, and the symmetry is provided with two horizontal extension's horn 3 on the horn mount pad 2, and driving motor 4, driving motor 4's output shaft screw 5 are installed to the end of the cantilever end of horn 3.
The many rotor unmanned aerial vehicle driving system testboard that this embodiment provided to two horn are connected to the horn mount pad, form rocking arm formula structure, and the scene of angle change in the simulation unmanned aerial vehicle actual flight surveys many rotor unmanned aerial vehicle's driving system's performance better.
Further, be provided with the mounting hole of two coaxial lines on the horn mount pad 2, two mounting holes are around the axis of rotation symmetric distribution of horn mount pad, installation horn 3 in every mounting hole, closely cooperate between horn 3 and the mounting hole, realize the firm installation of horn.
Further, a pair of connecting lugs 6 which are oppositely arranged and have coaxial holes are arranged on the base 1;
the horn mounting base 2 comprises a support plate 21 and connecting bases 22 arranged at two ends of the support plate 21, each connecting base 22 is provided with a mounting hole, the support plate 21 is provided with a through hole corresponding to the shaft hole of the connecting lug, and the support plate 21 is rotatably connected between the pair of connecting lugs 6 through a rotating shaft.
The swing of the horn mounting seat is realized through the rotary connection between the pair of connecting lugs and the supporting plate, and a structure similar to a seesaw is formed.
When the propellers on two sides are driven to move by a given signal, one of the engine arms is connected with the propellers and rises or falls suddenly, the whole test bench is easy to shake, and the placing structure is unstable.
As an alternative embodiment, unlike the test bench shown in fig. 1, in the test bench shown in fig. 2, an elastic buffer is further connected between each horn 3 and the base 1; the two elastic buffer parts are symmetrically distributed around the rotation axis of the horn mounting seat.
The elastic buffer piece keeps the initial states of the two machine arms horizontal, and when the propeller rotates to generate upward pulling force, instability caused by steep upwarping of the machine arms is avoided through the elastic buffer piece.
Furthermore, the elastic buffer piece is connected with the end head part of the cantilever end of the machine arm, so that the condition that the machine arm is steeply upwarped is relieved as much as possible.
The elastic buffer piece comprises a spring 7, a safety rope 8 is arranged inside the spring 7, the stretching length of the spring is limited by the safety rope, the specific motion amplitude of the propeller in the power system can be seen, and the stretching length of the spring is reasonably set to be matched with the motion amplitude of the propeller.
Furthermore, the elastic buffer part can also comprise an elastic rope, and when the machine arm is driven by the propeller to rise steeply, the elastic rope can avoid the unstable condition of the test bench caused by the elastic rope.
Further, as shown in fig. 3, the driving motor 4 includes a motor base, a motor 8 and an electronic controller electrically connected to a motor lead;
the motor base comprises a motor base body 9, a motor cover 10 and a bottom shell 11 connected with the bottom of the motor base body, the motor 8 is arranged between the top of the motor base body 9 and the motor cover 10, a containing cavity is formed between the motor base body 9 and the bottom shell 11, and the electric regulation device is arranged in the containing cavity.
The surface of the motor cover is provided with a plurality of heat dissipation openings for dissipating heat generated by the motor, so that the service life of the motor is prolonged; the output shaft of motor connects the screw, and the screw is located the surface of motor cover.
In the embodiment, the motor and the electric regulation are integrally arranged to form the driving motor, so that the installation process is simplified, and the operation is simple.
Further, a step surface 12 is arranged on the periphery of the bottom of the motor base body 9, a plurality of first heat dissipation grooves are formed in the step surface 12, and a plurality of second heat dissipation grooves are formed in the area, opposite to the step surface, of the top of the bottom shell, so that a heat dissipation gap is formed between the step surface and the top of the bottom shell. For example, a plurality of step surfaces are uniformly distributed on the periphery of the bottom of the motor seat body, and a plurality of heat dissipation gaps are formed between the step surfaces and the top of the bottom shell; or, the bottom of the motor seat body is provided with a circular bulge, and a circle of heat dissipation gap is formed between the outer peripheral side of the circular bulge and the top of the bottom shell; or, the bottom of the motor seat body is provided with a cylindrical bulge, and a circle of heat dissipation gap is formed between the peripheral side of the cylindrical bulge and the top of the bottom shell. Through heat radiation structure, can distribute away the heat that the motor produced with electricity accent effectively, improve the radiating effect, further reduce the temperature rise of motor and electricity accent, the life of extension motor and electricity accent.
Further, the bottom of the bottom case 11 is protrusively provided with a pair of lugs 13, and the lugs 13 are connected to the tip portions of the cantilever ends of the arms by bolts. The end head part of the cantilever end of the horn is provided with a lug matched with the lug, the lug is embedded between the pair of lugs, the pair of lugs are provided with coaxial threaded holes, the lugs are provided with through holes, and the lugs are in bolted connection with the lugs to realize the detachable connection of the driving motor.
The test table for the power system of the multi-rotor unmanned aerial vehicle is characterized in that the horn is a carbon tube horn, the horn mounting seat is a carbon tube mounting seat, and the horn, the horn mounting seat and the power system (the output shaft of the driving motor is connected with a propeller) all simulate an unmanned aerial vehicle object, so that the test requirement of vibration of the unmanned aerial vehicle on the reliability of the power system in actual flight is simulated more truly; the driving motor connected with the horn is integrally arranged by adopting the motor and the electric regulator, so that the actual power system can be simulated better, the installation process is simplified, and the operation is convenient.
The test board is connected with a flight control device, and a motor for driving the propeller to rotate is connected with the flight control device through a lead. Two sets of frequency sweeping programs with time intervals are burnt into the flight control device, and then the power is switched on. The power system operates periodically according to the throttle control signal. Can produce an ascending pulling force after the screw is rotatory, the unbalanced pulling force in both sides can make the device demonstrate the up-and-down motion automatically, and the incessant change of angle is to driving system reliability requirement when simulation unmanned aerial vehicle actually flies from this.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by those skilled in the art that the scope of the invention herein disclosed is not limited to the particular combination of features described above, but also encompasses other arrangements formed by any combination of the above features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (10)
1. The utility model provides a many rotor unmanned aerial vehicle driving system testboard, its characterized in that, includes the base, the base rotates and is connected with the horn mount pad, the symmetry is provided with two horn of horizontal extension on the horn mount pad, driving motor is installed to the end portion of the cantilever end of horn, driving motor's output shaft connects the screw.
2. The multi-rotor unmanned aerial vehicle power system test stand of claim 1, wherein the horn mount is provided with two coaxial mounting holes, the two mounting holes are symmetrically distributed about a rotation axis of the horn mount, and the horn is mounted in each mounting hole.
3. The multi-rotor unmanned aerial vehicle power system test stand of claim 2, wherein a pair of engaging lugs arranged oppositely and having coaxial holes are provided on the base;
the horn mounting seat comprises a support plate and connecting seats arranged at two ends of the support plate, each connecting seat is provided with a mounting hole, the support plate is provided with a through hole corresponding to the shaft hole of the connecting lug, and the support plate is rotatably connected between the pair of connecting lugs through a rotating shaft.
4. The testing stand of a multi-rotor unmanned aerial vehicle according to any of claims 1-3, wherein an elastomeric damper is further coupled between each of said horn and said base; the two elastic buffer parts are symmetrically distributed around the rotation axis of the horn mounting seat.
5. The multi-rotor unmanned aerial vehicle power system test stand of claim 4, wherein the elastomeric bumpers are attached to tip portions of cantilevered ends of the horn.
6. The multi-rotor unmanned aerial vehicle power system test stand of claim 5, wherein the elastomeric bumpers comprise springs having safety cords disposed therein.
7. The multi-rotor unmanned aerial vehicle power system test stand of claim 5, wherein the elastomeric bumpers comprise elastomeric cords.
8. The multi-rotor unmanned aerial vehicle power system test stand of claim 1, wherein the drive motor comprises a motor base, a motor, and an electrical governor electrically connected to a lead of the motor;
the motor base comprises a motor base body, a motor cover and a bottom shell connected with the bottom of the motor base body, the motor is arranged between the top of the motor base body and the motor cover, a containing cavity is formed between the motor base body and the bottom shell, and the electric regulator is arranged in the containing cavity.
9. The multi-rotor unmanned aerial vehicle power system test stand of claim 8, wherein a step surface is arranged on the periphery of the bottom of the motor base body, a plurality of first heat dissipation grooves are arranged on the step surface, and a plurality of second heat dissipation grooves are arranged in an area, opposite to the step surface, of the top of the bottom shell.
10. The multi-rotor unmanned aerial vehicle power system test stand of claim 8, wherein a pair of lugs are provided protruding from a bottom of the bottom housing, and are bolted to a tip portion of the cantilevered end of the horn.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822201443.3U CN210027979U (en) | 2018-12-26 | 2018-12-26 | Multi-rotor unmanned aerial vehicle power system test bench |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201822201443.3U CN210027979U (en) | 2018-12-26 | 2018-12-26 | Multi-rotor unmanned aerial vehicle power system test bench |
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| CN210027979U true CN210027979U (en) | 2020-02-07 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112737186A (en) * | 2021-01-28 | 2021-04-30 | 浙江吉利控股集团有限公司 | Motor installation assembly of vertical take-off and landing electric aircraft test platform |
| CN113148145A (en) * | 2021-05-08 | 2021-07-23 | 北京航空航天大学 | Flapping wing elastic energy storage mechanism of miniature bionic flapping wing aircraft |
| CN113306745A (en) * | 2021-07-30 | 2021-08-27 | 西咸新区千兆智能科技有限公司 | Power testing device and system |
-
2018
- 2018-12-26 CN CN201822201443.3U patent/CN210027979U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112737186A (en) * | 2021-01-28 | 2021-04-30 | 浙江吉利控股集团有限公司 | Motor installation assembly of vertical take-off and landing electric aircraft test platform |
| CN112737186B (en) * | 2021-01-28 | 2022-06-14 | 浙江吉利控股集团有限公司 | Motor installation assembly of vertical take-off and landing electric aircraft test platform |
| CN113148145A (en) * | 2021-05-08 | 2021-07-23 | 北京航空航天大学 | Flapping wing elastic energy storage mechanism of miniature bionic flapping wing aircraft |
| CN113306745A (en) * | 2021-07-30 | 2021-08-27 | 西咸新区千兆智能科技有限公司 | Power testing device and system |
| CN113306745B (en) * | 2021-07-30 | 2021-11-02 | 西咸新区千兆智能科技有限公司 | Power testing device and system |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210720 Address after: 518063 5th floor, block B, building 1, software industry base, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Fengyi Technology (Shenzhen) Co.,Ltd. Address before: 518061 Intersection of Xuefu Road (south) and Baishi Road (east) in Nanshan District, Shenzhen City, Guangdong Province, 6-13 floors, Block B, Shenzhen Software Industry Base Patentee before: SF TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right |