CN109141859A - A kind of helicopter circular rector tail boom experiment test device - Google Patents
A kind of helicopter circular rector tail boom experiment test device Download PDFInfo
- Publication number
- CN109141859A CN109141859A CN201811135330.6A CN201811135330A CN109141859A CN 109141859 A CN109141859 A CN 109141859A CN 201811135330 A CN201811135330 A CN 201811135330A CN 109141859 A CN109141859 A CN 109141859A
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- tail boom
- helicopter
- circular rector
- support plate
- fixed
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- 238000012360 testing method Methods 0.000 title claims abstract description 10
- 238000002474 experimental method Methods 0.000 title claims abstract description 9
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 15
- 230000008878 coupling Effects 0.000 claims abstract description 10
- 238000010168 coupling process Methods 0.000 claims abstract description 10
- 238000005859 coupling reaction Methods 0.000 claims abstract description 10
- 230000005611 electricity Effects 0.000 claims description 3
- 238000011160 research Methods 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012913 prioritisation Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of helicopter circular rector tail boom experiment test devices, include rotor module, fixed module, shaft coupling, torque sensor and helicopter circular rector tail boom；Fixed module includes pedestal, the first support plate, the second support plate and top plate；First support plate, the second support plate are arranged in parallel, and lower end is and the upper surface of pedestal is vertically connected, upper end is vertically connected with the lower end surface of top plate；Torque sensor is fixed on the lower end surface of top plate；Helicopter circular rector tail boom is arranged between pedestal and torque sensor, and the lower section on head is connect by bearing with pedestal, top is connect by shaft coupling with torque sensor；Rotor module is fixed on the upper surface of top plate.The present invention is simple and practical, safe and reliable, at low cost, can not only demonstrate the working principle of circular rector tail boom, also can measure the torque of circular rector tail boom, can make scientific research and teaching purposes, greatly improve the efficiency during research and teaching.
Description
Technical field
The present invention relates to aviation fields, and in particular to a kind of experimental provision for measuring circular rector tail boom torque.
Background technique
In recent years, with the fast development of aviation industry, helicopter circular rector tail boom can balance antitorque of rotor and ratio because of it
The advantages that common tail-rotor structure is simpler and safer reliable, noise is smaller and get the attention.But also relatively lacks close at present
In the experiment test device of circular rector tail boom.
Summary of the invention
Problem to be solved by this invention is to lack for current about this problem of the experiment test device of circular rector tail boom,
A kind of experimental provision measuring circular rector tail boom torque is provided.
The present invention uses following technical scheme in order to solve the above problem:
A kind of helicopter circular rector tail boom experiment test dress includes rotor module, fixed module, shaft coupling, torque sensor and straight
Rise machine circular rector tail boom；
The fixed module includes pedestal, the first support plate, the second support plate and top plate；
First support plate, the second support plate are arranged in parallel, the lower end vertically connected, upper end with the upper surface of the pedestal
Vertically it is connected with the lower end surface of the top plate；
The torque sensor is fixed on the lower end surface of the top plate；
The helicopter circular rector tail boom is arranged between the pedestal and torque sensor, and the lower section on head passes through bearing and bottom
Seat connection, top are connect by shaft coupling with torque sensor；
The rotor module is fixed on the upper surface of the top plate, includes several blades, propeller hub, battery, signal receiver, electricity
Machine and control unit；
The root of several blades is connected with the propeller hub, the output shaft fixed connection of the shaft of the propeller hub and the motor；
The signal receiver passes it to the control module for receiving external command；
Described control unit is electrically connected with battery, signal receiver, motor respectively, for according to the external command control received
Make the motor work.
It is tested as a kind of helicopter circular rector tail boom experiment of the present invention and fills further prioritization scheme, in the rotor module
The quantity of blade is two.
The invention adopts the above technical scheme compared with prior art, has following technical effect that
The present invention is simple, practical, safe and reliable, at low cost, can not only demonstrate the working principle of circular rector tail boom, also can measure ring
The torque for measuring tail boom can make scientific research and teaching purposes, greatly improve the efficiency during research and teaching.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is shaft side figure of the invention.
In figure, 1- helicopter circular rector tail boom, 2- blade, 3- propeller hub, 4- battery, 5- signal receiver, 6- motor, the top 7-
Plate, the first support plate of 8-, the second support plate of 9-, 10- shaft coupling, 11- torque sensor, 12- pedestal, 13- bearing, 14- are gone straight up to
The ducted fan of machine circular rector tail boom, the slit on 15- helicopter circular rector tail boom.
Specific embodiment
Technical solution of the present invention is described in further detail with reference to the accompanying drawing:
As shown in Figure 1 and Figure 2, the invention discloses a kind of helicopter circular rector tail booms to test test dress, includes rotor module, fixation
Module, shaft coupling, torque sensor and helicopter circular rector tail boom.
The fixed module includes pedestal, the first support plate, the second support plate and top plate；
First support plate, the second support plate are arranged in parallel, the lower end vertically connected, upper end with the upper surface of the pedestal
Vertically it is connected with the lower end surface of the top plate；
The torque sensor is fixed on the lower end surface of the top plate；
The helicopter circular rector tail boom is arranged between the pedestal and torque sensor, and the lower section on head passes through bearing and bottom
Seat connection, top are connect by shaft coupling with torque sensor.
The rotor module is fixed on the upper surface of the top plate, is received comprising several blades, propeller hub, battery, signal
Device, motor and control unit；
The root of several blades is connected with the propeller hub, the output shaft fixed connection of the shaft of the propeller hub and the motor；
The signal receiver passes it to the control module for receiving external command；
Described control unit is electrically connected with battery, signal receiver, motor respectively, for according to the external command control received
Make the motor work.
The quantity of blade is two in the rotor module.
When work, signal receiver receives external command and passes to control unit, and control unit is according to order control electricity
Machine work, drives rotor blade high speed rotation, generates downward air-flow.It allows helicopter circular rector tail boom to work at this time, starts its culvert
Road fan, outside air enters tail boom through ducted fan compression, so that the slot injection of tail boom side goes out air-flow, it is high-speed rotating
The downward air-flow that rotor blade generates accelerates through the side jet-stream wind of tail boom side slit, and two sidewind of tail boom is caused to generate speed
It is poor to spend, and then leads to pressure difference, generates torque.Since pedestal is fixed, helicopter circular rector tail boom is connect by bearing with pedestal, because
This is installed on the shaft coupling above helicopter circular rector tail boom and passes the torque that the torque that circular rector tail boom system generates is transferred to top
Sensor can measure the torque of circular rector tail boom system generation.
Those skilled in the art can understand that unless otherwise defined, all terms used herein (including skill
Art term and scientific term) there is meaning identical with the general understanding of those of ordinary skill in fields of the present invention.Also
It should be understood that those terms such as defined in the general dictionary should be understood that have in the context of the prior art
The consistent meaning of meaning will not be explained in an idealized or overly formal meaning and unless defined as here.
Above-described specific embodiment has carried out further the purpose of the present invention, technical scheme and beneficial effects
It is described in detail, it should be understood that being not limited to this hair the foregoing is merely a specific embodiment of the invention
Bright, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection scope within.
Claims (2)
1. a kind of helicopter circular rector tail boom experiment test dress, which is characterized in that include rotor module, fixed module, shaft coupling, torsion
Square sensor and helicopter circular rector tail boom；
The fixed module includes pedestal, the first support plate, the second support plate and top plate；
First support plate, the second support plate are arranged in parallel, the lower end vertically connected, upper end with the upper surface of the pedestal
Vertically it is connected with the lower end surface of the top plate；
The torque sensor is fixed on the lower end surface of the top plate；
The helicopter circular rector tail boom is arranged between the pedestal and torque sensor, and the lower section on head passes through bearing and bottom
Seat connection, top are connect by shaft coupling with torque sensor；
The rotor module is fixed on the upper surface of the top plate, includes several blades, propeller hub, battery, signal receiver, electricity
Machine and control unit；
The root of several blades is connected with the propeller hub, the output shaft fixed connection of the shaft of the propeller hub and the motor；
The signal receiver passes it to the control module for receiving external command；
Described control unit is electrically connected with battery, signal receiver, motor respectively, for according to the external command control received
Make the motor work.
2. helicopter circular rector tail boom experiment test dress according to claim 1, which is characterized in that paddle in the rotor module
The quantity of leaf is two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811135330.6A CN109141859A (en) | 2018-09-28 | 2018-09-28 | A kind of helicopter circular rector tail boom experiment test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811135330.6A CN109141859A (en) | 2018-09-28 | 2018-09-28 | A kind of helicopter circular rector tail boom experiment test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109141859A true CN109141859A (en) | 2019-01-04 |
Family
ID=64813228
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811135330.6A Pending CN109141859A (en) | 2018-09-28 | 2018-09-28 | A kind of helicopter circular rector tail boom experiment test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109141859A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20090039563A (en) * | 2007-10-18 | 2009-04-22 | 한국항공우주연구원 | Helicopter tail rotor test rig |
| CN102774509A (en) * | 2012-06-28 | 2012-11-14 | 南京航空航天大学 | Performance test bench for reaction torque device of helicopter |
| 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 |
| CA2802172A1 (en) * | 2012-01-12 | 2013-07-12 | Bell Helicopter Textron Inc. | System and method of measuring and monitoring torque in a rotorcraft drive system |
| CN203572672U (en) * | 2013-11-12 | 2014-04-30 | 大连浦州航空科技有限公司 | 300 kilogram helicopter comprehensive test platform |
| CN105241631A (en) * | 2015-11-04 | 2016-01-13 | 中航维拓（北京）科技有限责任公司 | Helicopter tail rotor vortex ring state testing system |
| CN105923169A (en) * | 2016-07-06 | 2016-09-07 | 西安交通大学 | Testing platform and testing method for power supply system of gasoline-electric hybrid unmanned aerial vehicle |
| CN108058824A (en) * | 2017-12-19 | 2018-05-22 | 合肥工业大学 | A kind of integrated electric motor deceleration system for empennage of helicopter |
| CN208937301U (en) * | 2018-09-28 | 2019-06-04 | 南京航空航天大学 | A kind of helicopter circular rector tail boom experiment test device |
-
2018
- 2018-09-28 CN CN201811135330.6A patent/CN109141859A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20090039563A (en) * | 2007-10-18 | 2009-04-22 | 한국항공우주연구원 | Helicopter tail rotor test rig |
| CA2802172A1 (en) * | 2012-01-12 | 2013-07-12 | Bell Helicopter Textron Inc. | System and method of measuring and monitoring torque in a rotorcraft drive system |
| CN102774509A (en) * | 2012-06-28 | 2012-11-14 | 南京航空航天大学 | Performance test bench for reaction torque device of helicopter |
| 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 |
| CN203572672U (en) * | 2013-11-12 | 2014-04-30 | 大连浦州航空科技有限公司 | 300 kilogram helicopter comprehensive test platform |
| CN105241631A (en) * | 2015-11-04 | 2016-01-13 | 中航维拓（北京）科技有限责任公司 | Helicopter tail rotor vortex ring state testing system |
| CN105923169A (en) * | 2016-07-06 | 2016-09-07 | 西安交通大学 | Testing platform and testing method for power supply system of gasoline-electric hybrid unmanned aerial vehicle |
| CN108058824A (en) * | 2017-12-19 | 2018-05-22 | 合肥工业大学 | A kind of integrated electric motor deceleration system for empennage of helicopter |
| CN208937301U (en) * | 2018-09-28 | 2019-06-04 | 南京航空航天大学 | A kind of helicopter circular rector tail boom experiment test device |
Non-Patent Citations (1)
| Title |
|---|
| 李家春: "直升机环量控制尾梁反扭矩系统研究", 中国博士学位论文全文数据库 工程科技Ⅱ辑, 15 February 2016 (2016-02-15), pages 99 - 120 * |
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