CN115140323A - Pneumatic characteristic testing device of tension torque decoupling type single rotor system - Google Patents
Pneumatic characteristic testing device of tension torque decoupling type single rotor system Download PDFInfo
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- CN115140323A CN115140323A CN202210728353.8A CN202210728353A CN115140323A CN 115140323 A CN115140323 A CN 115140323A CN 202210728353 A CN202210728353 A CN 202210728353A CN 115140323 A CN115140323 A CN 115140323A
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- 238000012360 testing method Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 claims description 9
- 238000013461 design Methods 0.000 description 5
- 238000005259 measurement Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011056 performance test Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012216 screening Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
- B64G2007/005—Space simulation vacuum chambers
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Abstract
The invention discloses a tension torque decoupling type single-rotor system aerodynamic characteristic testing device, which belongs to the field of testing of single-rotor aerodynamic characteristics of a Mars helicopter and comprises a torque testing module and a thrust testing module, wherein in the torque testing module, a motor rotor rotates to drive a rotor to rotate to generate torque, a motor stator generates torque which is equal to the torque in magnitude and opposite in direction, and the torque is transmitted to a torque sensor through a lower stepped shaft; in the thrust test module, the thrust that the rotor rotated the production passes through on motor, bearing, a supporting cylinder, the force sensor upper plate transmit three force sensor, has solved current aerodynamic characteristic testing arrangement and has been difficult to deal with little thrust, the low moment of torsion of mars helicopter rotor when hovering and produce too big error and the precision problem of crossing excessively.
Description
Technical Field
The invention relates to the technical field of testing of aerodynamic characteristics of single rotors of Mars helicopters, in particular to a device for testing aerodynamic characteristics of a tension torque decoupling type single rotor system.
Background
The Mars atmosphere is thin and the density is less than 1% of the earth, but the thin atmosphere provides possibility for the existence of the Mars helicopter. The human beings have a plurality of ways of exploring the mars, and the mars car is mostly used, but if the mars car is matched with the mars helicopter to explore the mars, a better effect can be obtained, and the mars helicopter can explore a wider area and can guide the advancing direction of the mars car to avoid obstacles. The characteristics of low Reynolds number and high Mach number are provided on the mars, which provides huge challenge for the design of the mars unmanned aerial vehicle.
The scheme of patent number "CN207133000U" in the prior publication solves the problems that the torque, the tension and other information of a propeller-motor are measured, so that the dynamic characteristics of a propeller-motor system are conveniently researched, the propeller-motor screening matching work is guaranteed, the using environment is the earth atmosphere, the overall pneumatic performance test of a Mars helicopter cannot be met, the torque and thrust test error is large and the precision is low for a Mars helicopter rotor, the stress condition of a fuselage of the Mars helicopter when the propeller is electrically driven to rotate cannot be accurately tested, and the pneumatic performance test of the Mars helicopter rotor cannot be met.
Disclosure of Invention
In order to solve the defects mentioned in the background technology, the invention aims to provide a tension torque decoupling type single-rotor system aerodynamic characteristic testing device, which overcomes the defects of large error and low precision of the existing ground aerodynamic characteristic testing device, and provides a tension torque decoupling type single-rotor Mars helicopter aerodynamic characteristic testing device which has high precision and small error and can respectively test the thrust generated by a rotor under the two conditions of upward and downward directions, and a torque and thrust testing method thereof
The purpose of the invention can be realized by the following technical scheme:
the invention discloses a tension torque decoupling type single-rotor system aerodynamic characteristic testing device which comprises a blade, a blade clamp-motor connecting flange, a motor, a sleeve, a bearing, a stepped shaft, a torque sensor upper end clamping ring, a torque sensor lower end clamping ring, a supporting cylinder mounting plate, a tension sensor, a mounting base plate and a base, wherein the blade is arranged on the lower end of the torque sensor;
the paddle is fixedly connected to the paddle clamp and rotates around the rotation center to generate thrust and moment;
the torque sensor measures the torque generated when the paddle rotates;
the tension sensor measures the thrust generated when the blade rotates.
The invention relates to a torque testing method of a tension torque decoupling type single-rotor system aerodynamic characteristic testing device, which comprises the following specific processes:
the invention can solve the problems that the existing rotor wing pneumatic testing device is only designed for an earth rotor wing, has large error and low precision for the starry helicopter rotor wing starting test, and can only test the thrust in one direction.
The invention has the beneficial effects that:
according to the invention, the thrust ball bearing is arranged between the support cylinder and the torque sensor to ensure the accuracy of torque measurement, and most of gravity is counteracted through the thrust ball bearing, so that the problems that the existing aerodynamic characteristic testing device is difficult to deal with overlarge error and over-low precision caused by small thrust and low torque when the Mars helicopter rotor is hovered are solved.
Drawings
In order to more clearly illustrate the embodiments or technical solutions in the prior art of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious for those skilled in the art to obtain other drawings without creative efforts;
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the motor of the present invention in a mounted position to the rotor portion;
FIG. 3 is a schematic cross-sectional view of a torque sensor and surrounding components of the present invention;
FIG. 4 is a schematic view of the installation positions of the upper end clamping ring of the upper torque sensor, the torque sensor and the lower end clamping ring of the torque sensor;
FIG. 5 is a schematic view of the tension sensor mounting location of the present invention;
the reference numbers are as follows:
1-paddle, 2-paddle clamp, 3-paddle clamp-motor connecting flange, 4-motor, 5-sleeve, 6-bearing, 7-step shaft, 8-torque sensor upper end clamping ring, 9-torque sensor, 10-torque sensor lower end clamping ring, 11-supporting cylinder, 12-supporting cylinder mounting plate, 13-tension sensor, 14-mounting bottom plate and 15-base.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first embodiment is as follows: as shown in fig. 1 to 5, a testing device comprises a paddle holder 2 and a motor 4, and is characterized in that: the paddle clamp 2 is installed on the motor 4 through a paddle clamp-motor connecting flange 3, the motor 4 is fixedly installed at the upper end of the stepped shaft 7, the torque sensor 9 is fixedly installed at the lower end of the stepped shaft 7, and the tension sensor 13 is fixedly installed at the lower end of the torque sensor 9;
in the testing process, when the motor 4 rotates, the paddle clamp 2 is driven to rotate through the paddle clamp-motor connecting flange 3, the two sides of the paddle clamp 2 are both provided with the paddles 1, and the paddles 1 are fixed through bolts; through the design, the blades can be quickly replaced, and the high Reynolds number airfoil profile, the low Reynolds number airfoil profile structure, the number of the blades and the geometric shape of the single-rotor system are evaluated according to various rotor index requirements, so that the method is convenient and quick;
when the paddle 1 rotates, the rotor of the motor 4 rotates to drive the paddle 1 to rotate to generate torque, and simultaneously, the stator of the motor 4 generates torque which is equal to the torque in magnitude and opposite to the torque in direction, and the torque is transmitted to the torque sensor 9 through the lower stepped shaft 7; the thrust generated by the rotation of the blade 1 is transmitted to the three tension sensors 13 through the motor 4, the bearing 6, the support cylinder 11 and the upper plate of the force sensor, and the tension condition and the stability of the helicopter body when the blade 1 rotates are determined by comparing the difference of the test values of the tension sensors 13. The fixed connection ensures that the torque and thrust generated by the rotor during rotation are transmitted to the torque sensor 9 and the tension sensor 13 completely.
In some disclosures, the upper end of the stepped shaft 7 is positioned by a boss and is connected with the motor 4 by a screw, and the lower end of the stepped shaft is positioned by the boss and is connected with the upper end clamping ring 8 of the torque sensor by the screw; the design can ensure the coaxiality of the torque sensor 8 and the motor spindle through the stepped shaft 7 to ensure the test accuracy.
In some disclosures, the upper end shaft and the lower end shaft of the torque sensor 9 are respectively provided with a torque sensor upper end clamping ring 8 and a torque sensor lower end clamping ring 10, and the torque sensor upper end clamping ring 8 and the torque sensor lower end clamping ring 10 are respectively connected with a tension sensor 13 through bolts and a stepped shaft 7; further, the torque sensor upper end clamping ring 8 and the torque sensor lower end clamping ring 10 are fastened by clamping the gaps on the side surfaces through bolts; the design can be realized through quickly completing the assembly, disassembly and replacement of the torque sensor 9 through the upper end clamping ring 8 and the lower end clamping ring 10 of the torque sensor, and respectively carrying out later maintenance and measurement correction.
In some disclosures, a sleeve 5 is arranged outside the stepped shaft 7, and the sleeve 5 is mounted on a support cylinder 11; can protect the motor through sleeve 5 like this and avoid the motor in-process to take place the striking and lead to equipment inefficacy.
In some disclosures, a lower end shaft of the torque sensor 9 is provided with a lower end clamping ring 10 of the torque sensor, a supporting cylinder mounting plate 12 is arranged below the lower end clamping ring 10 of the torque sensor, three tension sensors 13 are uniformly arranged below the supporting cylinder mounting plate 12 in a circumferential distribution mode, and the lower ends of the tension sensors 13 are arranged on a mounting bottom plate 14; the mounting base plate 14 is fixedly mounted on the base 15, so that the mounting base plate 14 can be fixedly mounted on the mounting base plate through the tension sensor 13, the stress condition of the helicopter and the motor mounting point when the blade 1 rotates is simulated, the stress condition of the helicopter body when the electric driving propeller of the Mars helicopter rotates is tested, and the inaccuracy of calculation of the stress condition of the helicopter body caused by different Mars environments due to the fact that the stress condition of the motor is tested simply can be avoided.
In some disclosures, the supporting cylinder mounting plate 12 is provided with a supporting cylinder 11, and a bearing 6 is arranged between the supporting cylinder 11 and the stepped shaft 7; further, the bearing 6 adopts a thrust ball bearing, and through the design, the thrust ball bearing can offset most gravity, so that the test results of the tension sensor 13 and the torque sensor 9 are accurate.
The supporting cylinder mounting plate 12 and the supporting cylinder 11 are matched with the bearing 6 for supporting and fixing, so that the situation that the tension sensor 13 and the static torque sensor 9 bear tension and torque at the same time can be avoided, the testing precision is interfered, and meanwhile, the static torque sensor cannot give out a torque value in real time.
Example two: as shown in fig. 1 to 5, a device for testing aerodynamic characteristics of a pull torque decoupling type single-rotor system includes: the paddle clamping device comprises a paddle 1, a paddle clamp 2, a paddle clamp-motor connecting flange 3, a motor 4, a sleeve 5, a bearing 6, a stepped shaft 7, a torque sensor upper end clamping ring 8, a torque sensor 9, a torque sensor lower end clamping ring 10, a support barrel 11, a support barrel mounting plate 12, a tension sensor 13, a mounting bottom plate 14 and a base 15; the sleeve 5 is connected with the supporting cylinder 11 through a bolt to shield the rotating motor 4.
The paddle 1 is divided into two pieces, and the two pieces are connected to two sides of the paddle clamp 2 in a bolt connection mode; the paddle clamp 2 is positioned with a paddle clamp-motor connecting flange through a spigot so as to ensure the coaxiality during rotation and is connected through a bolt; the paddle clamp-motor connecting flange 3 and the motor 4 are positioned through the openings to ensure the coaxiality during rotation and are connected through screws; the embodiment can ensure that the torque and the thrust generated by the rotor wing during rotation are completely transmitted to the torque sensor and the tension sensor.
A positioning spigot of a support cylinder 11 and a mounting seat of a clamping ring 10 at the lower end of the torque sensor are arranged on the support cylinder mounting plate 12; the torque sensor lower end clamping ring 10 is firstly connected with the support cylinder mounting plate 12 through screws, then the lower end of the torque sensor 9 is inserted into the torque sensor lower end clamping ring 10, and two bolts on the side surface of the torque sensor lower end clamping ring 10 are screwed to clamp the torque sensor 9.
The supporting cylinder 11 is installed on the supporting cylinder installation plate 12 through bolts, the bearing 6 is embedded into the upper section of the supporting cylinder 11, the stepped shaft 7 and the torque sensor upper end clamping ring 8 are connected through the bolts, then the stepped shaft 7 and the torque sensor upper end clamping ring 8 are embedded into the bearing inner ring from the upper side of the bearing, and two bolts on the side face of the torque sensor upper end clamping ring 8 are screwed down to clamp the torque sensor upper end shaft. At the moment, a small rotation difference can be generated between the upper end shaft and the lower end shaft of the torque sensor so as to measure the torque generated when the rotor rotates.
In some disclosures, the mounting base plate 14 is firstly mounted on the base 15 through bolts, the tension sensors 13 are uniformly distributed and mounted on the mounting base plate 14 through screw connection, and the support cylinder mounting plate 12 is connected above the tension sensors 13 through screws. Thus, the thrust generated by the rotation of the rotor wing can be completely measured by the tension sensor 13; according to the invention, limit measures are designed for the upper part and the lower part of the counter bearing, the motor, the tension sensor and the torque sensor so as to ensure that the upward thrust and the downward thrust generated by the rotor wing in the experimental process can not influence the structure of the invention. The invention can carry out high-precision measurement on clockwise and anticlockwise torque generated by the rotation of the rotor wing in a low-pressure environment, and can carry out precise measurement on the thrust in the upward and downward directions generated by the rotor wing on the premise of ensuring the structural strength.
Example three: according to the method, the device in the first embodiment or the second embodiment is placed in a large vacuum tank for testing, so that the stress condition of a helicopter body under a Mars atmospheric environment can be simulated, and real data can be passed through for the Mars helicopter.
Further, the air density in the large vacuum tank is 0.00129kg/m3;
furthermore, the air pressure in the large vacuum tank is 1Pa, the wingspan is 0.1m, and the rotating speed of the rotor wing is 100rpm.
Example four: a method for testing aerodynamic performance of a rotor wing is characterized in that the device in the first embodiment or the second embodiment is placed in a large vacuum tank for testing, so that the stress condition of a helicopter body under a Mars atmospheric environment can be simulated, and real data can be passed for a Mars helicopter.
Further, the air density in the large vacuum tank is 0.0129kg/m3;
further, the air pressure in the large vacuum tank is 104Pa, the span is 1.4m, and the rotating speed of the rotor wing is 4000rpm.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are given by way of illustration of the principles of the present invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, and such changes and modifications are within the scope of the invention as claimed.
Claims (10)
1. The utility model provides a pneumatic characteristic testing arrangement of single rotor system of pulling force torque decoupling type, includes that the oar presss from both sides (2) and motor (4), its characterized in that: the paddle clamp (2) is installed on the motor (4) through the paddle clamp-motor connecting flange (3), the motor (4) is fixedly installed at the upper end of the stepped shaft (7), the lower end of the stepped shaft (7) is fixedly provided with the torque sensor (9), and the lower end of the torque sensor (9) is fixedly provided with the tension sensor (13).
2. The pull torque decoupling type single-rotor system aerodynamic performance testing device is characterized in that the upper end of the stepped shaft (7) is positioned through a boss and connected with the motor (4) through a screw, the lower end of the stepped shaft is positioned through the boss and connected with an upper end clamping ring (8) of the torque sensor through the screw.
3. The pull torque decoupling type single-rotor system aerodynamic characteristic testing device is characterized in that a torque sensor upper end clamping ring (8) and a torque sensor lower end clamping ring (10) are mounted on an upper end shaft and a lower end shaft of the torque sensor (9) respectively, the torque sensor upper end clamping ring (8) and the torque sensor lower end clamping ring (10) are connected with a pull sensor (13) through bolts and a stepped shaft (7) respectively, and the torque sensor upper end clamping ring (8) and the torque sensor lower end clamping ring (10) enable gaps on the side faces to be clamped tightly through the bolts for fastening.
4. The device for testing the aerodynamic characteristics of the tension-torque decoupling type single-rotor system according to claim 1, wherein a sleeve (5) is arranged outside the stepped shaft (7), and the sleeve (5) is mounted on the support cylinder (11).
5. The device for testing the aerodynamic characteristics of the tension-torque decoupled single-rotor system according to claim 1 is characterized in that paddles (1) are mounted on two sides of the paddle clamp (2), and the paddles (1) are fixed through bolts.
6. The pull torque decoupling type single-rotor system aerodynamic characteristic testing device is characterized in that a lower end shaft of the torque sensor (9) is provided with a lower end clamping ring (10) of the torque sensor, a supporting cylinder mounting plate (12) is arranged below the lower end clamping ring (10) of the torque sensor, the pull sensor (13) is arranged below the supporting cylinder mounting plate (12), and the lower end of the pull sensor (13) is arranged on a mounting base plate (14).
7. The device for testing the aerodynamic characteristics of the tension-torque decoupling type single-rotor system according to claim 6 is characterized in that three tension sensors (13) which are uniformly distributed in the circumferential direction are arranged below the supporting cylinder mounting plate (12).
8. The device for testing the aerodynamic characteristics of the tension-torque decoupling type single-rotor system according to claim 7 is characterized in that a support cylinder (11) is mounted on the support cylinder mounting plate (12), and a bearing (6) is arranged between the support cylinder (11) and the stepped shaft (7).
9. A method for testing the aerodynamic performance of a rotor, which is characterized in that the method is used for testing by placing the device for testing the aerodynamic characteristics of the tension-torque decoupled single-rotor system according to claim 1 in a large vacuum tank.
10. The rotorcraft aerodynamic performance testing method of claim 9, wherein air pressure in the large vacuum tank is 1-104Pa.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210728353.8A CN115140323A (en) | 2022-06-24 | 2022-06-24 | Pneumatic characteristic testing device of tension torque decoupling type single rotor system |
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| CN202210728353.8A CN115140323A (en) | 2022-06-24 | 2022-06-24 | Pneumatic characteristic testing device of tension torque decoupling type single rotor system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116558766A (en) * | 2023-07-10 | 2023-08-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Ground simulation method for tail rotor aerodynamic characteristic test in aerodynamic interference environment |
| CN116593055A (en) * | 2023-06-27 | 2023-08-15 | 惠州好盈电机有限公司 | Coaxial testing arrangement of motor tensile force |
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| US20130125667A1 (en) * | 2010-07-14 | 2013-05-23 | University Of Florida Research Foundation, Inc. | System and method for assessing the performance of an attitude control system for small satellites |
| CN108438261A (en) * | 2018-03-20 | 2018-08-24 | 哈尔滨工业大学 | A kind of rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device and its test method |
| CN108502216A (en) * | 2018-05-02 | 2018-09-07 | 哈尔滨工业大学 | A kind of permanent tension system based on motor, constant moment of force mechanism and differential gear train |
| 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 |
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2022
- 2022-06-24 CN CN202210728353.8A patent/CN115140323A/en active Pending
Patent Citations (5)
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| JPH11115900A (en) * | 1997-10-14 | 1999-04-27 | Nippon Telegr & Teleph Corp <Ntt> | Hanging device |
| US20130125667A1 (en) * | 2010-07-14 | 2013-05-23 | University Of Florida Research Foundation, Inc. | System and method for assessing the performance of an attitude control system for small satellites |
| CN108438261A (en) * | 2018-03-20 | 2018-08-24 | 哈尔滨工业大学 | A kind of rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device and its test method |
| CN108502216A (en) * | 2018-05-02 | 2018-09-07 | 哈尔滨工业大学 | A kind of permanent tension system based on motor, constant moment of force mechanism and differential gear train |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116593055A (en) * | 2023-06-27 | 2023-08-15 | 惠州好盈电机有限公司 | Coaxial testing arrangement of motor tensile force |
| CN116593055B (en) * | 2023-06-27 | 2023-10-13 | 惠州好盈电机有限公司 | Coaxial testing arrangement of motor tensile force |
| CN116558766A (en) * | 2023-07-10 | 2023-08-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Ground simulation method for tail rotor aerodynamic characteristic test in aerodynamic interference environment |
| CN116558766B (en) * | 2023-07-10 | 2023-09-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Ground simulation method for tail rotor aerodynamic characteristic test in aerodynamic interference environment |
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