CN207066636U - Rotor thrust and force moment testing device - Google Patents
Rotor thrust and force moment testing device Download PDFInfo
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- CN207066636U CN207066636U CN201720333221.XU CN201720333221U CN207066636U CN 207066636 U CN207066636 U CN 207066636U CN 201720333221 U CN201720333221 U CN 201720333221U CN 207066636 U CN207066636 U CN 207066636U
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- rotor
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- test structure
- testing device
- force moment
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Abstract
Embodiment of the present utility model provides a kind of rotor thrust and force moment testing device, including the first test structure (A), wherein, the first test structure (A) includes：Structure-steel framing (7)；Tension-torsion sensor (2) in the first side of structure-steel framing (7)；And motor (3) coaxially connected with the first rotor (1) to be measured and backwards to the first rotor (1) to be measured, motor (3) is coaxially connected to tension-torsion sensor (2) by motor adaptor (4), for measuring the pulling force and torque of the first rotor (1) to be measured.The purpose of this utility model is to provide a kind of structure simpler and easily operated rotor thrust and force moment testing device.
Description
Technical field
The rotor testing field of aircraft is the utility model is related to, and is surveyed more particularly, to rotor thrust and torque
Trial assembly is put.
Background technology
When the rotor to aircraft carries out performance test, it usually needs detect the various of rotor using various sensors
Parameter, pulling force, torque and rotating speed etc..But in existing performance test apparatus, various sensors and proprotor it
Between annexation complex and middle attachment structure inertia measurement structure is had a great influence, precision is by larger shadow
Ring.
Utility model content
For problem present in correlation technique, the purpose of this utility model be to provide a kind of structure it is simpler and
Easily operated rotor thrust and force moment testing device.
According to embodiment of the present utility model, there is provided a kind of rotor thrust and force moment testing device, including the first test
Structure, wherein, the first test structure includes：Structure-steel framing；Tension-torsion sensor in the first side of structure-steel framing；And with
First rotor to be measured it is coaxially connected and backwards to the first rotor to be measured motor, motor pass through motor adaptor it is coaxially connected to draw
Turn round pulling force and torque that sensor is used to measure the first rotor to be measured.
According to embodiment of the present utility model, include the speed probe of the rotating speed for measuring the first rotor to be measured,
Speed probe installation is on the first side and close to the first rotor to be measured.
According to embodiment of the present utility model, further comprise：One base；It is identical with the structure of the first test structure
And the second test structure being oppositely arranged with the first test structure；Wherein, the second rotor to be measured in the second test structure with
First rotor to be measured is positioned opposite to each other in base.
According to embodiment of the present utility model, the rotation axis of the rotation axis of the second rotor to be measured and the first rotor to be measured
Overlap.
According to embodiment of the present utility model, the first test structure is fixedly mounted on base, and the second test structure
It is slidably mounted on base so that the second rotor to be measured is closer or far from the first rotor to be measured.
According to embodiment of the present utility model, the first test structure is fixedly mounted on base by keel so that first
The rotation axis of rotor to be measured and the second rotor to be measured is in sustained height.
According to embodiment of the present utility model, it is provided with what is be parallel to each other with the rotation axis of the second rotor to be measured on base
Guide rail, and the bottom of the second test structure is provided with sliding block, wherein, sliding block is connected on guide rail so that the second test structure can
Slided relative to base.
According to embodiment of the present utility model, the leading screw being parallel to each other with guide rail, and the bottom of sliding block are provided with base
Face is provided with screw thread, wherein, the other end that one end of leading screw cooperates with the screw thread of sliding block and leading screw is relative is provided with hand
Wheel, so that the second test structure can be slided when rotating handwheel along guide rail.
According to embodiment of the present utility model, be additionally provided with base to the first test structure and the second test structure it
Between the range unit that measures of spacing.
According to embodiment of the present utility model, rotor thrust and force moment testing device further comprise damping washer, damping
Packing ring is arranged between tension-torsion sensor and structure-steel framing, for eliminating dither.
Advantageous effects of the present utility model are：
In rotor thrust of the present utility model and force moment testing device, the first test structure includes being arranged on structure-steel framing
Tension-torsion sensor, be connected with the first rotor to be measured to drive the motor that it rotates, and motor passes through motor adaptor signal
Tension-torsion sensor is connected to, so as to measure the pulling force of rotor and torque by tension-torsion sensor.Therefore, rotation of the present utility model
Wing pulling force and force moment testing device structure are simpler, and more easily operate.
Further, the speed probe of the rotating speed for measuring the first rotor to be measured is arranged on structure-steel framing, so as to measure
The rotating speed of rotor.
Brief description of the drawings
Fig. 1 is the utility model rotor thrust and the stereogram of force moment testing device one embodiment；
Fig. 2 is the partial enlarged drawing of embodiment illustrated in fig. 1.
Embodiment
Rotor thrust of the present utility model and force moment testing device are described referring now to accompanying drawing.
As depicted in figs. 1 and 2, the utility model provides a kind of rotor thrust and force moment testing device, and it is comprised at least
First test structure A.As illustrated, the first test structure A includes the first rotor 1 to be measured, structure-steel framing 7, tension-torsion sensor 2, electricity
Machine 3 and motor adaptor 4.
Specifically, tension-torsion sensor 2 is arranged in the first side of structure-steel framing 7, and motor 3 and the first rotor 1 to be measured are coaxial
Connect to drive its rotation.In addition, coaxially connected by motor adaptor 4 backwards to the side of the first rotor 1 to be measured, motor 3
To tension-torsion sensor 2, so as to measure the pulling force and torque of the first rotor 1 to be measured using tension-torsion sensor 2.Therefore, with existing skill
Art is compared, and rotor thrust and force moment testing device structure of the present utility model is simpler, and more easily operates.
Further as depicted in figs. 1 and 2, rotor thrust and force moment testing device also include being used to measure the first rotor to be measured
The speed probe 6 of 1 rotating speed.Wherein, the speed probe 6 is installed on the first side and set close to the first rotor 1 to be measured
Put.Therefore, the speed probe 6 of the rotating speed for measuring the first rotor 1 to be measured is arranged on structure-steel framing 7, so as to measure rotor 1
Rotating speed.So, the utility model may be further in a manner of simpler simultaneously and structure carries out pulling force, the torque of rotor
And tachometric survey.
With continued reference to accompanying drawing, rotor thrust and force moment testing device of the present utility model may further include the second test
Structure B.The second test structure B is identical with the first test structure A structure and is set relatively with the first test structure A
Put.As shown in figure 1, the second 1.2 and first rotor 1 to be measured of rotor to be measured in the second test structure B is positioned opposite to each other the bottom of in
On seat 13.
In one embodiment, the rotation axis of the second rotor 1.2 to be measured can be with the rotation axis of the first rotor 1 to be measured
Overlap.Alternatively, the first test structure A is fixedly mounted on base 13, and the second test structure B is slidably mounted in bottom
So that the second rotor 1.2 to be measured is closer or far from the first rotor 1 to be measured on seat 13.So, the tests of the first test structure A and second
Spacing between structure B can be adjusted, so as to the test for various different parameters.
In one embodiment, as shown in figure 1, the first test structure A is fixedly mounted on base 13 by keel 12
So that the rotation axis of the first 1 and second rotor 1.2 to be measured of rotor to be measured is in sustained height, in order to measure the first rotation to be measured
1 and second rotor 1.2 to be measured of the wing rotates the parameters relationship of the mutual start of phase simultaneously.
In addition, the guide rail 8 being parallel to each other with the rotation axis of the second rotor 1.2 to be measured is provided with base 13, and the
Two test structure B bottom is provided with sliding block 11.Wherein, sliding block 11 is connected on guide rail 8 so that the second test structure B can be relative
Slided in base 13.More specifically, the leading screw 9 being parallel to each other with guide rail 8 is provided with base 13, and the bottom surface of sliding block 11 is set
It is equipped with screw thread.The other end that one end of leading screw 9 cooperates with the screw thread of sliding block 11 and leading screw 9 is relative is provided with handwheel 10.
So, when rotating handwheel 10, the second test structure B can slide along guide rail 8, so as to closer or far from the first test structure A, with
It is adjusted to suitable demand measurement position.
In addition, in one embodiment of the present utility model, it is additionally provided with base 13 to the first test structure A and
The range unit that spacing measures between two test structure B.And rotor thrust of the present utility model and force moment testing device
Further comprise damping washer 5, damping washer 5 is arranged between tension-torsion sensor 2 and structure-steel framing 7, for eliminating high frequency vibrating
It is dynamic, so as to improve the measurement accuracy of tension-torsion sensor 2.
In addition, in the preferred embodiment being not shown, tension-torsion sensor 2 and speed probe 6 can be via letters
Number externally connected processing equipment of Acquisition Circuit signal.
It is of the present utility model it is specifically used during, connection between all parts and part can by bolt or
Mode connects for screw.First rotor 1 to be measured of the driving of motor 3 produces pulling force and torque, pulling force and torque are acted on by motor adaptor 4
On tension-torsion sensor 2.Tension-torsion sensor 2 is by power and torque by electric signal output, while speed probe 6 passes through infrared external reflection
Principle measures rotor rotating speed and tach signal is switched into electric signal output.Tension-torsion sensor 2 and the signal of speed probe 6 are by letter
Number Acquisition Circuit is connected to computer and the window real-time display and record that pass through preprogramming.Damping washer 5 can be arranged on
To eliminate dither between motor adaptor 4 and structure-steel framing 7, the measurement accuracy of pulling force/torque sensor 6 is improved.Pass through handwheel
10 rotating threaded shafts 9 adjust the distance between two rotors, can measure the pulling force and torque of two rotors of different distance.
For device of the present utility model, it includes two kinds of mode of operations：Single rotor mode, is only needed in such a mode
To electricity on the motor, tension-torsion sensor and tachometer of measuring of one side；More rotor modes, the electricity to both sides is needed under this model
It is electric on machine, tension-torsion sensor and tachometer of measuring.
For single rotor measurement pattern, i.e., only survey rotor (such as first or second rotor 1,1.2 to be measured)
Pulling force, torque and rotating speed, the pattern only needs side arrangement works in Fig. 1 (left side or right side), if the performance parameter of rotor
, it is known that the parameter of the device measuring motor can be used, if the parameter of the device measuring rotor can be used known to the parameter of motor.
The pattern needs to measure rotating speed n, pulling force F, moment of torsion M, electric moter voltage V and the electric current I of propeller, draws these amount can meters
Calculate the performance of rotor and motor.
, it is necessary to which structure on two sides works together for more rotor measurement patterns, i.e., two rotors 1,1.2 rotate simultaneously,
And 5 parameters are measured as single rotor mode, while also need to the distance between two rotors of measurement L, obtain these ginsengs
Number can calculates corresponding performance by the parameter between them.
In summary, rotor thrust and force moment testing device structure of the present utility model is simpler, and more easily
Operation.And test device of the present utility model can realize propeller pulling force, torque and measurement of rotating speed, and can be simultaneously right
Two rotors are tested, and are tested its coefficient result, are interfered for analyzing it.Pulling force, torque and rotating speed are surveyed
Measurer has real-time.
Preferred embodiment of the present utility model is the foregoing is only, is not limited to the utility model, for this
For the technical staff in field, the utility model can have various modifications and variations.It is all in the spirit and principles of the utility model
Within, any modification, equivalent substitution and improvements made etc., it should be included within the scope of protection of the utility model.
Claims (10)
1. a kind of rotor thrust and force moment testing device, it is characterised in that including the first test structure (A), wherein, described first
Test structure (A) includes：
Structure-steel framing (7)；
Tension-torsion sensor (2) in the first side of the structure-steel framing (7)；And
Motor (3) coaxially connected with the first rotor (1) to be measured and backwards to the described first rotor (1) to be measured, the motor (3)
By motor adaptor (4) the tension-torsion sensor (2), for measuring the drawing of the described first rotor (1) to be measured
Power and torque.
2. rotor thrust according to claim 1 and force moment testing device, it is characterised in that also include described for measuring
The speed probe (6) of the rotating speed of first rotor (1) to be measured, the speed probe (6) be arranged on the first side on and
Close to the described first rotor (1) to be measured.
3. rotor thrust according to claim 2 and force moment testing device, it is characterised in that further comprise：One base；
The second survey that is identical with the structure of first test structure (A) and being oppositely arranged with first test structure (A)
Try structure (B)；
Wherein, the second rotor (1.2) to be measured in second test structure (B) and the described first rotor (1) to be measured phase each other
To being arranged at the base.
4. rotor thrust according to claim 3 and force moment testing device, it is characterised in that second rotor to be measured
(1.2) rotation axis and the rotation axis coincident of the described first rotor (1) to be measured.
5. rotor thrust according to claim 4 and force moment testing device, it is characterised in that first test structure
(A) it is fixedly mounted on the base (13), and second test structure (B) is slidably mounted in the base (13)
Above so that second rotor (1.2) to be measured is closer or far from the described first rotor (1) to be measured.
6. rotor thrust according to claim 5 and force moment testing device, it is characterised in that first test structure
(A) it is fixedly mounted on by keel (12) on the base (13) so that first rotor (1) to be measured and described second is treated
The rotation axis for surveying rotor (1.2) is in sustained height.
7. rotor thrust according to claim 5 and force moment testing device, it is characterised in that set on the base (13)
There are the guide rail (8) that the rotation axis with the described second rotor (1.2) to be measured is parallel to each other, and second test structure (B)
Bottom be provided with sliding block (11), wherein, the sliding block (11) is connected on the guide rail (8) so that second test structure
(B) can be slided relative to the base (13).
8. rotor thrust according to claim 7 and force moment testing device, it is characterised in that set on the base (13)
There is the leading screw (9) being parallel to each other with the guide rail (8), and the bottom surface of the sliding block (11) is provided with screw thread,
Wherein, the screw thread of one end of the leading screw (9) and the sliding block (11) cooperates and that the leading screw (9) is relative is another
One end is provided with handwheel (10), so that second test structure (B) can be along the guide rail (8) when rotating handwheel (10)
Slide.
9. rotor thrust according to claim 8 and force moment testing device, it is characterised in that on the base (13) also
It is provided with to spacing measures between first test structure (A) and second test structure (B) range unit.
10. rotor thrust according to claim 1 and force moment testing device, it is characterised in that the rotor thrust and power
Torque test device further comprises damping washer (5), and the damping washer (5) is arranged on the tension-torsion sensor (2) and described
Between structure-steel framing (7), for eliminating dither.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720333221.XU CN207066636U (en) | 2017-03-31 | 2017-03-31 | Rotor thrust and force moment testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720333221.XU CN207066636U (en) | 2017-03-31 | 2017-03-31 | Rotor thrust and force moment testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207066636U true CN207066636U (en) | 2018-03-02 |
Family
ID=61501305
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720333221.XU Active CN207066636U (en) | 2017-03-31 | 2017-03-31 | Rotor thrust and force moment testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207066636U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639379A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft rotor component test device |
| CN109436376A (en) * | 2018-12-29 | 2019-03-08 | 深圳市赛为智能股份有限公司 | Devices and methods therefor for unmanned plane propeller tensile test |
-
2017
- 2017-03-31 CN CN201720333221.XU patent/CN207066636U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639379A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft rotor component test device |
| CN109436376A (en) * | 2018-12-29 | 2019-03-08 | 深圳市赛为智能股份有限公司 | Devices and methods therefor for unmanned plane propeller tensile test |
| CN109436376B (en) * | 2018-12-29 | 2023-12-22 | 深圳市赛为智能股份有限公司 | Device and method for testing pull force of propeller of unmanned aerial vehicle |
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