CN208036658U - Multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device - Google Patents
Multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device Download PDFInfo
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- CN208036658U CN208036658U CN201820190414.9U CN201820190414U CN208036658U CN 208036658 U CN208036658 U CN 208036658U CN 201820190414 U CN201820190414 U CN 201820190414U CN 208036658 U CN208036658 U CN 208036658U
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- rotor
- hoistable platform
- rotor system
- elevator
- ground effect
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Abstract
The utility model discloses a kind of multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment devices, including：Main support, hoistable platform, lifting motor, retarder, transmission turning device, hoistable platform elevator, rotor system elevator, rotor system X-direction shifter, X-direction translation bar, six COMPONENT BALANCE of rotor, six COMPONENT BALANCE of body；The lifting motor is by the retarder and transmission turning device driving hoistable platform elevator on main support, to drive hoistable platform to move up and down；Rotor system X-direction shifter is mounted on hoistable platform both sides；Rotor system elevator is mounted on X-direction translation bar and removable along Z-direction；Six COMPONENT BALANCE of rotor/body is separately mounted to the position between rotor system elevator/X-direction translation bar and rotor system/body.The utility model have many advantages, such as it is versatile, it is easy to operate, applicable various sizes of more rotors vert aircraft aerodynamic interference and ground effect testing research.
Description
Technical field
The utility model belongs to aerodynamics experimental technique field, refers specifically to vert flight vehicle aerodynamic for a kind of more rotors
Interference and ground effect integrated experiment device.
Background technology
When more rotors vert aircraft winged state before hovering flight state and low speed, between wing/rotor/fuselage
Aerodynamic interference is particularly acute.Aerodynamic interference between wing/rotor/fuselage can vert to more rotors each lift member of aircraft
It has a huge impact.In flight near the ground, rotor wake forms complicated flow field after being interfered by ground, also can be to revolving more
Vert each lift member of aircraft of the wing has a huge impact.
The interaction relationship flown before hovering flight and low speed between stage rotor wake and wing, fuselage, ground is complicated,
Aerodynamic interference and ground effect problem between wing/rotor/fuselage can't be studied by theoretical calculation well at present, it must
It must be studied by aerodynamic interference and ground effect problem of the method for experiment between wing/rotor/fuselage.
In addition, the aerodynamic interference between the wing/rotor/fuselage for the aircraft that verted to more rotors by test method and ground
Face effect problem is studied, to more rotors vert aircraft aerodynamic arrangement, power arrangement design etc. work have
Significance.The testing stand of flight vehicle aerodynamic interference and ground effect of verting not yet in relation to more rotors domestic at present.It is external big
Be also to vert the size of aircraft according to more rotors of itself research and research emphasis designs the experiment for meeting oneself requirement more
Platform.
In view of this, it is really necessary to propose a kind of multi-rotor aerocraft aerodynamic interference and ground effect compbined test dress
It sets.
Invention content
Above-mentioned the deficiencies in the prior art are directed to, the purpose of this utility model is to provide a kind of multi-rotor aerocraft is pneumatic
Interference and ground effect integrated experiment device, to solve that wing/rotation can not be studied well by theoretical calculation in the prior art
The problem of aerodynamic interference and ground effect between the wing/fuselage.
In order to achieve the above objectives, the technical solution adopted in the utility model is as follows：
A kind of multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device of the utility model, including：Main branch
Frame, hoistable platform, lifting motor, retarder, transmission turning device, hoistable platform elevator, rotor system elevator, rotor system
X-direction shifter, X-direction translation bar, six COMPONENT BALANCE of six COMPONENT BALANCE of rotor and body, wherein：
The lifting motor, retarder, transmission turning device and hoistable platform elevator are mounted on main support, lifting motor
It drives hoistable platform elevator, hoistable platform elevator drives to connect hoistable platform by retarder and transmission turning device, changes
The position of hoistable platform in the Y direction；
Rotor system X-direction shifter is mounted on hoistable platform both sides, changes X-direction and translates bar in the position of X-direction；
Rotor system elevator is movably mounted to along Z-direction on X-direction translation bar, is fixedly connected with aircraft rotor system
System, change of flight device rotor system is in the Y direction and the position of Z-direction；
Six COMPONENT BALANCE of multiple rotors is separately mounted between multiple rotor system elevators and aircraft rotor system
Position, for measuring power and torque in rotor system suffered by each rotor；Two six COMPONENT BALANCEs of body are mounted on two X-directions
The position between bar and aircraft body is translated, for measuring power and torque suffered by body.
Preferably, coordinated by lockable sliding equipment between the hoistable platform and X-direction translation bar, keep X-direction flat
Bar is moved to change and lock in the position of X-direction.
Preferably, the lockable sliding equipment includes the circular protrusions being set on hoistable platform and is translated set on X-direction
Groove on bar.
Preferably, the experimental rig is only installed under aircraft rotor system situation, changes X, Y and Z between each rotor
The relative position in direction studies the aerodynamic interference between rotor/rotor.
Preferably, after experimental rig installation aircraft body, change of flight device rotor system and aircraft body it
Between Y-direction relative position, study rotor/body between aerodynamic interference.
Preferably, the experimental rig simulates the liftoff height of multi-rotor aerocraft by the Y-direction position of change hoistable platform
Degree variation, influence of the exploratory flight device terrain clearance to multi-rotor aerocraft rotor and load born by engine body.
The beneficial effects of the utility model：
The multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device of the utility model have versatile, behaviour
Make the advantages that easy, applicable various sizes of more rotors vert aircraft aerodynamic interference and ground effect testing research.Very
To aerodynamic interference and the ground effect testing research for being applicable to tiltrotor aircraft.It verts aircraft to studying more rotors
The great significance for design of aerodynamic arrangement and power arrangement.
Description of the drawings
Fig. 1 is the first structure schematic diagram of the utility model integrated experiment device.
Fig. 2 is the second structural schematic diagram of the utility model integrated experiment device.
Fig. 3 translates the schematic diagram that bar is connected with hoistable platform for rotor system elevator, X-direction in example.
Specific implementation mode
For the ease of the understanding of those skilled in the art, the utility model is made with reference to embodiment and attached drawing further
Explanation, the content that embodiment refers to not is restriction to the utility model.
Shown in Fig. 3, a kind of multi-rotor aerocraft aerodynamic interference and ground effect the synthesis examination of the utility model
Experiment device selects quadrotor in example, including：Main support 1, hoistable platform 2, lifting motor 3, retarder 4, transmission turn
To device 5, hoistable platform elevator 6, rotor system elevator 7, rotor system X-direction shifter 8, X-direction translation bar 9, rotor
Six COMPONENT BALANCEs 10, six COMPONENT BALANCE 11 of body, wherein：
In example, main support 1 is built into frame structure by square steel tube.The lifting motor 3, retarder 4, transmission turning device
5 and hoistable platform elevator 6 be mounted on main support 1 on, hoistable platform elevator 6 be mounted on four, 1 top of main support angle, pass through
Axis 4 hoistable platform elevators 6 of series connection, ensure that 2 four points of hoistable platform rise or simultaneously decline simultaneously；Lifting motor 3 is logical
It crosses retarder 4 and transmission turning device 5 drives hoistable platform elevator 6, hoistable platform elevator 6 to be drivingly connected hoistable platform 2, change
Become the position of hoistable platform 2 in the Y direction；
Rotor system X-direction shifter 8 is mounted on 2 both sides of hoistable platform, changes X-direction and translates bar 9 in the position of X-direction
It sets；Wherein, coordinated by lockable sliding equipment between the hoistable platform 2 and X-direction translation bar 9, X-direction is made to translate bar 9
It changes and locks in the position of X-direction.
In this example, the sliding equipment includes the circular protrusions being set on hoistable platform 2 and translates bar 9 set on X-direction
On groove.In other examples, circular protrusions can be also set on X-direction translation bar, and groove is set on hoistable platform.
Rotor system elevator 7 is movably mounted to along Z-direction on X-direction translation bar 9, and rotor system elevator 7 is fixed
Connect aircraft rotor system 13, change of flight device rotor system 13 is in the Y direction and the position of Z-direction；X-direction translates on bar 9
If there are two the symmetrical sliding slot along Z-direction, rotor system elevator 7 can in being slided along Z-direction in the sliding slot of the Z-direction,
To which change of flight device rotor system 13 is in the position of Z-direction.
Four six COMPONENT BALANCEs 10 of rotor be separately mounted to four rotor system elevators 7 and aircraft rotor system 13 it
Between position, for measuring power and torque in rotor system suffered by each rotor；Two six COMPONENT BALANCEs 11 of body are mounted on two
Position between a X-direction translation bar 9 and aircraft body 12, for measuring power and torque suffered by body.Due to aircraft
Body 12 and aircraft rotor system 13 are completely disengaged, and therefore, six COMPONENT BALANCE 10 of rotor and six COMPONENT BALANCE 11 of body measure
Range is non-interference.
Wherein, the pilot system is only installed under aircraft rotor system situation, changes X, Y and Z between four rotors
The relative position in direction studies the aerodynamic interference between rotor/rotor.
Wherein, after the pilot system installation aircraft body, between change of flight device rotor system and aircraft body
Y-direction relative position, study rotor/body between aerodynamic interference.
When carrying out aerodynamic interference experiment, hoistable platform 2 is fixed on a higher position by hoistable platform elevator 6, only
Aircraft rotor system 13 is installed, the relative position of X, Y and Z-direction between four rotors can be changed, is recorded without aircraft machine
Power and torque in the case of body suffered by aircraft rotor system.To data carry out processing and analysis can be obtained rotor/rotor it
Between aerodynamic interference.After aircraft body is installed, the Y between rotor system and body can be changed by rotor system elevator 7
The relative position in direction can record power and torque suffered by rotor system and body.Being handled data and being analyzed can obtain
Interference between rotor/body.
When carrying out ground effect test, aircraft body 12 and aircraft rotor system 13 are installed, aircraft machine is regulated
The relative position of body 12 and aircraft rotor system 13 simulates quadrotor and verts aircraft.Existed by changing hoistable platform 2
The position of Y-direction can simulate quadrotor and vert the variation of aircraft terrain clearance, can record power suffered by rotor system and body and
Torque.Processing carried out to data and analysis can be obtained aircraft terrain clearance to quadrotor vert aircraft rotor and body by
The influence of power.
There are many utility model concrete application approach, and the above is only the preferred embodiment of the utility model, should
It points out, for those skilled in the art, without departing from the principle of this utility model, can also make
Go out several improvement, these improvement also should be regarded as the scope of protection of the utility model.
Claims (6)
1. a kind of multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device, which is characterized in that including：Main support
（1）, hoistable platform（2）, lifting motor（3）, retarder（4）, transmission turning device（5）, hoistable platform elevator（6）, rotor system
System elevator（7）, rotor system X-direction shifter（8）, X-direction translate bar（9）, six COMPONENT BALANCE of rotor（10）With body six
COMPONENT BALANCE（11）, wherein
The lifting motor（3）, retarder（4）, transmission turning device（5）With hoistable platform elevator（6）Mounted on main support（1）
On, lifting motor（3）Pass through retarder（4）With transmission turning device（5）Drive hoistable platform elevator（6）, hoistable platform lifting
Machine（6）It is drivingly connected hoistable platform（2）, change hoistable platform（2）Position in the Y direction；
Rotor system X-direction shifter（8）Mounted on hoistable platform（2）Both sides change X-direction and translate bar（9）In X-direction
Position；
Rotor system elevator（7）It is movably mounted to X-direction along Z-direction and translates bar（9）On, it is fixedly connected with aircraft rotor
System（13）, change of flight device rotor system（13）In the Y direction and the position of Z-direction；
Six COMPONENT BALANCE of multiple rotors（10）It is separately mounted to multiple rotor system elevators（7）With aircraft rotor system（13）
Between position, measure power and torque suffered by each rotor in rotor system；Two six COMPONENT BALANCEs of body（11）Mounted on two
A X-direction translates bar（9）And aircraft body（12）Between position, measure body suffered by power and torque.
2. multi-rotor aerocraft aerodynamic interference according to claim 1 and ground effect integrated experiment device, feature exist
In the hoistable platform（2）Bar is translated with X-direction（9）Between coordinated by lockable sliding equipment, make X-direction translate bar（9）
It changes and locks in the position of X-direction.
3. multi-rotor aerocraft aerodynamic interference according to claim 2 and ground effect integrated experiment device, feature exist
In the lockable sliding equipment includes to be set to hoistable platform（2）On circular protrusions and set on X-direction translate bar（9）On
Groove.
4. multi-rotor aerocraft aerodynamic interference according to claim 1 and ground effect integrated experiment device, feature exist
In the experimental rig is only installed under aircraft rotor system situation, and the opposite position of X, Y and Z-direction between each rotor are changed
It sets.
5. multi-rotor aerocraft aerodynamic interference according to claim 1 and ground effect integrated experiment device, feature exist
In, after the experimental rig installation aircraft body, the phase of the Y-direction between change of flight device rotor system and aircraft body
To position.
6. multi-rotor aerocraft aerodynamic interference according to claim 1 and ground effect integrated experiment device, feature exist
In the experimental rig passes through the Y-direction position of change hoistable platform, simulation multi-rotor aerocraft terrain clearance variation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820190414.9U CN208036658U (en) | 2018-02-05 | 2018-02-05 | Multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820190414.9U CN208036658U (en) | 2018-02-05 | 2018-02-05 | Multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device |
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| Publication Number | Publication Date |
|---|---|
| CN208036658U true CN208036658U (en) | 2018-11-02 |
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| CN201820190414.9U Expired - Fee Related CN208036658U (en) | 2018-02-05 | 2018-02-05 | Multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109932123A (en) * | 2019-03-22 | 2019-06-25 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Propeller single-blade leaf determination of six components of foree device |
-
2018
- 2018-02-05 CN CN201820190414.9U patent/CN208036658U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109932123A (en) * | 2019-03-22 | 2019-06-25 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Propeller single-blade leaf determination of six components of foree device |
| CN109932123B (en) * | 2019-03-22 | 2020-10-16 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Propeller single-blade six-component measuring device |
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|---|---|---|---|
| GR01 | Patent grant | ||
| 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: 20181102 Termination date: 20220205 |