CN108146656A - Multifunctional rotary wing helicopter test experiments rack - Google Patents
Multifunctional rotary wing helicopter test experiments rack Download PDFInfo
- Publication number
- CN108146656A CN108146656A CN201711472537.8A CN201711472537A CN108146656A CN 108146656 A CN108146656 A CN 108146656A CN 201711472537 A CN201711472537 A CN 201711472537A CN 108146656 A CN108146656 A CN 108146656A
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- test
- pulling force
- clamping plate
- test block
- rotary wing
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Classifications
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- 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
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention provides a kind of multifunctional rotary wing helicopter test experiments rack, including pedestal, counter-jib, debugger, weight frame and runing rest, debugger includes main shaft, installing plate, test device and adjustment and installation seat, installing plate, test device passes sequentially through main shaft with adjustment and installation seat and connects, adjustment and installation seat is hinged with counter-jib, test device includes test block and test device ontology, test block is arranged on the top edge of test device, test block is connected with installing plate bottom surface, test block passes through pulling force sensor connecting test device body respectively both horizontally and vertically.The present invention can be used for testing and building each degree of freedom torque state model of heligyro, and simple in structure, measuring and calculation is convenient and efficient.
Description
Technical field
The invention belongs to Helicopter Technology fields, and in particular to a kind of multifunctional rotary wing helicopter test experiments rack.
Background technology
Heligyro test experiments rack is mainly used for research ＆ development in flight test, production test and the repacking of heligyro
In test.Heligyro especially rotor wing unmanned aerial vehicle is real using the test of indoor heligyro before sizing manufacture or repacking
Testing rack can be tested and be analyzed to stability of every flight parameter of rotor wing unmanned aerial vehicle etc. and parameter etc..Heligyro
Test experiments rack is using lever construction, it can be achieved that the unmanned plane during flying parameter testing of ground safety, reduces unmanned plane outfield
Test the frequency and cost.
In unmanned plane during flying parameter, the grasp of the torque situation of each degree of freedom of rotor wing unmanned aerial vehicle is very important.Profit
Each degree of freedom torque of rotor wing unmanned aerial vehicle is tested with heligyro test experiments rack and builds each degree of freedom torque
Model can monitor motion state, movement tendency and load born by engine body situation of each degree of freedom of determining rotor wing unmanned aerial vehicle etc..
A kind of multi-rotor unmanned aerial vehicle test platform of patent (day for announcing 2017.09.05, notification number CN206466190U) is open
A kind of multi-rotor unmanned aerial vehicle test platform including pedestal, main swivel mount, cross bar one, cross bar two, end seat one, end seat two and is surveyed
Platform is tried, the main swivel mount is connect with pedestal by bearing, and the cross bar one is parallel with cross bar two, and makes cross bar one and cross bar
Two middles are hinged with main swivel mount, and one end of the cross bar one is hinged with end seat one, and other end is hinged with end seat two, described
One end of cross bar two is hinged with end seat one, and other end is hinged with end seat two, and the test platform is connect with end seat one, the end
One upper end of seat is equipped with supporting rod, and two upper end of end seat is equipped with counterweight sinker, and the counterweight sinker upper end is equipped with screw, institute
It states test platform to be made of swivel mount, rotating frame and unmanned plane fixed platform, the swivel mount is U-typed structure.The practicality is new
Type is used to implement the pitching of unmanned plane and roll test.But the utility model can not each degree of freedom torque shape of intelligence test calculating
State.
Therefore be badly in need of it is a kind of simple in structure, can intelligently, more work(of quickly and easily each degree of freedom torque state of measuring and calculation
It can heligyro test experiments rack.
Invention content
In order to solve the above technical problem, the present invention provides a kind of multifunctional rotary wing helicopter test experiments rack, the knots
Structure can be used for testing and building each degree of freedom torque state model of heligyro, and simple in structure, measuring and calculation is convenient and efficient.
The present invention provides following technical solutions：
A kind of multifunctional rotary wing helicopter test experiments rack, including pedestal, counter-jib, debugger, weight frame and rotation
Stent, runing rest are connected with pedestal by bearing, and debugger, runing rest and weight frame are hinged on counter-jib successively, rotation
Turn stent mounted on counter-jib centre position, debugger and weight frame mounted on the both ends of counter-jib, debugger includes main shaft, peace
Loading board, test device and adjustment and installation seat, installing plate, test device pass sequentially through main shaft with adjustment and installation seat and connect, debugging peace
Dress seat is hinged with counter-jib, and test device includes test block and test device ontology, and test block is arranged on the top of test device
Edge, test block are connected with installing plate bottom surface, and test block is connected both horizontally and vertically by pulling force sensor respectively
Connect test device ontology.
Preferably, the quantity of test block is 3, and test block is distributed in equilateral triangle, and test device ontology includes right up and down
The first panel and second panel of title, test block are in first panel in same level, and each test block is hung down mutually by 2
Directly and between test block and main shaft the symmetrical pulling force sensor connection first panel of line, each test block are set vertically by 1
The pulling force sensor connection second panel put.
Preferably, signal processing apparatus, controller, radio transmitting device and remote computer are further included, pulling force sensor,
Signal processing apparatus and radio transmitting device are electrically connected with the controller, and controller is electromechanical by radio transmitting device and remote computation
The pulling force real-time tele-communication number monitored is transferred to signal processing apparatus, signal processing by connection, controller control pulling force sensor
Device is filtered pulling force real-time tele-communication number amplification and analog-to-digital conversion forms pulling force digital signal, controller control wireless transmission
Device transmits pulling force digital signal to remote computer, and remote computer is based on pulling force digital signal and carries out integrated treatment analysis
Obtain each degree of freedom torque state outcome of aircraft.
Preferably, installing plate is equipped with several installation through-holes, is set vertically by several between first panel and second panel
The pillar connection put.
Preferably, first panel edge is equipped with several openings, and second panel edge is equipped with several through-holes, pulling force sensor one
Connecting test block is held, the pulling force sensor other end is equipped with idler wheel, and idler wheel is hinged in opening and through-hole.
Preferably, weight frame includes box body and clamping plate, and clamping plate is L-shaped, and clamping plate has 2, and clamping plate is hinged with counter-jib, box body
Clamping plate upper surface is arranged on, the bottom surface and side of box body are connected with clamping plate, and clamping plate bottom is equipped with universal rolling wheel.
Preferably, adjustment and installation seat includes upper clamp plate, left clamp, right clamping plate and lower clamp plate, left clamp and right clamping plate or so
It symmetrically sets up, left clamp is connected with the upper and lower ends of right clamping plate by upper clamp plate with lower clamp plate, and main shaft passes through upper clamp plate and left
Clamping plate and the clamping of right clamping plate, lower clamp plate lower section are equipped with universal rolling wheel.
Preferably, several idler wheels are equipped with below pedestal, several deep floors are equipped between pedestal and bearing.
The beneficial effects of the invention are as follows：
1st, the configuration of the present invention is simple, it is easy for installation.
2nd, testboard of the present invention is set there are three test point, this 3 points are distributed in equilateral triangle, and each test point is orthogonal
Pulling force sensor is respectively mounted on three directions for measuring all directions deformation.It can be calculated by the change in displacement for measuring three directions
Go out power in each direction, the resultant force and resultant moment that can be calculated on entire debugger are summarized by the stress of three points.So as to
According to corresponding test event, on the direction that power and torque are decomposed to wanted test moment, can thus obtain on aircraft
Various torques.Test point facilitates calculating each using pulling force sensor is respectively mounted on equilateral triangle distribution and orthogonal three directions
The Impact direction of pulling force sensor and between influence relationship, convenient for building the moment model of each degree of freedom.
3rd, setting signal processing unit of the present invention, controller, radio transmitting device and remote computer, available for pulling force
The filtered amplification of pulling force real-time tele-communication number and analog-to-digital conversion that sensor obtains form pulling force digital signal and pass through remote computation
Machine integrated treatment is analyzed to obtain each degree of freedom torque state outcome of aircraft.
4th, installing plate of the present invention is equipped with several installation through-holes, facilitates installation each component of unmanned plane.Testboard first panel
It is connected between second panel by several pillars being vertically arranged, consolidates testboard durable.
5th, weight frame of the present invention includes box body and clamping plate, and box body is arranged on clamping plate upper surface, and clamping plate bottom is equipped with universal rolling
Wheel.By placing the weight of different weight in box body, debugger is placed in highest point, facilitates test.Box body places article side
Just, universal rolling wheel can assist box body to carry out mobile transport on ground.
6th, adjustment and installation seat of the present invention include upper clamp plate, left clamp, right clamping plate and lower clamp plate, main shaft pass through upper clamp plate and by
Left clamp and the clamping of right clamping plate, facilitate fixed main shaft.Be equipped with below lower clamp plate universal rolling wheel can subtest platform carried out on ground
Mobile transport.
7th, several deep floors are equipped between pedestal and bearing of the present invention, it is multi-functional to increase the rigidity of the structure of pedestal
Heligyro test experiments rack disclosure satisfy that the use of middle-size and small-size rotor wing unmanned aerial vehicle.
Description of the drawings
Attached drawing is used to provide further understanding of the present invention, and a part for constitution instruction, the reality with the present invention
Example is applied together for explaining the present invention, is not construed as limiting the invention.In the accompanying drawings：
Fig. 1 is overall structure diagram of the present invention；
Fig. 2 is testing bench structure schematic diagram of the present invention；
Fig. 3 is test device structure diagram of the present invention；
Fig. 4 is principal functional structure connection diagram of the present invention.
In figure label for：1st, pedestal；2nd, counter-jib；3rd, debugger；31st, main shaft；32nd, installing plate；33rd, test device；
331st, test block；332nd, test device ontology；333rd, pulling force sensor；334th, pillar；34th, adjustment and installation seat；4th, weight frame；
41st, box body；42nd, clamping plate；5th, runing rest；6th, rotor wing unmanned aerial vehicle；7th, floor；8th, signal processing apparatus；9th, controller；10th, nothing
Line transmitting device；11st, remote computer.
Specific embodiment
The preferred embodiment of the present invention is described below in conjunction with the accompanying drawings.
As shown in Figure 1, Figure 2, Figure 3 shows, a kind of multifunctional rotary wing helicopter test experiments rack, including pedestal 1, counter-jib 2,
Debugger 3, weight frame 4 and runing rest 5, runing rest 5 are connected with pedestal 1 by bearing, debugger 3, runing rest 5 and again
Rack 4 is hinged on successively on counter-jib 2, and runing rest 5 is mounted on 2 centre position of counter-jib, and debugger 3 and weight frame 4 are installed
At the both ends of counter-jib 2, debugger 3 include main shaft 31, installing plate 32, test device 33 and adjustment and installation seat 34, installing plate 32,
Test device 33 and adjustment and installation seat 34 pass sequentially through main shaft 31 and connect, and adjustment and installation seat 34 is hinged with counter-jib 2, test device
33 include test block 331 and test device ontology 332, and test block 331 is arranged on the top edge of test device 33, test block
331 are connected with 32 bottom surface of installing plate, and test block 331 is connected both horizontally and vertically by pulling force sensor 333 respectively
Connect test device ontology 332.
Specifically, installing plate 32 is equipped with several installation through-holes.Installation through-hole can be used for installing rotor wing unmanned aerial vehicle 6.
Specifically, the quantity of test block 331 is 3, test block 331 is distributed in equilateral triangle, and test device ontology 332 wraps
First panel and second panel symmetrical above and below are included, test block 331 is in first panel in same level, each test block
331 is orthogonal and the symmetrical pulling force sensor 333 of line connects the first face between test block 331 and main shaft 31 by 2
Plate, each test block 331 connect second panel by 1 pulling force sensor being vertically arranged 333.Specifically, first panel and
It is connected between two panels by several pillars 334 being vertically arranged.
Specifically, first panel edge is equipped with several openings, second panel edge is equipped with several through-holes, pulling force sensor
333 one end connecting test blocks 331,333 other end of pulling force sensor are equipped with idler wheel, and idler wheel is hinged in opening and through-hole.
Specifically, weight frame 4 includes box body 41 and clamping plate 42, clamping plate 42 is L-shaped, and clamping plate 42 has 2, and clamping plate 42 is with balancing
Arm 2 is hinged, and box body 41 is arranged on 42 upper surface of clamping plate, and the bottom surface and side of box body 41 are connected with clamping plate 42,42 bottom of clamping plate
Equipped with universal rolling wheel.
Specifically, adjustment and installation seat 34 includes upper clamp plate, left clamp, right clamping plate and lower clamp plate, left clamp and right clamping plate are left
The right side symmetrically is set up, and left clamp is connected with the upper and lower ends of right clamping plate by upper clamp plate with lower clamp plate, main shaft 31 across upper clamp plate and
It is clamped by left clamp and right clamping plate, universal rolling wheel is equipped with below lower clamp plate.
Specifically, 1 lower section of pedestal is equipped with several idler wheels, several deep floors 7 are equipped between pedestal 1 and bearing.
As shown in figure 4, further including signal processing apparatus 8, controller 9, radio transmitting device 10 and remote computer 11, draw
Force snesor 333, signal processing apparatus 8 and radio transmitting device 10 are electrically connected with controller 9, and controller 9 passes through wireless transmission
Device 10 is electrically connected with remote computer 11, and controller 9 controls pulling force sensor 333 to pass the pulling force real-time tele-communication number monitored
Signal processing apparatus 8 is defeated by, signal processing apparatus 8 is filtered pulling force real-time tele-communication number amplification and analog-to-digital conversion forms pulling force
Digital signal, controller 9 control radio transmitting device 10 to transmit pulling force digital signal to remote computer 11, remote computer
11 carry out integrated treatment based on pulling force digital signal analyzes to obtain each degree of freedom torque state outcome of rotor wing unmanned aerial vehicle 6.
When carrying out test job, three test points in equilateral triangle distribution, each test point is in three orthogonal directions
On be respectively mounted pulling force sensor for measuring all directions deflection.Power, which is acted on pulling force sensor, to be deformed making pulling force
Weak current variation is generated in sensor, forms pulling force real-time tele-communication number.It, will be micro- by the filter and amplification of signal processing apparatus 8
Weak curent change is converted into electric signal；Electric signal is converted into pulling force digital signal, then by wireless by digital-to-analogue conversion again
Transmitting device 10 is sent on remote computer 11, and carrying out calculating comprehensive analysis using the software of remote computer 11 obtains rotor
Each degree of freedom torque state outcome of unmanned plane 6, and build moment model.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, although with reference to aforementioned reality
Example is applied the present invention is described in detail, it for those skilled in the art, still can be to aforementioned each implementation
Technical solution recorded in example modifies or carries out equivalent replacement to which part technical characteristic.All essences in the present invention
With within principle, any modification, equivalent replacement, improvement and so on should all be included in the protection scope of the present invention god.
Claims (8)
1. a kind of multifunctional rotary wing helicopter test experiments rack, which is characterized in that including pedestal, counter-jib, debugger, weight
Frame and runing rest, the runing rest are connected with the pedestal by bearing, the debugger, the runing rest and described
Weight frame is hinged on successively on the counter-jib, and the runing rest is mounted on the counter-jib centre position, the debugger
The both ends of the counter-jib are mounted on the weight frame, the debugger includes main shaft, installing plate, test device and debugging peace
Seat is filled, the installing plate, the test device pass sequentially through the main shaft with the adjustment and installation seat and connect, the adjustment and installation
Seat is hinged with the counter-jib, and the test device includes test block and test device ontology, and the test block is arranged on described
The top edge of test device, the test block are connected with the installing plate bottom surface, and the test block is in the horizontal direction and vertical
Nogata by pulling force sensor to connecting the test device ontology respectively.
2. multifunctional rotary wing helicopter test experiments rack according to claim 1, which is characterized in that the test block
Quantity is 3, and the test block is distributed in equilateral triangle, and the test device ontology includes first panel symmetrical above and below and the
Two panels, the test block and the first panel are in same level, each test block by 2 it is orthogonal,
And symmetrically the pulling force sensor connects the first panel, each survey to line between the test block and the main shaft
Test block connects the second panel by 1 pulling force sensor being vertically arranged.
3. multifunctional rotary wing helicopter test experiments rack according to claim 1, which is characterized in that further include at signal
Manage device, controller, radio transmitting device and remote computer, the pulling force sensor, the signal processing apparatus and described
Radio transmitting device is electrically connected with the controller, and the controller passes through the radio transmitting device and the remote computer
Electrical connection, the controller control the pulling force sensor that the pulling force real-time tele-communication number monitored is transferred to the signal processing
Device, the signal processing apparatus is filtered pulling force real-time tele-communication number amplification and analog-to-digital conversion forms pulling force digital signal,
The controller controls the radio transmitting device to transmit pulling force digital signal to remote computer, the remote computer base
Integrated treatment is carried out in pulling force digital signal to analyze to obtain each degree of freedom torque state outcome of aircraft.
4. multifunctional rotary wing helicopter test experiments rack according to claim 3, which is characterized in that on the installing plate
Equipped with several installation through-holes, connected between the first panel and the second panel by several pillars being vertically arranged.
5. multifunctional rotary wing helicopter test experiments rack according to claim 2, which is characterized in that the first panel
Edge is equipped with several openings, and the second panel edge is equipped with several through-holes, and described pulling force sensor one end connects the test
Block, the pulling force sensor other end are equipped with idler wheel, and the idler wheel is hinged in the opening and the through-hole.
6. multifunctional rotary wing helicopter test experiments rack according to claim 1, which is characterized in that the weight frame packet
Box body and clamping plate are included, the clamping plate is L-shaped, and the clamping plate there are 2, and the clamping plate is hinged with the counter-jib, and the box body is set
It puts in the clamping plate upper surface, the bottom surface and side of the box body are connected with the clamping plate, and the clamping plate bottom is equipped with universal
Idler wheel.
7. multifunctional rotary wing helicopter test experiments rack according to claim 1, which is characterized in that the adjustment and installation
Seat includes upper clamp plate, left clamp, right clamping plate and lower clamp plate, the left clamp and right clamping plate is symmetrical sets up, the left side
Clamping plate is connected with the upper and lower ends of the right clamping plate by the upper clamp plate with the lower clamp plate, and the main shaft passes through the upper folder
It plate and is clamped by the left clamp and the right clamping plate, universal rolling wheel is equipped with below the lower clamp plate.
8. multifunctional rotary wing helicopter test experiments rack according to claim 1, which is characterized in that below the pedestal
Equipped with several idler wheels, several deep floors are equipped between the pedestal and the bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711472537.8A CN108146656A (en) | 2017-12-29 | 2017-12-29 | Multifunctional rotary wing helicopter test experiments rack |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711472537.8A CN108146656A (en) | 2017-12-29 | 2017-12-29 | Multifunctional rotary wing helicopter test experiments rack |
Publications (1)
| Publication Number | Publication Date |
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| CN108146656A true CN108146656A (en) | 2018-06-12 |
Family
ID=62463885
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711472537.8A Pending CN108146656A (en) | 2017-12-29 | 2017-12-29 | Multifunctional rotary wing helicopter test experiments rack |
Country Status (1)
| Country | Link |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910080A (en) * | 2018-06-26 | 2018-11-30 | 中国直升机设计研究所 | A kind of helicopter tail rotor aerodynamic loading environmental simulation test device |
| CN109466795A (en) * | 2018-12-04 | 2019-03-15 | 湖南山河科技股份有限公司 | A kind of unmanned helicopter automatically testing platform |
| CN110641731A (en) * | 2019-09-29 | 2020-01-03 | 江苏科技大学 | Rotor motor lift force measuring device for multi-rotor unmanned aerial vehicle |
| CN116754174A (en) * | 2023-08-16 | 2023-09-15 | 中国空气动力研究与发展中心低速空气动力研究所 | Layout conversion method for thrust-tension type tail rotor of helicopter wind tunnel test |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2493917Y (en) * | 2001-08-28 | 2002-05-29 | 中国科学院合肥智能机械研究所 | Five-dimension force force-measuring platform |
| CN102180270A (en) * | 2011-03-10 | 2011-09-14 | 北京航空航天大学 | Microminiature rotorcraft experiment platform and application thereof |
| RU2011133319A (en) * | 2011-08-10 | 2013-02-20 | Государственное научное учреждение "Центральный научно-исследовательский и опытно-конструкторский институт робототехники и технической кибернетики" (ГНУ ЦНИИ РТК) | ADAPTIVE THREE-POINT GRABBING DEVICE |
| CN104990719A (en) * | 2015-07-08 | 2015-10-21 | 国网山东省电力公司电力科学研究院 | Unmanned aerial vehicle test bed system for inspection and detection |
| CN105182770A (en) * | 2015-08-27 | 2015-12-23 | 北京控制工程研究所 | System and method for spacecraft semi-physical simulation experiment based on rotor craft |
| WO2015198093A1 (en) * | 2014-06-24 | 2015-12-30 | Peter Ireland | Efficiency improvements for flow control body and system shocks |
| CN205952340U (en) * | 2016-07-11 | 2017-02-15 | 河北工业大学 | Rotor unmanned aerial vehicle testboard |
| CN207826599U (en) * | 2017-12-29 | 2018-09-07 | 江苏方阔航空科技有限公司 | Multifunctional rotary wing helicopter test experiments rack |
-
2017
- 2017-12-29 CN CN201711472537.8A patent/CN108146656A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2493917Y (en) * | 2001-08-28 | 2002-05-29 | 中国科学院合肥智能机械研究所 | Five-dimension force force-measuring platform |
| CN102180270A (en) * | 2011-03-10 | 2011-09-14 | 北京航空航天大学 | Microminiature rotorcraft experiment platform and application thereof |
| RU2011133319A (en) * | 2011-08-10 | 2013-02-20 | Государственное научное учреждение "Центральный научно-исследовательский и опытно-конструкторский институт робототехники и технической кибернетики" (ГНУ ЦНИИ РТК) | ADAPTIVE THREE-POINT GRABBING DEVICE |
| WO2015198093A1 (en) * | 2014-06-24 | 2015-12-30 | Peter Ireland | Efficiency improvements for flow control body and system shocks |
| CN104990719A (en) * | 2015-07-08 | 2015-10-21 | 国网山东省电力公司电力科学研究院 | Unmanned aerial vehicle test bed system for inspection and detection |
| CN105182770A (en) * | 2015-08-27 | 2015-12-23 | 北京控制工程研究所 | System and method for spacecraft semi-physical simulation experiment based on rotor craft |
| CN205952340U (en) * | 2016-07-11 | 2017-02-15 | 河北工业大学 | Rotor unmanned aerial vehicle testboard |
| CN207826599U (en) * | 2017-12-29 | 2018-09-07 | 江苏方阔航空科技有限公司 | Multifunctional rotary wing helicopter test experiments rack |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910080A (en) * | 2018-06-26 | 2018-11-30 | 中国直升机设计研究所 | A kind of helicopter tail rotor aerodynamic loading environmental simulation test device |
| CN108910080B (en) * | 2018-06-26 | 2021-11-02 | 中国直升机设计研究所 | Helicopter tail rotor pneumatic load environment simulation test device |
| CN109466795A (en) * | 2018-12-04 | 2019-03-15 | 湖南山河科技股份有限公司 | A kind of unmanned helicopter automatically testing platform |
| CN109466795B (en) * | 2018-12-04 | 2022-03-29 | 湖南山河科技股份有限公司 | Automatic test platform of unmanned helicopter |
| CN110641731A (en) * | 2019-09-29 | 2020-01-03 | 江苏科技大学 | Rotor motor lift force measuring device for multi-rotor unmanned aerial vehicle |
| CN110641731B (en) * | 2019-09-29 | 2022-11-15 | 江苏科技大学 | Rotor motor lift force measuring device for multi-rotor unmanned aerial vehicle |
| CN116754174A (en) * | 2023-08-16 | 2023-09-15 | 中国空气动力研究与发展中心低速空气动力研究所 | Layout conversion method for thrust-tension type tail rotor of helicopter wind tunnel test |
| CN116754174B (en) * | 2023-08-16 | 2023-10-31 | 中国空气动力研究与发展中心低速空气动力研究所 | Layout conversion method for thrust-tension type tail rotor of helicopter wind tunnel test |
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