CN108593169A - Rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device and torsion-testing method and lift test method - Google Patents
Rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device and torsion-testing method and lift test method Download PDFInfo
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- CN108593169A CN108593169A CN201810355506.2A CN201810355506A CN108593169A CN 108593169 A CN108593169 A CN 108593169A CN 201810355506 A CN201810355506 A CN 201810355506A CN 108593169 A CN108593169 A CN 108593169A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
Rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device and torsion-testing method and lift test method, belong to single rotor air vehicle technique field, the present invention is to solve existing rotor system aerodynamic characteristic test device to be difficult to realize the small lift of Mars unmanned plane rotor system, low torque index request, problem poor for applicability, measurement error is big.The present invention includes motion module, torque measurement module and lift measurement module；Motion module lower face is connect with torque measurement module upper end, and motion module is placed in the upper surface of lift measurement module balancing bar one end with torque measurement module；Motion module generates torque and lift for generating rotary motion；Torque measurement module is used to measure the torque of motion module generation；Lift measurement module is used to measure the lift of motion module generation.The present invention is used for the unmanned plane single rotor system of mars exploration.
Description
Technical field
The present invention relates to a kind of aerodynamic characteristic test devices of Mars unmanned plane single rotor system, belong to single rotor unmanned plane
Technical field.
Background technology
The presence for seeking the Evolution, origin of life, water source of near-earth planet is all domestic and international scientist all the time
Carry out one of the focus that survey of deep space is probed into.Mars has similar physical size with the earth, equally has thin air
Layer has same four seasons alternating and day-night change, and there are convenient temperature, thus mars exploration becomes survey of deep space and appoints
The important goal of business.Currently, the main means of mars exploration include transmitting satellite, Mars Rover etc., however these means by
To the limitation of detection accuracy and efficiency.It develops a kind of for assisting Mars Rover to complete the Mars unmanned plane of mars exploration task
Become the new way of current mars exploration.Compared to unmanned planes such as fixed-wing formula, floating balloons, rotary wind type Mars unmanned plane has
The advantages such as high flight speed, extensive investigative range, VTOL, accuracy energy, become the research weight of Mars unmanned plane
Point.However, martian atmosphere pressure, temperature are far below earth environment, unique low reynolds number, High Mach number flight environment of vehicle are to the mankind
The rotor system for developing unmanned plane proposes huge challenge.Current rotor characteristic test device is revolved mainly for earth unmanned plane
Wing system, it is difficult to meet the small lift of Mars unmanned plane rotor, the index request of low torque, develop a kind of rotary wind type Mars nobody
Machine single rotor mechanics of system characteristic test device is significant to China's future survey of deep space.
Existing aerodynamic characteristic test device is only used for the aerodynamic characteristic assessment of earth unmanned plane rotor system, poor for applicability
And measurement error is big, it is difficult to realize that the small lift of rotor system, low torque measure under Mars environment.
Invention content
The invention aims to solve existing rotor system aerodynamic characteristic test device to be difficult to realize Mars unmanned plane
Small lift, the low torque index request of rotor system, problem poor for applicability, measurement error is big provide a kind of rotary wind type fire
Star unmanned plane single rotor system gas dynamic characteristic test device and torsion-testing method and lift test method.
Rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device of the present invention, it include motion module,
Torque measurement module and lift measurement module；
Motion module lower face is connect with torque measurement module upper end, and motion module is placed in lift survey with torque measurement module
Measure the upper surface of module balancing bar one end；
Motion module generates torque and lift for generating rotary motion；
Torque measurement module is used to measure the torque of motion module generation；
Lift measurement module is used to measure the lift of motion module generation.
Torsion-testing side of the present invention based on rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device
The detailed process of method, torsion-testing method is：
Step 9-1, external high-speed brushless motor drives test rotor high speed rotation, and generates clockwise torque；
Step 9-2, the torque that step 9-1 is generated passes sequentially through No.1 adapting rod and No. two adapting rods are transferred to grating
Ruler generates small rotation on upper grating scale；
Step 9-3, variable angle is generated between upper grating scale and lower grating scale；
Step 9-4, the variable angle that step 9-3 is generated causes the pressure change of laser emitter and laser receiver；
Step 9-5, the torque value of test rotor is obtained according to the pressure change that step 9-4 is generated.
Lift test side of the present invention based on rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device
The detailed process of method, lift test method is：
Step 10-1, the motion module of balancing pole one end is placed in by increasing the mass balance of clump weight in clump weight pallet
With torque measurement module；
Step 10-2, external high-speed brushless motor drives test rotor high speed rotation, and generates lift straight up；When
When balancing pole is in equilbrium position, pressure-strain piece is contacted with balancing pole not to be squeezed；
Step 10-3, the lift that step 10-2 is generated passes sequentially through motion module and torque measurement module is transferred to balance
Bar；
Step 10-4, the lift of balancing pole one end is converted into the pressure of balancing pole other end pressure-strain piece, at this point, pressure
Power is acted between foil gauge and balancing pole；
Step 10-5, the value of lift of test rotor is obtained by the variation of pressure-strain piece pressure.
The present invention can solve nothing of the existing rotor system aerodynamic characteristic test device mainly for earth atmosphere environment
Man-machine rotor system, it is difficult to realize small lift, the low torque index request of Mars unmanned plane rotor system, poor for applicability, measurement
Rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test system of the present invention is placed in large size by the big problem of error
In the low vacuum gaseous environment of vacuum tank, motion module is directly connected to torque measurement module, motion module and torque measurement mould
Block is arranged on the balancing pole of lift measurement device, and when rotor system moves, torque square measurement module directly measures rotor system
The low torque of system, mechanical meaurement device balances the quality of rotor system by clump weight, and uses cloth by " seesaw " structure
The pressure-strain piece for being placed in the other side measures the small lift of rotor system.Aerodynamic characteristic test device can be directed to rotor system
The important indicators such as airfoil structure, blade construction, the blade geometric shape of system are assessed, with the higher scope of application and flexibly
Property.The present invention is used for the rotation of the deep space probes such as the rotary wind type unmanned plane of survey of deep space, survey of deep space tilt-rotor unmanned plane
The assessment of wing system aerodynamic characteristic is tested.
Advantages of the present invention：
1, design is scientific and reasonable for structure of the invention, and motion module and the torque measurement module of rotor system are directly connected to,
The accurate torque value of rotor system can be directly obtained in rotor system motion process；Lift measurement module uses " seesaw " formula knot
Structure, rotor system, in the side of lift measurement module balancing bar, pass through matching for the balancing pole other side with torque measurement module arrangement
Pouring weight balances the quality of rotor system and torque measurement module, is risen to realize that foil gauge generates rotor system under working condition
The small lift measurement of power.Test device meets the measurement accuracy requirement to single rotor aerodynamic characteristic, measurement method novelty, error
It is low.
2, working media of the invention is carbon dioxide, the work using large-scale vacuum tank as aerodynamic characteristic test device
Environment, it is reliable using process safety, it is pollution-free, it is suitable for popularity and uses.
3, test object of the invention have can special replaceability, for a variety of rotor index requests, including to single rotor system
The assessment of the airfoil structures such as the high reynolds number aerofoil profile of system, low Reynolds number airfoil；It can be to single rotor blade quantity, blade construction, several
The assessment of the important indicators such as what shape.
4, the present invention by sample test of many times it is found that the present invention is within 1-104Pa environment of low vacuum is to span 1.0m
Single rotor system the 0-6000r/min ranges of speeds carry out aerodynamic characteristic test.
5, the present invention by sample test of many times it is found that the situation that the present invention stablizes in residing gaseous environment pressure index
Under, lift measurement error is less than 0.01N, and torque measurement error is less than 0.1mNm.
Description of the drawings
Fig. 1 is the structural representation of rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device of the present invention
Figure；
Fig. 2 is motion module of the present invention, the positional structure schematic diagram of torque measurement module and lift measurement module；
Fig. 3 is the structural schematic diagram of motion module of the present invention；
Fig. 4 is the sectional view of torque measurement module of the present invention；
Fig. 5 is the structural schematic diagram of torque measurement module of the present invention；
Fig. 6 is the positional structure schematic diagram of support pedestal and balancing pole of the present invention；
Fig. 7 is the part-structure schematic diagram of lift measurement module of the present invention.
Specific implementation mode
Specific implementation mode one：Illustrate present embodiment with reference to Fig. 1 and Fig. 2, rotary wind type fire described in present embodiment
Star unmanned plane single rotor system gas dynamic characteristic test device, it includes motion module 1, torque measurement module 2 and lift measurement mould
Block 3；
1 lower face of motion module is connect with 2 upper end of torque measurement module, and motion module 1 is placed in liter with torque measurement module 2
The upper surface of 3 balancing pole one end of power measurement module；
Motion module 1 generates torque and lift for generating rotary motion；
Torque measurement module 2 is used to measure the torque of the generation of motion module 1；
Lift measurement module 3 is used to measure the lift of the generation of motion module 1.
Specific implementation mode two：Illustrate that present embodiment, present embodiment make into one embodiment one with reference to Fig. 3
Step explanation, motion module 1 include test rotor 1-1, external high-speed brushless motor 1-2, Hall element 1-3 and No.1 adapting rod 1-
4；
The output shaft driving test rotor 1-1 rotations of external high-speed brushless motor 1-2, external high-speed brushless motor 1-2's
Shell is connect by flange in the bottom with the upper ends No.1 adapting rod 1-4, Hall element 1-3 and the external bottoms high-speed brushless motor 1-2
Flanged joint, Hall element 1-3 is adjacent with external high-speed brushless motor 1-2 and does not contact, and Hall element 1-3 is used for external height
The rotating speed of fast brushless motor 1-2 carries out closed-loop control.
In present embodiment, external high-speed brushless motor 1-2 is directly connected to test rotor 1-1, using Hall element 1-3
Self feed back control is carried out to external high-speed brushless motor 1-2 rotating speeds, quickly and accurately realizes that the high rotary speed movement of rotor system is wanted
It asks.
Specific implementation mode three：Illustrate present embodiment with reference to Fig. 4 and Fig. 5, present embodiment is to embodiment two
It is described further, torque measurement module 2 includes two groups of ball bearing 2-1, laser emitter 2-2, upper grating scale 2-3, lower light
Grid ruler 2-4, laser receiver 2-5, No. two adapting rod 2-6, closure head 2-7, shell 2-8, lower grating seat 2-9 and Housing bottom cover
2-10；
No. two adapting rod 2-6 are T-shape, and the upper end of No. two adapting rod 2-6 is connect with the lower end of No.1 adapting rod 1-4, two
The lower end of number adapting rod 2-6 is connect with upper grating scale 2-3, and closure head 2-7, shell 2-8 and Housing bottom cover 2-10 pass through screw
It is sequentially connected, lower grating scale 2-4, lower grating seat 2-9 and Housing bottom cover 2-10 are sequentially connected, and lower grating seat 2-9 is located at shell
The center of bottom cover 2-10, upper grating scale 2-3 are coaxially oppositely arranged with lower grating scale 2-4, the inner circle difference of two groups of ball bearing 2-1
Coordinate with No. two adapting rod 2-6, the bearing top circle of two groups of ball bearing 2-1 coordinates with shell 2-8 respectively, laser emitter 2-2
It is connect with shell 2-8 inner walls, laser receiver 2-5 is connect with Housing bottom cover 2-10, laser emitter 2-2 and laser receiver 2-
5 are coaxially oppositely arranged.
In present embodiment, the inner circle of two groups of ball bearing 2-1 coordinates with No. two adapting rod 2-6 respectively, two groups of ball axis
The bearing top circle for holding 2-1 coordinates with shell 2-8 respectively, realizes the rotation of the slight resistance of No. two adapting rod 2-6, also, realize
By the gravity unloading of motion module 1 to shell 2-8.
Specific implementation mode four：Illustrate present embodiment with reference to Fig. 4 and Fig. 5, present embodiment is to embodiment three
It is described further, is connected using thin connecting rod between upper grating scale 2-3 and lower grating scale 2-4, motion module 1 is by the variation of torque
It is transferred to upper grating scale 2-3 by No. two adapting rod 2-6, the change in torque of upper grating scale 2-3 causes carefully to connect torsion of bar, carefully connect
Torsion of bar drives lower grating scale 2-4 torsions, between upper grating scale 2-3 and lower grating scale 2-4 the change of angle change commanders motion module 1
Torque be converted to angle change, and change in torque is amplified.
In present embodiment, thin connecting rod is superfine connecting rod.
Specific implementation mode five：Present embodiment is described further embodiment four, and thin connecting rod is cylinder.
Specific implementation mode six：Present embodiment is described further embodiment five, and thin connecting rod is cylinder, is carefully connected
Bar can replace the different connecting rod of diameter according to the torque of different range.
Specific implementation mode seven：Illustrate present embodiment with reference to Fig. 6 and Fig. 7, present embodiment is to embodiment three
It is described further, lift measurement module 3 includes support pedestal 3-1, balancing pole 3-2, clump weight pallet 3-3, pressure-strain piece
3-4 and dial indicator holder 3-5；
The bottom end of Housing bottom cover 2-10 and one end of balancing pole 3-2 are connected by screw, support pedestal 3-1 and balancing pole 3-
2 connections, and support pedestal 3-1 is placed in the bottom among balancing pole 3-2, pressure-strain piece 3-4 is contacted with balancing pole 3-2, and is pressed
Stress-strain piece 3-4 is placed in the other end of balancing pole 3-2, and dial indicator holder 3-5 is connect with pressure-strain piece 3-4, clump weight pallet 3-3
It is placed between pressure-strain piece 3-4 and support pedestal 3-1, and clump weight pallet 3-3 is connect with the top of balancing pole 3-2.
In present embodiment, support pedestal 3-1 and balancing pole 3-2 cooperations make lift measurement module 3 form " seesaw " knot
Structure.
In present embodiment, Fig. 2, Fig. 6 and Fig. 7 collectively constitute Fig. 1.
Specific implementation mode eight：Present embodiment is described further embodiment seven, support pedestal 3-1 and balancing pole
3-2 is connected by bearing group.
Specific implementation mode nine：Present embodiment is described further embodiment three or four, torsion-testing method
Detailed process is：
Step 9-1, external high-speed brushless motor 1-2 drives test rotor 1-1 high speed rotations, and generates clockwise torsion
Square；
Step 9-2, the torque that step 9-1 is generated passes sequentially through No.1 adapting rod 1-4 and No. two adapting rod 2-6 are transferred to
Grating scale 2-3 generates small rotation on upper grating scale 2-3；
Step 9-3, variable angle is generated between upper grating scale 2-3 and lower grating scale 2-4；
Step 9-4, the variable angle that step 9-3 is generated causes the pressure of laser emitter 2-2 and laser receiver 2-5 to become
Change；
Step 9-5, the torque value of test rotor 1-1 is obtained according to the pressure change that step 9-4 is generated.
Specific implementation mode ten：Present embodiment is described further embodiment seven or eight, lift test method
Detailed process is：
Step 10-1, the fortune of the one end balancing pole 3-2 is placed in by increasing the mass balance of clump weight in clump weight pallet 3-3
Dynamic model block 1 and torque measurement module 2；
Step 10-2, external high-speed brushless motor 1-2 drives test rotor 1-1 high speed rotations, and generates straight up
Lift；When balancing pole 3-2 is in equilbrium position, pressure-strain piece 3-4 is contacted with balancing pole 3-2 and is not squeezed；
Step 10-3, the lift that step 10-2 is generated passes sequentially through motion module 1 and torque measurement module 2 is transferred to balance
Bar 3-2；
Step 10-4, the lift of the one end balancing pole 3-2 is converted into the pressure of balancing pole 3-2 other end pressure-strain pieces 3-4,
At this point, acting power between pressure-strain piece 3-4 and balancing pole 3-2；
Step 10-5, the value of lift of test rotor 1-1 is obtained by the variation of pressure-strain piece 3-4 pressure.
In present embodiment, when balancing pole 3-2 is in equilbrium position, the axis inside balancing pole 3-2 and support pedestal 3-1
A group cooperation is held, ensures that the rotor lifts of balancing pole 3-2 during the test cause small sway not rubbed by support pedestal 3-1
It influences.
In the present invention, test rotor 1-1, external high-speed brushless motor 1-2, No.1 adapting rod 1-4, No. two adapting rod 2-6,
Upper grating scale 2-3 and lower grating scale 2-4 are coaxially arranged, by the variable angle between upper grating scale 2-3 and lower grating scale 2-4,
Coordinate the pressure change of laser emitter 2-2 and laser receiver 2-5, measures what test rotor 1-1 was generated in the operating condition
Torque.Accurately and rapidly directly measure the low torque value of rotor system.
In the present invention, when testing rotor 1-1 stoppings, passing through the clump weight being arranged on clump weight pallet 3-3, use
The balancing pole 3-2 balance exercises module 1 of " seesaw " form and the quality of torque measurement module 2, at this time pressure-strain piece 3-4 with
Balancing pole 3-2 contacts do not squeeze；When testing rotor 1-1 work, rotor system is generated using pressure-strain piece 3-4 small liter
Power measures.Quickly and accurately measure the small value of lift of rotor system.
The present invention the course of work be：
1, torsion-testing process is as follows：Under the driving effect of voltage, external high-speed brushless motor 1-2 high speed rotations simultaneously will
Rotary motion is transferred to test rotor 1-1.It tests rotor 1-1 high speed rotations and generates clockwise torque, and torque is passed
No.1 adapting rod 1-4, No.1 adapting rod 1-4 is handed to connect with No. two adapting rod 2-6 and transfer a torque to No. two adapting rod 2-
6.No. two adapting rod 2-6, two groups of ball bearing 2-1, shell 2-8 coordinate successively, are located at two by two groups of ball bearing 2-1 balances
The pressure of number adapting rod 2-6, and realized between No. two adapting rod 2-6 and shell 2-8 by two groups of ball bearing 2-1 without rubbing back
Turn (negligible).It is connected by superfine connecting rod between upper grating scale 2-3 and lower grating scale 2-4.No. two adapting rod 2-6's
Torque is transferred to the connecting rod between grating scale 2-3 and lower grating scale 2-4 and causes even torsion of bar, generates certain torsion
Angle.The torsion angle of connecting rod is transferred to grating scale 2-3, causes the angular deviation between grating scale 2-3 and lower grating scale 2-4,
Angular deviation will cause the pressure change of laser emitter 2-2 and laser receiver 2-5, eventually by laser emitter 2-2 with
The pressure change of laser receiver 2-5 can get the torque value of test rotor 1-1.
2, lift test process is as follows：Under the driving effect of voltage, external high-speed brushless motor 1-2 high speed rotations simultaneously will
Rotary motion is transferred to test rotor 1-1.The production of rotor 1-1 high speed rotations is tested along value of lift straight up.Lift passes through fortune
Dynamic model block 1, torque measurement module 2 are transferred to the balancing pole 3-2 of lift measurement module 3.Balancing pole 3-2 and support pedestal 3-1 groups
At " seesaw " structure, will be converted to positioned at the other sides balancing pole 3-2 pressure-strain piece 3- positioned at the lift of the sides balancing pole 3-2
4 pressure.The value of lift of test rotor 1-1 is obtained by the variation of pressure-strain piece 3-4 pressure.
Claims (10)
1. rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device, which is characterized in that it includes motion module
(1), torque measurement module (2) and lift measurement module (3)；
Motion module (1) lower face is connect with torque measurement module (2) upper end, and motion module (1) is set with torque measurement module (2)
Upper surface in lift measurement module (3) balancing pole one end；
Motion module (1) generates torque and lift for generating rotary motion；
Torque measurement module (2) is used to measure the torque of motion module (1) generation；
Lift measurement module (3) is used to measure the lift of motion module (1) generation.
2. rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device according to claim 1, feature exist
In motion module (1) includes test rotor (1-1), external high-speed brushless motor (1-2), Hall element (1-3) and No.1 switching
Bar (1-4)；
The output shaft driving test rotor (1-1) of external high-speed brushless motor (1-2) rotates, external high-speed brushless motor (1-2)
Shell connect with the upper end No.1 adapting rod (1-4) by flange in the bottom, Hall element (1-3) and external high-speed brushless motor
(1-2) flange in the bottom connects, and Hall element (1-3) is adjacent with external high-speed brushless motor (1-2) and does not contact, Hall element
(1-3) is used to carry out closed-loop control to the rotating speed of external high-speed brushless motor (1-2).
3. rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device according to claim 2, feature exist
In torque measurement module (2) includes two groups of ball bearings (2-1), laser emitter (2-2), upper grating scale (2-3), lower grating
Ruler (2-4), laser receiver (2-5), No. two adapting rods (2-6), closure head (2-7), shell (2-8), lower grating seat (2-9)
With Housing bottom cover (2-10)；
No. two adapting rods (2-6) are T-shape, and the upper end of No. two adapting rods (2-6) is connect with the lower end of No.1 adapting rod (1-4),
The lower end of No. two adapting rods (2-6) is connect with upper grating scale (2-3), closure head (2-7), shell (2-8) and Housing bottom cover (2-
10) it being sequentially connected by screw, lower grating scale (2-4), lower grating seat (2-9) and Housing bottom cover (2-10) are sequentially connected, and under
Grating seat (2-9) is located at the center of Housing bottom cover (2-10), upper grating scale (2-3) with lower grating scale (2-4) is coaxial is oppositely arranged,
The inner circle of two groups of ball bearings (2-1) coordinates with No. two adapting rods (2-6) respectively, the bearing top circle of two groups of ball bearings (2-1)
Coordinate respectively with shell (2-8), laser emitter (2-2) is connect with shell (2-8) inner wall, laser receiver (2-5) and shell
Bottom cover (2-10) connects, laser emitter (2-2) with laser receiver (2-5) is coaxial is oppositely arranged.
4. rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device according to claim 3, feature exist
In being connect using thin connecting rod between upper grating scale (2-3) and lower grating scale (2-4), motion module (1) passes through the variation of torque
No. two adapting rods (2-6) are transferred to grating scale (2-3), and the change in torque of upper grating scale (2-3) causes carefully to connect torsion of bar, carefully
The torsion of connecting rod drives lower grating scale (2-4) torsion, between upper grating scale (2-3) and lower grating scale (2-4) change of angle change commanders
The torque of motion module (1) is converted to angle change, and change in torque is amplified.
5. rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device according to claim 4, feature exist
In thin connecting rod is cylinder.
6. rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device according to claim 5, feature exist
In thin connecting rod can replace the different connecting rod of diameter according to the torque of different range.
7. rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device according to claim 3, feature exist
In lift measurement module (3) includes support pedestal (3-1), balancing pole (3-2), clump weight pallet (3-3), pressure-strain piece (3-
And dial indicator holder (3-5) 4)；
The bottom end of Housing bottom cover (2-10) and one end of balancing pole (3-2) are connected by screw, support pedestal (3-1) and balancing pole
(3-2) is connected, and support pedestal (3-1) is placed in the intermediate bottom of balancing pole (3-2), pressure-strain piece (3-4) and balancing pole (3-
2) it contacts, and pressure-strain piece (3-4) is placed in the other end of balancing pole (3-2), dial indicator holder (3-5) and pressure-strain piece (3-
4) it connects, clump weight pallet (3-3) is placed between pressure-strain piece (3-4) and support pedestal (3-1), and clump weight pallet (3-
3) it is connect with the top of balancing pole (3-2).
8. rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device according to claim 7, feature exist
In support pedestal (3-1) is connected with balancing pole (3-2) by bearing group.
9. the torque measuring based on the rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device of claim 3 or 4
Method for testing, which is characterized in that the detailed process of torsion-testing method is：
Step 9-1, external high-speed brushless motor (1-2) drives test rotor (1-1) high speed rotation, and generates clockwise torsion
Square；
Step 9-2, the torque that step 9-1 is generated passes sequentially through No.1 adapting rod (1-4) and No. two adapting rods (2-6) are transferred to
Grating scale (2-3) generates small rotation on upper grating scale (2-3)；
Step 9-3, variable angle is generated between upper grating scale (2-3) and lower grating scale (2-4)；
Step 9-4, the variable angle that step 9-3 is generated causes the pressure of laser emitter (2-2) and laser receiver (2-5) to become
Change；
Step 9-5, the torque value of test rotor (1-1) is obtained according to the pressure change that step 9-4 is generated.
10. the lift based on the rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device of claim 7 or 8 is surveyed
Method for testing, which is characterized in that the detailed process of lift test method is：
Step 10-1, the fortune of the one end balancing pole (3-2) is placed in by increasing the mass balance of clump weight in clump weight pallet (3-3)
Dynamic model block (1) and torque measurement module (2)；
Step 10-2, external high-speed brushless motor (1-2) drives test rotor (1-1) high speed rotation, and generates straight up
Lift；When balancing pole (3-2) is in equilbrium position, pressure-strain piece (3-4) is contacted with balancing pole (3-2) and is not squeezed；
Step 10-3, the lift that step 10-2 is generated passes sequentially through motion module (1) and torque measurement module (2) is transferred to balance
Bar (3-2)；
Step 10-4, the lift of the one end balancing pole (3-2) is converted into the pressure of balancing pole (3-2) other end pressure-strain piece (3-4)
Power, at this point, acting power between pressure-strain piece (3-4) and balancing pole (3-2)；
Step 10-5, the value of lift of test rotor (1-1) is obtained by the variation of pressure-strain piece (3-4) pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810355506.2A CN108593169B (en) | 2018-04-19 | 2018-04-19 | Aerodynamic characteristic testing device, torque testing method and lift force testing method for single rotor system of rotary-wing Mars unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810355506.2A CN108593169B (en) | 2018-04-19 | 2018-04-19 | Aerodynamic characteristic testing device, torque testing method and lift force testing method for single rotor system of rotary-wing Mars unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108593169A true CN108593169A (en) | 2018-09-28 |
| CN108593169B CN108593169B (en) | 2021-05-07 |
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| CN110562481A (en) * | 2018-06-06 | 2019-12-13 | 长城汽车股份有限公司 | Aircraft power testing arrangement |
| CN110562483A (en) * | 2019-09-24 | 2019-12-13 | 哈尔滨工业大学 | lift-drag characteristic measuring device for vertical Mars aircraft coaxial rotor system |
| CN110562484A (en) * | 2019-09-24 | 2019-12-13 | 哈尔滨工业大学 | Hovering characteristic testing device for testing single-shaft rotor system of Mars aircraft |
| 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 |
| CN111114857A (en) * | 2019-09-24 | 2020-05-08 | 哈尔滨工业大学 | Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft |
| CN111114856A (en) * | 2019-09-24 | 2020-05-08 | 哈尔滨工业大学 | Pneumatic characteristic measuring device with automatically adjustable interval between upper rotor wing and lower rotor wing of Mars aircraft |
| CN112193435A (en) * | 2020-10-12 | 2021-01-08 | 中国科学院沈阳自动化研究所 | Unmanned helicopter propeller matching test system |
| CN113295316A (en) * | 2021-07-06 | 2021-08-24 | 零重力南京飞机工业有限公司 | Working method of multi-rotor-wing unmanned aerial vehicle power system measurement test bed |
| CN115027697A (en) * | 2022-07-12 | 2022-09-09 | 广东汇天航空航天科技有限公司 | Rotor system testing device, system and method |
| CN116242575A (en) * | 2023-05-08 | 2023-06-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual flight test device of low-speed wind tunnel |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110562481A (en) * | 2018-06-06 | 2019-12-13 | 长城汽车股份有限公司 | Aircraft power testing arrangement |
| CN110562483A (en) * | 2019-09-24 | 2019-12-13 | 哈尔滨工业大学 | lift-drag characteristic measuring device for vertical Mars aircraft coaxial rotor system |
| CN110562484A (en) * | 2019-09-24 | 2019-12-13 | 哈尔滨工业大学 | Hovering characteristic testing device for testing single-shaft rotor system of Mars aircraft |
| CN111114857A (en) * | 2019-09-24 | 2020-05-08 | 哈尔滨工业大学 | Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft |
| CN111114856A (en) * | 2019-09-24 | 2020-05-08 | 哈尔滨工业大学 | Pneumatic characteristic measuring device with automatically adjustable interval between upper rotor wing and lower rotor wing of Mars aircraft |
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| CN111114857B (en) * | 2019-09-24 | 2022-10-28 | 哈尔滨工业大学 | Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft |
| 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 |
| CN112193435A (en) * | 2020-10-12 | 2021-01-08 | 中国科学院沈阳自动化研究所 | Unmanned helicopter propeller matching test system |
| CN113295316A (en) * | 2021-07-06 | 2021-08-24 | 零重力南京飞机工业有限公司 | Working method of multi-rotor-wing unmanned aerial vehicle power system measurement test bed |
| CN115027697A (en) * | 2022-07-12 | 2022-09-09 | 广东汇天航空航天科技有限公司 | Rotor system testing device, system and method |
| CN116242575A (en) * | 2023-05-08 | 2023-06-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual flight test device of low-speed wind tunnel |
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