CN107806996A - A kind of unmanned plane propeller dynamic tension monitoring device - Google Patents
A kind of unmanned plane propeller dynamic tension monitoring device Download PDFInfo
- Publication number
- CN107806996A CN107806996A CN201710997476.0A CN201710997476A CN107806996A CN 107806996 A CN107806996 A CN 107806996A CN 201710997476 A CN201710997476 A CN 201710997476A CN 107806996 A CN107806996 A CN 107806996A
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- CN
- China
- Prior art keywords
- unmanned plane
- equipment
- cover plate
- pulling force
- force sensor
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- 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.)
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
A kind of unmanned plane propeller dynamic tension monitoring device of the present invention, including equipment cover plate, equipment bay, pulling force sensor and straight-line motion mechanism；Equipment bay is fixed on the position that unmanned plane originally installed airscrew engine；Unmanned plane airscrew engine is fixed on equipment cover plate；Pulling force sensor is arranged between equipment cover plate and equipment bay, and pulling force sensor both ends are fixed with equipment bay and equipment cover plate respectively, and the measurement axis of pulling force sensor and unmanned plane airscrew engine alignment of shafts axis collinear；Straight-line motion mechanism is made up of at least three groups of line slide rails and linear bearing；Linear bearing is fixedly mounted on equipment cover plate, and line slide rail is fixedly mounted on equipment bay, and linear bearing can move along line slide rail, and the measurement diameter parallel of line slide rail and pulling force sensor.The present invention can be directly installed on unmanned plane, realize that the propeller dynamic tension under the conditions of live flying monitors in real time.
Description
Technical field
The present invention relates to engine tensile test technical field, specially a kind of unmanned plane is monitored with propeller dynamic tension
Device
Background technology
At present, it is universal that propeller is still driven as main power form using motor in SUAV field.Cause
This obtains accurate propeller pulling force, UAS is designed particularly important.
At present, the major way for obtaining propeller pulling force is to build test-bed on ground, is obtained by ground experiment mode
Pulling force data of the propeller under different rotating speeds is obtained, but due to live flying condition air speed, sky in ground experiment, can not be simulated
The influence factors such as air tightness, the spiral that the pulling force data for causing to obtain under the conditions of ground experiment can not reflect during live flying
Paddle state.Of course, it is possible to carry out ground experiment in wind-tunnel, the influence of air speed, atmospheric density under the conditions of live flying is simulated, but
For SUAV, this mode is obviously not achievable from the aspect of cost and feasibility.
In addition, the method for propeller pulling force is obtained under the conditions of also having practical flight in the air at present, but current method is all
It is that pulling force data is converted into by way of surveying moment of torsion.Because the spy of efficiency change under different operating modes in itself be present in propeller
Sign, so there is also the problem of scaling results inaccuracy for this method measured indirectly.
Applicant has found during practical study, in the air during practical flight, in order to not influence carrier aircraft in itself
Aeroperformance, the volume of test device itself is unsuitable excessive, so it is relatively good to be measured using small-sized pulling force sensor
Selection, but because pulling force sensor itself can not bear moment of torsion, so there is no disclosed technical scheme at present by small-sized pulling force
Sensor is applied directly in the propeller tension measurement in flight course.
The content of the invention
To solve the problems, such as that prior art is present, the present invention proposes that a kind of unmanned plane is monitored with propeller dynamic tension and filled
Put, can be directly installed on unmanned plane, have Remote Dynamic collection propeller pulling force function, have higher reliability with
Convenience.
The technical scheme is that：
A kind of unmanned plane propeller dynamic tension monitoring device, it is characterised in that：Including equipment cover plate, equipment bottom
Plate, pulling force sensor and straight-line motion mechanism；
The equipment bay is fixed on the position that unmanned plane originally installed airscrew engine；Unmanned plane airscrew engine
It is fixed on equipment cover plate；Pulling force sensor is arranged between equipment cover plate and equipment bay, and pulling force sensor both ends are distinguished
Fixed with equipment bay and equipment cover plate, and the measurement axis of pulling force sensor and the unmanned plane airscrew engine alignment of shafts
Axis collinear；
The straight-line motion mechanism is made up of at least three groups of line slide rails and linear bearing；Linear bearing, which is fixedly mounted on, to be set
On standby cover plate, line slide rail is fixedly mounted on equipment bay, and linear bearing can move along line slide rail, and line slide rail with
The measurement diameter parallel of pulling force sensor.
Further preferred scheme, a kind of unmanned plane propeller dynamic tension monitoring device, it is characterised in that：Institute
State in straight-line motion mechanism, at least three groups of line slide rails and linear bearing are same centered on axis is measured by pulling force sensor
It is uniformly distributed on circumference.
Further preferred scheme, a kind of unmanned plane propeller dynamic tension monitoring device, it is characterised in that：Draw
Force snesor both ends are fixed with equipment bay and equipment cover plate respectively by nut；The installing plate of unmanned plane airscrew engine
Coordinated between equipment cover plate by pad, pacified using bolt through equipment cover plate, pad and unmanned plane airscrew engine
Loading board, unmanned plane airscrew engine is fixed on equipment cover plate.
Further preferred scheme, a kind of unmanned plane propeller dynamic tension monitoring device, it is characterised in that：If
Standby bottom plate and unmanned plane were coordinated between originally installing airscrew engine position by cushion blocking, and equipment bottom is passed through using bolt
Equipment bay is fixed on the opening position that unmanned plane originally installed airscrew engine by plate, cushion blocking.
Beneficial effect
Propeller dynamic tension monitoring device proposed by the present invention can be directly installed on unmanned plane, realized and truly flown
Propeller dynamic tension under the conditions of row monitors in real time；And the apparatus structure is compact, the device thickness in embodiment is only
24mm, the influence of the installation of the device to the aeroperformance of unmanned plane can be ignored, ensure that the flying quality of unmanned plane not by
The influence of experimental provision；Straight-line motion mechanism is formed using multigroup sliding bearing and cylindrical slide rail in the present invention, which is not
Only compact-sized, securely and reliably, and force of sliding friction is small, measurement result is influenceed small；In addition, pass through the machine of moving along a straight line
Structure bears caused reaction torque during propeller rotational, avoids influence of the reaction torque to pulling force sensor, only propeller
Axial tension pass to pulling force sensor.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Brief description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become in the description from combination accompanying drawings below to embodiment
Substantially and it is readily appreciated that, wherein：
Fig. 1 applies the decomposition texture schematic diagram on unmanned plane for the present invention；
Fig. 2 applies the overall structure diagram on unmanned plane for the present invention.
Wherein：1st, propeller；2nd, brushless electric machine；3rd, unmanned plane airscrew engine installing plate；4th, cushion block；5th, device cover
Plate；6th, linear bearing fixing bolt；7th, the fixing nut of sensor first；8th, monetary apparatus pulling force sensor；9th, linear slide bearing；
10th, linear bearing fixing nut；11st, line slide rail；12nd, equipment bay；13rd, the fixing nut of line slide rail first；14th, sensor
Second fixing nut；15th, the fixing nut of line slide rail second；16th, unmanned plane body.
Embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning to end
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and is not considered as limiting the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " are based on orientation shown in the drawings or position relationship, are for only for ease of
Description is of the invention to be described with simplified, rather than the device or element of instruction or hint meaning must be with specific orientation, Yi Te
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
In addition, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or hint relative importance
Or the implicit quantity for indicating indicated technical characteristic.Therefore, define " first ", the feature of " second " can be expressed or
Implicitly include one or more this feature.In the description of the invention, " multiple " are meant that two or more,
Unless otherwise specifically defined.
Present invention is generally directed to be propeller driving SUAV tension measurement problem.
At present, the major way for obtaining propeller pulling force is to build test-bed on ground, is obtained by ground experiment mode
Pulling force data of the propeller under different rotating speeds is obtained, but due to live flying condition air speed, sky in ground experiment, can not be simulated
The influence factors such as air tightness, the spiral that the pulling force data for causing to obtain under the conditions of ground experiment can not reflect during live flying
Paddle state.Of course, it is possible to carry out ground experiment in wind-tunnel, the influence of air speed, atmospheric density under the conditions of live flying is simulated, but
For SUAV, this mode is obviously not achievable from the aspect of cost and feasibility.
In addition, the method for propeller pulling force is obtained under the conditions of also having practical flight in the air at present, but current method is all
It is that pulling force data is converted into by way of surveying moment of torsion.Because the spy of efficiency change under different operating modes in itself be present in propeller
Sign, so there is also the problem of scaling results inaccuracy for this method measured indirectly.
Applicant has found during practical study, in the air during practical flight, in order to not influence carrier aircraft in itself
Aeroperformance, the volume of test device itself is unsuitable excessive, so it is relatively good to be measured using small-sized pulling force sensor
Selection, but because pulling force sensor itself can not bear moment of torsion, so there is no disclosed technical scheme at present by small-sized pulling force
Sensor is applied directly in the propeller tension measurement in flight course.
To solve the above problems, the present invention proposes a kind of unmanned plane propeller dynamic tension monitoring device, Neng Gouzhi
Connect on unmanned plane, there is the function of Remote Dynamic collection propeller pulling force, there is higher reliability and convenience.
As depicted in figs. 1 and 2, unmanned plane propeller dynamic tension monitoring device, including equipment cover plate 5, equipment bottom
Plate 12, monetary apparatus pulling force sensor 8 and straight-line motion mechanism.
The equipment bay 12 is fixed on the position that unmanned plane originally installed airscrew engine, as shown in figure 1, equipment bottom
Plate 12 and unmanned plane were coordinated between originally installing airscrew engine position by cushion blocking, and equipment bay is passed through using bolt
12nd, equipment bay is fixed on the opening position that unmanned plane originally installed airscrew engine by cushion blocking.
Unmanned plane airscrew engine is fixed on equipment cover plate 5, as shown in figure 1, unmanned plane airscrew engine includes
Propeller 1, brushless electric machine 2 and unmanned plane airscrew engine installing plate 3；Set on unmanned plane airscrew engine installing plate 3
There is brushless electric machine 2, brushless electric machine 2 is connected with propeller 1.Lead between unmanned plane airscrew engine installing plate 3 and equipment cover plate 5
Cross pad 4 to coordinate, equipment cover plate 5, pad 4 and unmanned plane airscrew engine installing plate 3 are passed through using bolt, by unmanned plane
Airscrew engine is fixed on equipment cover plate 5.By the design of pad 4 and equipment cover plate 5, such as it is provided with equipment cover plate 5
Multiple standards mounting hole, the unmanned plane airscrew engine installing plate 3 of different dimensional configurations and size can be coordinated, so as to
Adapt to the unmanned plane airscrew engine installing plate 3 of a variety of various configurations and size.
Monetary apparatus pulling force sensor 8 is arranged between equipment cover plate 5 and equipment bay 12, and monetary apparatus pulling force sensor 8
Both ends are fixed with equipment bay 12 and equipment cover plate 5 respectively by nut, and the measurement axis of monetary apparatus pulling force sensor 8 with
Unmanned plane airscrew engine alignment of shafts axis collinear, to guarantee accurate measurement propeller pulling force.
The straight-line motion mechanism is made up of four groups of line slide rails 11 and linear bearing 9；Four groups of line slide rails 11 and straight line
Bearing 9 is uniformly distributed on the same circumference centered on measuring axis by monetary apparatus pulling force sensor 8, and linear bearing 9 fixes peace
On equipment cover plate 5, line slide rail 11 is fixedly mounted on equipment bay 12, and linear bearing 9 can move along line slide rail 11
It is dynamic, and the measurement diameter parallel of line slide rail 11 and monetary apparatus pulling force sensor 8.Propeller is born by straight-line motion mechanism to turn
Caused reaction torque during dynamic, avoids the axial tension transmission of influence of the reaction torque to pulling force sensor, only propeller
To pulling force sensor.
The present invention measures pulling force signal by the monetary apparatus pulling force sensor of inside, and is converted to voltage by measurement signal
For signal output to flight control system, signal is passed back to earth station by flight control system by Data transfer system, and carries out conversion calculating, is obtained
Pulling force real time data, and can be recorded.
Propeller dynamic tension monitoring device proposed by the present invention can be directly installed on unmanned plane, realized and truly flown
Propeller dynamic tension under the conditions of row monitors in real time；And the apparatus structure is compact, the device thickness in embodiment is only
24mm, the influence of the installation of the device to the aeroperformance of unmanned plane can be ignored, ensure that the flying quality of unmanned plane not by
The influence of experimental provision；Straight-line motion mechanism is formed using multigroup sliding bearing and cylindrical slide rail in the present invention, which is not
Only compact-sized, securely and reliably, and force of sliding friction is small, measurement result is influenceed small；In addition, pass through the machine of moving along a straight line
Structure bears caused reaction torque during propeller rotational, avoids influence of the reaction torque to pulling force sensor, only propeller
Axial tension pass to pulling force sensor.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from the principle and objective of the present invention
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (4)
- A kind of 1. unmanned plane propeller dynamic tension monitoring device, it is characterised in that：Including equipment cover plate, equipment bay, drawing Force snesor and straight-line motion mechanism；The equipment bay is fixed on the position that unmanned plane originally installed airscrew engine；Unmanned plane airscrew engine is fixed On equipment cover plate；Pulling force sensor is arranged between equipment cover plate and equipment bay, and pulling force sensor both ends are respectively with setting Standby bottom plate and equipment cover plate are fixed, and the measurement axis of pulling force sensor and unmanned plane airscrew engine alignment of shafts axis Collinearly；The straight-line motion mechanism is made up of at least three groups of line slide rails and linear bearing；Linear bearing is fixedly mounted on device cover On plate, line slide rail is fixedly mounted on equipment bay, and linear bearing can move along line slide rail, and line slide rail and pulling force The measurement diameter parallel of sensor.
- A kind of 2. unmanned plane propeller dynamic tension monitoring device according to claim 1, it is characterised in that：The straight line In motion, at least three groups of line slide rails and linear bearing are on the same circumference centered on measuring axis by pulling force sensor It is uniformly distributed.
- A kind of 3. unmanned plane propeller dynamic tension monitoring device according to claim 2, it is characterised in that：Pull sensing Device both ends are fixed with equipment bay and equipment cover plate respectively by nut；The installing plate and equipment of unmanned plane airscrew engine Coordinated between cover plate by pad, equipment cover plate, pad and unmanned plane airscrew engine installing plate are passed through using bolt, will Unmanned plane airscrew engine is fixed on equipment cover plate.
- A kind of 4. unmanned plane propeller dynamic tension monitoring device according to claim 2, it is characterised in that：Equipment bay Originally installed with unmanned plane and coordinated by cushion blocking between airscrew engine position, using bolt through equipment bay, vibration damping Pad the opening position that equipment bay is fixed on unmanned plane and originally installed airscrew engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710997476.0A CN107806996A (en) | 2017-10-24 | 2017-10-24 | A kind of unmanned plane propeller dynamic tension monitoring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710997476.0A CN107806996A (en) | 2017-10-24 | 2017-10-24 | A kind of unmanned plane propeller dynamic tension monitoring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107806996A true CN107806996A (en) | 2018-03-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710997476.0A Pending CN107806996A (en) | 2017-10-24 | 2017-10-24 | A kind of unmanned plane propeller dynamic tension monitoring device |
Country Status (1)
| Country | Link |
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| CN (1) | CN107806996A (en) |
Cited By (4)
| 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 |
| CN108918136A (en) * | 2018-05-17 | 2018-11-30 | 西安理工大学 | Propeller dynamic tension-torsion measuring device |
| CN114476025A (en) * | 2021-12-20 | 2022-05-13 | 中国航天空气动力技术研究院 | Device and method for monitoring and intelligently controlling propeller pitch angle in real time |
| US20220177128A1 (en) * | 2020-11-03 | 2022-06-09 | Tyto Robotics Inc. | Apparatus and method for fluid-screw system property measurement |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104483053A (en) * | 2014-12-25 | 2015-04-01 | 深圳市博尔创意文化发展有限公司 | Torque measuring device of small engine |
| CN205066989U (en) * | 2015-11-03 | 2016-03-02 | 上海圣尧智能科技有限公司 | Screw pulling force and torque -measuring apparatus and system thereof |
| CN105923169A (en) * | 2016-07-06 | 2016-09-07 | 西安交通大学 | Testing platform and testing method for power supply system of gasoline-electric hybrid unmanned aerial vehicle |
| CN105947233A (en) * | 2016-06-22 | 2016-09-21 | 北方信息控制集团有限公司 | Multi-rotor power testing device and method |
| CN106143949A (en) * | 2016-07-06 | 2016-11-23 | 西安交通大学 | A kind of unmanned vehicle testboard and method of testing thereof |
| WO2017098122A1 (en) * | 2015-12-08 | 2017-06-15 | Safran Aircraft Engines | Aircraft propulsion assembly provided with steps allowing an operator to reach the top of same |
-
2017
- 2017-10-24 CN CN201710997476.0A patent/CN107806996A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104483053A (en) * | 2014-12-25 | 2015-04-01 | 深圳市博尔创意文化发展有限公司 | Torque measuring device of small engine |
| CN205066989U (en) * | 2015-11-03 | 2016-03-02 | 上海圣尧智能科技有限公司 | Screw pulling force and torque -measuring apparatus and system thereof |
| WO2017098122A1 (en) * | 2015-12-08 | 2017-06-15 | Safran Aircraft Engines | Aircraft propulsion assembly provided with steps allowing an operator to reach the top of same |
| CN105947233A (en) * | 2016-06-22 | 2016-09-21 | 北方信息控制集团有限公司 | Multi-rotor power testing device and method |
| CN105923169A (en) * | 2016-07-06 | 2016-09-07 | 西安交通大学 | Testing platform and testing method for power supply system of gasoline-electric hybrid unmanned aerial vehicle |
| CN106143949A (en) * | 2016-07-06 | 2016-11-23 | 西安交通大学 | A kind of unmanned vehicle testboard and method of testing thereof |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108918136A (en) * | 2018-05-17 | 2018-11-30 | 西安理工大学 | Propeller dynamic tension-torsion measuring device |
| CN108918136B (en) * | 2018-05-17 | 2020-04-21 | 西安理工大学 | Propeller dynamic tension and torsion measuring device |
| 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 |
| US20220177128A1 (en) * | 2020-11-03 | 2022-06-09 | Tyto Robotics Inc. | Apparatus and method for fluid-screw system property measurement |
| CN114476025A (en) * | 2021-12-20 | 2022-05-13 | 中国航天空气动力技术研究院 | Device and method for monitoring and intelligently controlling propeller pitch angle in real time |
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Application publication date: 20180316 |