CN111114857A - Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft - Google Patents
Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft Download PDFInfo
- Publication number
- CN111114857A CN111114857A CN201910906796.XA CN201910906796A CN111114857A CN 111114857 A CN111114857 A CN 111114857A CN 201910906796 A CN201910906796 A CN 201910906796A CN 111114857 A CN111114857 A CN 111114857A
- Authority
- CN
- China
- Prior art keywords
- truss
- module
- rotor
- torque sensor
- layer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/14—Space shuttles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model relates to a split type mars aircraft rotor system aerodynamic characteristic measuring device is transferred to hand, it relates to aerodynamic characteristic measuring device, concretely relates to split type mars aircraft rotor system aerodynamic characteristic measuring device is transferred to hand. The invention aims to solve the problem that the machining precision and the manufacturing process of the conventional coaxial rotor system aerodynamic characteristic measuring device are difficult to guarantee. The invention comprises an upper rotor wing module, a general truss module and a lower rotor wing module, wherein the upper rotor wing module and the lower rotor wing module are sequentially arranged on the general truss module from top to bottom, and the rotating shaft of the upper rotor wing module is coaxial with the rotating shaft of the lower rotor wing module. The invention belongs to the field of aerospace.
Description
Technical Field
The invention relates to a pneumatic characteristic measuring device, in particular to a pneumatic characteristic measuring device of a rotor system of a manually-adjusted split Mars aircraft, and belongs to the field of aerospace.
Background
Mars have a physical environment similar to the earth, so that the Mars detection task is beneficial to expanding the living space of human beings and deepening the understanding of the evolution of the earth and the origin of life. At present, the detection of mars by human beings is still in the detection stage of a mars rover. The Mars aircraft can fly at a certain height on the surface of the Mars, obtains images with higher resolution than that of a satellite, and provides a far visual field for the Mars vehicle so as to perform large-range accurate navigation on the Mars vehicle. The safety of the Mars vehicle in a complex Mars terrain environment is guaranteed, and the efficiency of a Mars detection task is guaranteed. Among the Mars aircrafts, the rotor type aircraft has the advantages of fixed-point takeoff and landing and high adaptability to various terrains. The thin and cold atmosphere of mars makes the rotor surface of rotor type mars aircraft be low reynolds number and high mach number state, and this puts higher demands on the aerodynamic performance of rotor. Since the coaxial rotor type mars aircraft has high flight efficiency, it is necessary to study the coaxial rotor type configuration and to study the influence of the coupling effect of the air flow between the upper and lower rotors on the aerodynamic characteristics of the rotors.
The conventional aerodynamic characteristic measuring device of the coaxial rotor system mainly comprises an integrated scheme and a split scheme. The machining precision and the manufacturing process of the integrated scheme are relatively difficult to guarantee relative to a split type, and therefore the split type mars aircraft rotor system aerodynamic characteristic measuring device is selected to test the coupling effect of air currents between the upper rotor and the lower rotor.
Disclosure of Invention
The invention provides a device for measuring the aerodynamic characteristics of a rotor system of a manually-adjusted split Mars aircraft, which aims to solve the problem that the machining precision and the manufacturing process of the conventional device for measuring the aerodynamic characteristics of a coaxial rotor system are difficult to guarantee.
The technical scheme adopted by the invention for solving the problems is as follows: the invention comprises an upper rotor wing module, a general truss module and a lower rotor wing module, wherein the upper rotor wing module and the lower rotor wing module are sequentially arranged on the general truss module from top to bottom, and the rotating shaft of the upper rotor wing module is coaxial with the rotating shaft of the lower rotor wing module.
Further, the totality truss module includes the truss top layer, the truss middle level, truss bottom and two vertical trusses, two vertical trusses are vertical to be set up side by side, the truss top layer, the truss middle level, the truss bottom is from top to bottom in proper order the level set up between two vertical trusses, the both ends of truss top layer and the upper end fixed connection of two vertical trusses, the middle part fixed connection of the middle part of truss both ends and two vertical trusses, the both ends of truss bottom and the lower extreme fixed connection of two vertical trusses, go up the middle part at truss top layer lower surface of rotor module installation, the middle part at truss middle level upper surface is installed to lower rotor module.
Furthermore, the overall truss module further comprises three sliding assemblies, one end of the middle layer of the truss is connected with the vertical truss through the two sliding assemblies, and the other end of the middle layer of the truss is connected with the vertical truss through one sliding assembly.
Furthermore, each sliding assembly comprises a sliding short truss, a connecting plate, a sliding block, a linear guide rail and a guide rail clamp, the middle layer of the truss is connected with the sliding short truss, the sliding short truss is connected with the sliding block through the connecting plate, the sliding block is connected with the linear guide rail in a sliding mode, the linear guide rail is installed on the vertical truss in a specified mode, and the guide rail clamp is installed at the lower end of the linear guide rail.
Furthermore, the upper rotor module comprises a motor with a torque sensor, an upper torque sensor support, three groups of upper tension sensors, an upper motor base, an upper power transmission mechanism, an upper rotor and an upper centering cone, wherein the upper torque sensor support is installed on the top layer of the truss, the upper rotor is connected with the upper power transmission mechanism, the upper power transmission mechanism is connected with the motor with the torque sensor, the upper power transmission mechanism is installed on the upper motor base, the upper motor base is connected with the upper torque sensor support through the three groups of tension sensors, and the upper centering cone is screwed on the upper rotor through self threads.
Further, the lower rotor wing module comprises a lower rotor wing, a lower power transmission mechanism, a motor support with a torque sensor at the lower part, an optical platform, a lower centering cone and a motor with a torque sensor at the lower part, the optical platform is arranged on the middle layer of the truss, the motor support with the torque sensor at the lower part is arranged on the optical platform, the motor with the torque sensor at the lower part is arranged on the motor support with the torque sensor at the lower part, the motor with the torque sensor at the lower part is connected with the lower power transmission mechanism, the lower rotor wing is connected with the lower power transmission mechanism, and the lower centering cone is screwed on the lower rotor wing through self threads.
The invention has the beneficial effects that: the device has scientific and reasonable structural design, the upper rotor module of the device for measuring the aerodynamic characteristics of the manually-adjusted split rotor system is arranged on the top layer of the truss, and the lower rotor module is arranged on the middle layer of the truss. The middle layer of the truss is connected with the overall truss module through three groups of sliding block linear guide rails. When the guide rail clamp is loosened and the fixing bolt of the truss part is unscrewed, the middle layer of the truss can drive the lower rotor wing module to move up and down linearly, and the stay at any position in a given range is realized. The guide rail clamp and the bolt are tightened to perform experiments, and the influence of different propeller distances on the pneumatic performance of the upper rotor and the lower rotor can be measured. The scheme is used for realizing the pneumatic characteristic measurement of the split rotor system, the coaxiality between the upper rotor shaft and the lower rotor shaft is improved, and the difficulty and the cost of design and processing assembly are reduced. The upper rotor wing module and the lower rotor wing module of the pneumatic characteristic measuring device of the manual adjustment split type rotor wing system comprise a motor, a transmission shaft, a tension sensor, a torque sensor and the like;
the upper rotor module and the lower rotor module are provided with mechanical interfaces capable of mounting blades with different mounting angles and geometric characteristics, so that the rotor blades can be quickly replaced, and aerodynamic characteristic experiments can be conveniently carried out on the blades with different parameters;
the working environment of the invention is carbon dioxide (Mars) or air (earth), which is suitable for being widely popularized and used;
the upper rotor wing module and the lower rotor wing module can respectively and independently perform single-shaft rotor wing aerodynamic characteristic experiments, and the application range is wide.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a side view of the present invention;
FIG. 3 is a front view of the overall truss module;
FIG. 4 is a front view of the upper rotor module;
FIG. 5 is a front view of the lower rotor module;
FIG. 6 is an enlarged view at A in FIG. 3;
fig. 7 is an enlarged view at B in fig. 2.
Detailed Description
The first embodiment is as follows: the embodiment is described with reference to fig. 1 to 7, and the aerodynamic characteristic measurement device of the manual split type mars aircraft rotor system in the embodiment includes an upper rotor module 1, a total truss module 2 and a lower rotor module 3, where the upper rotor module 1 and the lower rotor module 3 are sequentially installed on the total truss module 2 from top to bottom, and a rotating shaft of the upper rotor module 1 is coaxial with a rotating shaft of the lower rotor module 3.
The rotating speed adjusting range of the upper rotor wing module and the lower rotor wing module is 0-4500 r/min, the lift force measuring precision is 0.01N, the torque measuring precision is 0.01 N.m, the span adjusting range is 0-1000 mm, and the pitch adjusting range is 0-500 mm.
In the invention, the upper rotor wing module 1 is arranged on the top layer 2-1 of the truss, the lower rotor wing module 3 is arranged on the middle layer 2-2 of the truss, and a plurality of weights can be stacked on the bottom layer 2-3 of the truss, thereby ensuring the rigidity of the whole structure in the operation of the upper and lower rotor wings and weakening the possible resonance of the system.
The second embodiment is as follows: the embodiment is described with reference to fig. 1 to 7, and the overall truss module 2 of the manual adjustment split type mars aircraft rotor system aerodynamic characteristic measurement device in the embodiment comprises a truss top layer 2-1, a truss middle layer 2-2, a truss bottom layer 2-3 and two vertical trusses 2-4, wherein the two vertical trusses 2-4 are vertically arranged side by side, the truss top layer 2-1, the truss middle layer 2-2 and the truss bottom layer 2-3 are sequentially and horizontally arranged between the two vertical trusses 2-4 from top to bottom, two ends of the truss top layer 2-1 are fixedly connected with the upper ends of the two vertical trusses 2-4, two ends of the truss middle layer 2-2 are fixedly connected with the middle parts of the two vertical trusses 2-4, two ends of the truss bottom layer 2-3 are fixedly connected with the lower ends of the two vertical trusses 2-4, the upper rotor wing module 1 is arranged in the middle of the lower surface of the top layer 2-1 of the truss, and the lower rotor wing module 3 is arranged in the middle of the upper surface of the middle layer 2-2 of the truss. Other components and connections are the same as those in the first embodiment.
The third concrete implementation mode: the embodiment is described with reference to fig. 1 to 7, the overall truss module 2 of the aerodynamic characteristic measurement device of the manual adjustment split type mars aircraft rotor system of the embodiment further comprises three sliding assemblies, one end of the middle truss layer 2-2 is connected with the vertical truss 2-4 through the two sliding assemblies, and the other end of the middle truss layer 2-2 is connected with the vertical truss 2-4 through one sliding assembly.
Other components and connection relationships are the same as those in the second embodiment.
The fourth concrete implementation mode: the embodiment is described with reference to fig. 1 to 7, each sliding assembly of the aerodynamic characteristic measurement device of the manual split type mars aircraft rotor system in the embodiment comprises a sliding short truss 2-5, a connecting plate 2-6, a sliding block 2-7, a linear guide rail 2-8 and a guide rail clamp 2-9, the truss middle layer 2-2 is connected with the sliding short truss 2-5, the sliding short truss 2-5 is connected with the sliding block 2-7 through the connecting plate 2-6, the sliding block 2-7 is connected with the linear guide rail 2-8 in a sliding mode, the linear guide rail 2-8 is installed on a vertical truss 2-4 in a specified mode, and the guide rail clamp 2-9 is installed at the lower end of the linear guide rail 2-8.
The middle layer 2-2 of the truss, the short sliding truss 2-5, the connecting plate 2-6, the sliding blocks 2-7, the linear guide rails 2-8 and the vertical truss 2-4 are connected, and the lower surfaces of the sliding blocks, which are positioned below the three groups of linear guide rails, are in fit connection with one guide rail clamp 2-9. The upper rotor module 1 is arranged on the top layer 2-1 of the truss, and the lower rotor module 3 is arranged on the middle layer 2-2 of the truss. When the guide rail clamp 2-9 is loosened and the fixing bolt of the truss part is unscrewed, the middle layer 2-2 of the truss can drive the lower rotor module 3 to move up and down linearly, and the guide rail clamp and the bolt are tightened again to stop at any position in a given range. Experiments are carried out, and the influence of the aerodynamic performance of the upper rotor and the lower rotor caused by different propeller distances can be measured. The scheme is used for realizing the pneumatic characteristic measurement of the split rotor system, the coaxiality between the upper rotor shaft and the lower rotor shaft is improved, and the difficulty and the cost of design and processing assembly are reduced.
Other components and connection relationships are the same as those in the third embodiment.
The fifth concrete implementation mode: the embodiment is described with reference to fig. 1 to 7, an upper rotor module 1 of the device for measuring aerodynamic characteristics of a rotor system of a manually-adjusted split type mars aircraft according to the embodiment includes a motor 1-1 with a torque sensor, an upper torque sensor support 1-2, three groups of pull-up sensors 1-3, an upper motor base 1-4, an upper power transmission mechanism 1-5, an upper rotor 1-6 and an upper centering cone 1-7, the upper torque sensor support 1-2 is mounted on a top layer 2-1 of a truss, the upper rotor 1-6 is connected with the upper power transmission mechanism 1-5, the upper power transmission mechanism 1-5 is connected with the motor 1-1 with the torque sensor, the upper power transmission mechanism 1-5 is mounted on the upper motor base 1-4, the upper motor base 1-4 is connected with the upper torque sensor support 1-2 through the three groups of pull-3, the upper centering cones 1-7 are screwed on the upper rotor wings 1-6 through self threads. Other components and connection relationships are the same as those in the first or second embodiment.
The sixth specific implementation mode: the embodiment is described with reference to fig. 1 to 7, and the lower rotor module 3 of the aerodynamic characteristic measurement device of the rotor system of the hand-adjusting split type mars aircraft according to the embodiment comprises a lower rotor 3-1, a lower power transmission mechanism 3-2, a motor support 3-3 with a torque sensor at the lower part, an optical platform 3-4, a lower centering cone 3-5 and a motor 3-6 with a torque sensor at the lower part, wherein the optical platform 3-4 is arranged on the middle layer 2-2 of the truss, the motor support 3-3 with a torque sensor at the lower part is arranged on the optical platform 3-4, the motor 3-6 with a torque sensor at the lower part is arranged on the motor support 3-3 with a torque sensor at the lower part, and the motor 3-6 with a torque sensor at the lower part is connected with the lower power transmission mechanism 3-2, the lower rotor 3-1 is connected with the lower power transmission mechanism 3-2, and the lower centering cone 3-5 is screwed on the lower rotor 3-1 through self threads. Other components and connection relationships are the same as those in the first or second embodiment.
Principle of operation
The oar interval adjustment process of the manual adjustment split type rotor system aerodynamic characteristic measuring device: when the guide rail clamp 2-9 is loosened and the fixing bolt of the truss part is screwed off, the middle layer 2-2 of the truss can drive the lower rotor module 3 to do up-and-down linear motion on the three groups of linear guide rails 2-8, the guide rail clamp 2-9 and the sliding block 2-7 are tightened again, and the relevant fixing bolt is screwed off, so that the lower rotor module 3 can be stopped at any position in a given height range. Because lower rotor module 3 is upper and lower movable, adjust and carry out a lot of experiments, can measure the influence that different oar intervals brought for upper and lower rotor aerodynamic performance, and then the air current coupling effect between the upper and lower rotor of research. Therefore, the aerodynamic characteristic measurement of the split rotor system is realized, the parallel of the tip rotating plane of the upper rotor 1-6 relative to the tip rotating plane of the lower rotor 3-1 in the rotating process is ensured, and the difficulty and the cost of design, processing and assembly are reduced;
the centering adjustment process of the pneumatic characteristic measuring device of the manual adjustment split type rotor system comprises the following steps: at the initial moment, the truss structure precision is lower than that of a machined part, and the centering needs to be adjusted, so that the rotary wing rotating axes of the upper rotary wing module and the lower rotary wing module can be collinear. The method comprises the steps that an upper centering cone 1-7 of an upper rotor wing module 1 is installed on an upper rotor wing 1-6, a lower centering cone 3-5 of a lower rotor wing module 3 is installed on a lower rotor wing 3-1, the lower rotor wing module 3 and a middle layer 2-2 of a truss are lifted to the highest position and three groups of sliding blocks 2-7 are locked after assembly is finished, the upper centering cone 1-7 is tried to be inserted into a centering cone 3-5 conical hole to detect the coaxiality of the upper rotor wing 1-6 and the lower rotor wing 3-1, then screws on the truss are adjusted until the upper centering cone and the lower centering cone are aligned, centering of the upper rotor wing and the lower rotor wing is achieved, and coaxiality is. Therefore, the accuracy of the pneumatic characteristic experiment of the split rotor system can be improved;
truss support process of the device for measuring aerodynamic characteristics of a manually-adjusted split rotor system: the upper rotor module 1 is installed on the top layer 2-1 of the truss, the lower rotor module 3 is installed on the middle layer 2-2 of the truss, and the truss is of a hollow structure, so that the system can generate resonance when the upper rotor and the lower rotor work simultaneously, and the experimental process and result are influenced. More weights can be stacked on the bottom layers 2-3 of the truss, so that the rigidity of the whole structure in the operation of the upper and lower rotary wings is ensured, and the resonance of the system is weakened. The paddle of the upper rotor module 1 and the paddle of the lower rotor module 3 are reversely installed, thrust is generated downwards to offset the influence of the ground effect on the experiment, so that the thrust directions generated by the two rotors are vertical downwards, the total resultant force is downward, and the structure of the testing device is stable.
Although the present invention has been described with reference to a preferred embodiment, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (6)
1. The utility model provides a split type mars aircraft rotor system aerodynamic characteristic measuring device of hand modulation, its characterized in that: the device for measuring the aerodynamic characteristics of the manually-adjusted split type Mars aircraft rotor system comprises an upper rotor module (1), an overall truss module (2) and a lower rotor module (3), wherein the upper rotor module (1) and the lower rotor module (3) are sequentially installed on the overall truss module (2) from top to bottom, and the rotating shaft of the upper rotor module (1) is coaxial with the rotating shaft of the lower rotor module (3).
2. The device for measuring the aerodynamic characteristics of a manually adjusted split-type mars aircraft rotor system according to claim 1, wherein: the overall truss module (2) comprises a truss top layer (2-1), a truss middle layer (2-2), a truss bottom layer (2-3) and two vertical trusses (2-4), wherein the two vertical trusses (2-4) are vertically arranged side by side, the truss top layer (2-1), the truss middle layer (2-2) and the truss bottom layer (2-3) are sequentially and horizontally arranged between the two vertical trusses (2-4) from top to bottom, two ends of the truss top layer (2-1) are fixedly connected with the upper ends of the two vertical trusses (2-4), two ends of the truss middle layer (2-2) are fixedly connected with the middle parts of the two vertical trusses (2-4), two ends of the truss bottom layer (2-3) are fixedly connected with the lower ends of the two vertical trusses (2-4), the upper rotary wing module (1) is installed in the middle part of the lower surface of the truss top layer (2, the lower rotor wing module (3) is arranged in the middle of the upper surface of the middle layer (2-2) of the truss.
3. The device for measuring the aerodynamic characteristics of a manually adjusted split-type mars aircraft rotor system according to claim 2, wherein: the overall truss module (2) further comprises three sliding assemblies, one end of the middle truss layer (2-2) is connected with the vertical truss (2-4) through the two sliding assemblies, and the other end of the middle truss layer (2-2) is connected with the vertical truss (2-4) through one sliding assembly.
4. The device for measuring the aerodynamic characteristics of a manually adjusted split-type mars aircraft rotor system according to claim 3, wherein: each sliding assembly comprises a sliding short truss (2-5), a connecting plate (2-6), a sliding block (2-7), a linear guide rail (2-8) and a guide rail clamp (2-9), the middle layer (2-2) of the truss is connected with the sliding short truss (2-5), the sliding short truss (2-5) is connected with the sliding block (2-7) through the connecting plate (2-6), the sliding block (2-7) is connected with the linear guide rail (2-8) in a sliding mode, the linear guide rail (2-8) is installed on a vertical truss (2-4) in a specified mode, and the guide rail clamp (2-9) is installed at the lower end of the linear guide rail (2-8).
5. The device for measuring the aerodynamic characteristics of a rotor system of a manually adjusted split mars aircraft according to claim 1 or 2, wherein: the upper rotary wing module (1) comprises a motor (1-1) with a torque sensor, an upper torque sensor support (1-2), three groups of upper tension sensors (1-3), an upper motor base (1-4), an upper power transmission mechanism (1-5), an upper rotary wing (1-6) and an upper centering cone (1-7), the upper torque sensor support (1-2) is installed on the top layer (2-1) of the truss, the upper rotary wing (1-6) is connected with the upper power transmission mechanism (1-5), the upper power transmission mechanism (1-5) is connected with the motor (1-1) with the torque sensor, the upper power transmission mechanism (1-5) is installed on the upper motor base (1-4), the upper motor base (1-4) is connected with the upper torque sensor support (1-2) through the three groups of tension sensors (1-3), the upper centering cones (1-7) are screwed on the upper rotor wings (1-6) through self threads.
6. The device for measuring the aerodynamic characteristics of a rotor system of a manually adjusted split mars aircraft according to claim 1 or 2, wherein: the lower rotor wing module (3) comprises a lower rotor wing (3-1), a lower power transmission mechanism (3-2), a motor support (3-3) with a torque sensor at the lower part, an optical platform (3-4), a lower centering cone (3-5) and a motor (3-6) with a torque sensor at the lower part, wherein the optical platform (3-4) is arranged on the middle layer (2-2) of the truss, the motor support (3-3) with a torque sensor at the lower part is arranged on the optical platform (3-4), the motor (3-6) with a torque sensor at the lower part is arranged on the motor support (3-3) with a torque sensor at the lower part, the motor (3-6) with a torque sensor at the lower part is connected with the lower power transmission mechanism (3-2), the lower rotor wing (3-1) is connected with the lower power transmission mechanism (3-2), the lower centering cone (3-5) is screwed on the lower rotor wing (3-1) through self threads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910906796.XA CN111114857B (en) | 2019-09-24 | 2019-09-24 | Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910906796.XA CN111114857B (en) | 2019-09-24 | 2019-09-24 | Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111114857A true CN111114857A (en) | 2020-05-08 |
| CN111114857B CN111114857B (en) | 2022-10-28 |
Family
ID=70495307
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910906796.XA Active CN111114857B (en) | 2019-09-24 | 2019-09-24 | Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111114857B (en) |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB410532A (en) * | 1932-11-26 | 1934-05-24 | Cierva Juan De La | Improvements in and relating to aircraft having rotative wings |
| US3651690A (en) * | 1968-08-02 | 1972-03-28 | Gkn Transmissions Ltd | Apparatus for measuring output characteristics of a rotary moving part |
| EP0545750A1 (en) * | 1991-12-02 | 1993-06-09 | AEROSPATIALE Société Nationale Industrielle | Multiple blade variable pitch rotor, in particular for rear antitorque apparatus of a rotorcraft |
| EP0831314A1 (en) * | 1996-09-19 | 1998-03-25 | Martin Lauener | Device for measuring torque |
| CN101549754A (en) * | 2009-04-29 | 2009-10-07 | 北京航空航天大学 | A composite rotating fixed-wing aircraft and its design method |
| CN102901623A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Device for testing coaxial inversion rotor wing of helicopter |
| CN103743557A (en) * | 2014-01-02 | 2014-04-23 | 上海大学 | Comprehensive propeller test system |
| US20140271193A1 (en) * | 2013-03-15 | 2014-09-18 | Frontier Wind, Llc | Load Distribution Estimation |
| CN204341397U (en) * | 2014-12-04 | 2015-05-20 | 北方天途航空技术发展（北京）有限公司 | Many rotor wing unmanned aerial vehicles screw propeller |
| CN104913912A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Hanging type coaxial contrarotating rotor wing testing device |
| CN107985582A (en) * | 2017-11-30 | 2018-05-04 | 哈尔滨工业大学 | A kind of coaxial anti-paddle twayblade rotor system of Mars rotary wind type unmanned plane |
| 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 |
| CN108454838A (en) * | 2018-03-27 | 2018-08-28 | 佛山科学技术学院 | A kind of titling coaxial bispin wing aircraft |
| CN108593169A (en) * | 2018-04-19 | 2018-09-28 | 哈尔滨工业大学 | Rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device and torsion-testing method and lift test method |
| CN109612681A (en) * | 2018-11-16 | 2019-04-12 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerodynamic interference measurement method of the coaxial rigid rotor model of helicopter |
-
2019
- 2019-09-24 CN CN201910906796.XA patent/CN111114857B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB410532A (en) * | 1932-11-26 | 1934-05-24 | Cierva Juan De La | Improvements in and relating to aircraft having rotative wings |
| US3651690A (en) * | 1968-08-02 | 1972-03-28 | Gkn Transmissions Ltd | Apparatus for measuring output characteristics of a rotary moving part |
| EP0545750A1 (en) * | 1991-12-02 | 1993-06-09 | AEROSPATIALE Société Nationale Industrielle | Multiple blade variable pitch rotor, in particular for rear antitorque apparatus of a rotorcraft |
| EP0831314A1 (en) * | 1996-09-19 | 1998-03-25 | Martin Lauener | Device for measuring torque |
| CN101549754A (en) * | 2009-04-29 | 2009-10-07 | 北京航空航天大学 | A composite rotating fixed-wing aircraft and its design method |
| CN102901623A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Device for testing coaxial inversion rotor wing of helicopter |
| US20140271193A1 (en) * | 2013-03-15 | 2014-09-18 | Frontier Wind, Llc | Load Distribution Estimation |
| CN103743557A (en) * | 2014-01-02 | 2014-04-23 | 上海大学 | Comprehensive propeller test system |
| CN204341397U (en) * | 2014-12-04 | 2015-05-20 | 北方天途航空技术发展（北京）有限公司 | Many rotor wing unmanned aerial vehicles screw propeller |
| CN104913912A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Hanging type coaxial contrarotating rotor wing testing device |
| CN107985582A (en) * | 2017-11-30 | 2018-05-04 | 哈尔滨工业大学 | A kind of coaxial anti-paddle twayblade rotor system of Mars rotary wind type unmanned plane |
| 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 |
| CN108454838A (en) * | 2018-03-27 | 2018-08-28 | 佛山科学技术学院 | A kind of titling coaxial bispin wing aircraft |
| CN108593169A (en) * | 2018-04-19 | 2018-09-28 | 哈尔滨工业大学 | Rotary wind type Mars unmanned plane single rotor system gas dynamic characteristic test device and torsion-testing method and lift test method |
| CN109612681A (en) * | 2018-11-16 | 2019-04-12 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerodynamic interference measurement method of the coaxial rigid rotor model of helicopter |
Non-Patent Citations (2)
| Title |
|---|
| 周凌宇等: "共轴双旋翼涵道风扇的气动特性研究", 《长春理工大学学报(自然科学版)》 * |
| 赵鹏越等: "旋翼式火星无人机技术发展综述", 《宇航学报》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111114857B (en) | 2022-10-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108844711B (en) | Wing type two-degree-of-freedom dynamic wind tunnel test device | |
| CN109632238B (en) | 90-degree large attack angle device for sub-span supersonic wind tunnel | |
| CN105547676A (en) | Multifunctional swing-arm type rotor wing test stand | |
| CN108275287B (en) | Comprehensive test device and method for aerodynamic interference and ground effect of multi-rotor aircraft | |
| CN109506877B (en) | Sub-span super wind tunnel 90-degree large attack angle coupling 360-degree rolling device | |
| CN111017256B (en) | Pneumatic lift resistance test device with controllable and adjustable aircraft model pitch angle | |
| CN103837322A (en) | Hydrodynamic performance testing method of water surface aircraft | |
| CN104180977A (en) | Multifunctional linear electromechanical actuator performance test bench | |
| CN110561097B (en) | Device and method for tightening alignment nut of aircraft engine link mechanism | |
| CN115140323A (en) | Pneumatic characteristic testing device of tension torque decoupling type single rotor system | |
| CN111114857B (en) | Manual-adjustment pneumatic characteristic measuring device for rotor system of split Mars aircraft | |
| CN208795498U (en) | A kind of dynamic attitude-simulating turntable for the test of large scale equipment ground performance | |
| Tsai et al. | Whirl flutter test of the Maryland tiltrotor rig: Overview | |
| CN114910244A (en) | Full-aircraft model gust load alleviation wind tunnel test method based on forward-looking feedback | |
| CN212172579U (en) | Comprehensive test bed for oil-electricity hybrid power transmission system of rotary wing aircraft | |
| CN210258828U (en) | Four rotor wing vibration detection control device based on multisensor | |
| CN110562484B (en) | Hovering characteristic testing device for testing single-shaft rotor system of Mars aircraft | |
| CN111688951A (en) | Multifunctional unmanned aerial vehicle lift force measuring device | |
| CN110606222B (en) | Pneumatic characteristic testing device for single rotor system of suspended Mars aircraft | |
| CN115754710A (en) | Coaxial motor testing mechanism and brushless motor | |
| CN100422711C (en) | Apparatus for fatigue test of horizontal hinge bearing of helicopter | |
| CN215952979U (en) | Radial static stiffness testing device of foil air bearing | |
| CN213323764U (en) | Multifunctional unmanned aerial vehicle lift force measuring device | |
| CN118457942B (en) | Device and method for testing structural strength of control surface of navigation aircraft | |
| CN107521719B (en) | Wind power loading device for wing ground resonance test |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |