CN205664959U - Be applied to dynamic pulling force testing arrangement on unmanned aerial vehicle motor and rotor - Google Patents
Be applied to dynamic pulling force testing arrangement on unmanned aerial vehicle motor and rotor Download PDFInfo
- Publication number
- CN205664959U CN205664959U CN201620556082.2U CN201620556082U CN205664959U CN 205664959 U CN205664959 U CN 205664959U CN 201620556082 U CN201620556082 U CN 201620556082U CN 205664959 U CN205664959 U CN 205664959U
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- motor
- rotor
- fixed
- motor fixing
- screw
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Abstract
The utility model discloses a be applied to dynamic pulling force testing arrangement on unmanned aerial vehicle motor and rotor, including sliding rail support, slide rail, slider, motor fixing base, tensiometer, motor, rubber tube, hexagonal screw, hexagon socket head cap screw, rotor, liquid crystal display, button, aluminum alloy cushion, solid iron plate, motor and rotor are fixed on the motor fixing base, its characterized in that: the top position at sliding rail support is fixed through hexagon socket head cap screw respectively to slide rail and slider, the motor fixing base passes through hexagon socket head cap screw and slider fixed connection, and the slider cover is on the slide rail, the tensiometer passes through hexagonal screw to be fixed on the aluminum alloy cushion, the rubber tube is arranged in between motor fixing base and the tensiometer, and the rubber tube upper end is fixed inside the motor fixing base through hexagonal screw, the utility model discloses an adopt accurate ball slider as the motor mount pad, can effectively offset the anti - torsion that motor and rotor during operation produced, keep the degree of freedom to tensile action direction.
Description
Technical field
This utility model relates to a kind of unmanned plane device for testing tensile force, specially one and is applied to unmanned plane motor and rotor
On dynamic tension test device.
Background technology
Unmanned plane is the not manned vehicle of the presetting apparatus manipulation utilizing radio robot with providing for oneself.It is special
Point is the features such as landing flexible, easy manipulation, good stability, is widely used in the purposes such as agricultural plant protection, middle scouting, supervision.
The value of thrust that the torsion of the motor of aircraft and rotor torsion produce is the core design foundation of the type aircraft
With product quality basis for estimation, and existing motor and rotor thrust test device use, motor is directly installed on pulling force
On sensor, so can cause the situation that tensile test precision is the highest and strain gauge is easily damaged.
Utility model content
The purpose of this utility model is to provide a kind of dynamic tension being applied on unmanned plane motor and rotor test dress
Putting, it can effectively solve the problem that problem present in background technology.
For achieving the above object, this utility model provides following technical scheme: one is applied to unmanned plane motor and rotor
On dynamic tension test device, including sliding rail rack (1), slide rail (2), slide block (3), motor fixing seat (4), strain gauge (5),
Motor (6), rubber tube (7), hex(agonal)screw (8), hexagon socket head cap screw (9), rotor (10), LCDs (11), button (12),
Aluminium alloy cushion block (13), solid iron (14)；Described motor (6) and rotor (10) are fixed in motor fixing seat (4)；Its feature
It is: described slide rail (2) and slide block (3) are fixed on the top position of sliding rail rack (1) respectively by hexagon socket head cap screw (9)；Institute
State motor fixing seat (4) to be connected by hexagon socket head cap screw (9) and slide block (3) are fixing, and slide block (3) is enclosed within slide rail (2)；Described
Strain gauge (5) is fixed on aluminium alloy cushion block (13) by hex(agonal)screw (8)；Described rubber tube (7) is placed in motor fixing seat (4)
And between strain gauge (5), and rubber tube (7) upper end is fixed on motor fixing seat (4) inside by hex(agonal)screw (8).
Further, described slide block (3) is placed between motor fixing seat (4) and sliding rail rack (1), and slides with slide rail (2)
Connect.
Further, described fixing seat (4) is connected with strain gauge (5) elasticity.
Further, described strain gauge (5) upper surface location is provided with LCDs (11) and button (12).
Further, described sliding rail rack (1) and strain gauge (5) are by hex(agonal)screw (8) is fixing and centre position is also installed
There is an aluminium alloy cushion block (13).
Further, described solid iron (14) is fixed on sliding rail rack (1) by hexagon socket head cap screw (9), described solid
Iron block (14) is equipped with one at slide rail (2) upper and lower side.
Compared with prior art, the beneficial effects of the utility model are: this one is applied on unmanned plane motor and rotor
Dynamic tension test device use precise ball slide block as motor mount, it is possible to when effectively offsetting motor and rotor work
The anti-twisted power produced, and, large stroke reciprocating fluent along slide rail when supporting motor and rotor work；Solve and existed in the past
The anti-twisted power of the circumferencial direction impact on pulling force sensor in tension measurement, and the action direction of pulling force is kept degree of freedom；
It addition, this utility model cost of manufacture is lower, assembling is simpler, more meets process requirements.
Accompanying drawing explanation
Fig. 1 is right view of the present utility model；
Fig. 2 is front view of the present utility model；
Fig. 3 is partial enlarged drawing of the present utility model；
In reference: 1-sliding rail rack, 2-slide rail, 3-slide block, 4-motor fixing seat, 5-strain gauge, 6-motor, 7-rubber
Sebific duct, 8-hex(agonal)screw, 9-hexagon socket head cap screw, 10-rotor, 11-LCDs, 12-button, 13-aluminium alloy cushion block, 14-
Solid iron.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole
Embodiment.Based on the embodiment in this utility model, those of ordinary skill in the art are not under making creative work premise
The all other embodiments obtained, broadly fall into the scope of this utility model protection.
Referring to Fig. 1, Fig. 2 and Fig. 3, this utility model provides a kind of technical scheme: one be applied to unmanned plane motor and
Dynamic tension test device on rotor, including sliding rail rack, slide rail, slide block, motor fixing seat, strain gauge, motor, rubber
Pipe, hex(agonal)screw, hexagon socket head cap screw, rotor, hexagon socket head cap screw；Slide rail is fixed on the upper position of sliding rail rack by hex(agonal)screw
Putting, strain gauge is fixed on the lower position of sliding rail rack by hexagon socket head cap screw, and meanwhile, strain gauge is provided with a liquid crystal display
Screen and nine buttons；Slide block is placed between motor fixing seat and sliding rail rack, and slide block set is on slide rail, and slide block slides with slide rail
Connect.It addition, fixing seat is connected with strain gauge elasticity, and motor fixing seat is fixed on slide block by hexagon socket head cap screw, meanwhile,
The quantity of hexagon socket head cap screw has four；Motor and rotor are fixed in motor fixing seat；Rubber tube is placed in motor fixing seat and draws
Between power meter；Sliding rail rack and strain gauge are fixed with an aluminium alloy cushion block by hex(agonal)screw, are used for fixing connecting sliding rail
Support and strain gauge；Solid iron is placed in the two ends up and down of slide rail, is fixed on sliding rail rack by hexagon socket head cap screw, is used for limiting
The sliding scale of fixed slider.
Of the present utility model when design: when motor and rotor work, it will produce a pulling force vertically upward, this
Pulling force meeting drive motor fixes seat and slide block moves upwardly together, and this time, due to the elastic reaction of rubber tube, will produce
One elastic force, when after pulling force with Spring balanced, motor fixing seat and slide block will no longer move upward, and at this moment motor and rotor produce
Pulling force will pass to strain gauge by rubber tube, now, the size of pulling force just can be in the upper display of strain gauge.
It addition, this kind of dynamic tension test device being applied on unmanned plane motor and rotor uses precise ball slide block
As motor mount, it is possible to the anti-twisted power produced when effectively offsetting motor and rotor work, and support motor and rotor work
Time, large stroke reciprocating fluent along slide rail；Solve in the past in tension measurement the anti-twisted power of circumferencial direction to pulling force
The impact of sensor, and the action direction of pulling force is kept degree of freedom.
Embodiment the most of the present utility model, for the ordinary skill in the art,
It is appreciated that in the case of without departing from principle of the present utility model and spirit and these embodiments can be carried out multiple change, repair
Changing, replace and modification, scope of the present utility model is defined by the appended claims and the equivalents thereof.
Claims (6)
1. be applied on unmanned plane motor and rotor dynamic tension test a device, including sliding rail rack (1), slide rail (2),
Slide block (3), motor fixing seat (4), strain gauge (5), motor (6), rubber tube (7), hex(agonal)screw (8), hexagon socket head cap screw (9),
Rotor (10), LCDs (11), button (12), aluminium alloy cushion block (13), solid iron (14)；Described motor (6) and rotation
The wing (10) is fixed in motor fixing seat (4)；It is characterized in that: described slide rail (2) and slide block (3) pass through hexagon socket head cap screw respectively
(9) top position of sliding rail rack (1) it is fixed on；Described motor fixing seat (4) is solid with slide block (3) by hexagon socket head cap screw (9)
Determine to connect, and slide block (3) is enclosed within slide rail (2)；Described strain gauge (5) is fixed on aluminium alloy cushion block by hex(agonal)screw (8)
(13) on；Described rubber tube (7) is placed between motor fixing seat (4) and strain gauge (5), and hexagonal is passed through in rubber tube (7) upper end
It is internal that screw (8) is fixed on motor fixing seat (4).
A kind of dynamic tension test device being applied on unmanned plane motor and rotor the most according to claim 1, it is special
Levy and be: described slide block (3) is placed between motor fixing seat (4) and sliding rail rack (1), and be slidably connected with slide rail (2).
A kind of dynamic tension test device being applied on unmanned plane motor and rotor the most according to claim 1, it is special
Levy and be: described fixing seat (4) is connected with strain gauge (5) elasticity.
A kind of dynamic tension test device being applied on unmanned plane motor and rotor the most according to claim 1, it is special
Levy and be: described strain gauge (5) upper surface location is provided with LCDs (11) and button (12).
A kind of dynamic tension test device being applied on unmanned plane motor and rotor the most according to claim 1, it is special
Levy and be: described sliding rail rack (1) and strain gauge (5) are by hex(agonal)screw (8) is fixing and centre position is also equipped with an aluminum
Alloy cushion block (13).
A kind of dynamic tension test device being applied on unmanned plane motor and rotor the most according to claim 1, it is special
Levy and be: described solid iron (14) is fixed on sliding rail rack (1) by hexagon socket head cap screw (9), described solid iron (14)
It is equipped with one at slide rail (2) upper and lower side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620556082.2U CN205664959U (en) | 2016-06-07 | 2016-06-07 | Be applied to dynamic pulling force testing arrangement on unmanned aerial vehicle motor and rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620556082.2U CN205664959U (en) | 2016-06-07 | 2016-06-07 | Be applied to dynamic pulling force testing arrangement on unmanned aerial vehicle motor and rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205664959U true CN205664959U (en) | 2016-10-26 |
Family
ID=57156948
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620556082.2U Expired - Fee Related CN205664959U (en) | 2016-06-07 | 2016-06-07 | Be applied to dynamic pulling force testing arrangement on unmanned aerial vehicle motor and rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205664959U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108444631A (en) * | 2018-07-05 | 2018-08-24 | 陈俊胤 | A kind of real-time stretching force detecting apparatus of unmanned plane and its pull force calculation method |
| CN109000841A (en) * | 2018-08-24 | 2018-12-14 | 中国兵器工业计算机应用技术研究所 | A kind of general tensile test tooling rack of propeller |
| CN109029808A (en) * | 2018-07-05 | 2018-12-18 | 陈俊胤 | A kind of airborne propeller dynamic tension measuring device |
-
2016
- 2016-06-07 CN CN201620556082.2U patent/CN205664959U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108444631A (en) * | 2018-07-05 | 2018-08-24 | 陈俊胤 | A kind of real-time stretching force detecting apparatus of unmanned plane and its pull force calculation method |
| CN109029808A (en) * | 2018-07-05 | 2018-12-18 | 陈俊胤 | A kind of airborne propeller dynamic tension measuring device |
| CN109000841A (en) * | 2018-08-24 | 2018-12-14 | 中国兵器工业计算机应用技术研究所 | A kind of general tensile test tooling rack of propeller |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161026 Termination date: 20180607 |