CN109050968A - A kind of rotor measuring system of coaxial helicopter - Google Patents
A kind of rotor measuring system of coaxial helicopter Download PDFInfo
- Publication number
- CN109050968A CN109050968A CN201810546775.7A CN201810546775A CN109050968A CN 109050968 A CN109050968 A CN 109050968A CN 201810546775 A CN201810546775 A CN 201810546775A CN 109050968 A CN109050968 A CN 109050968A
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- blade
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- rotor
- coaxial helicopter
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Length Measuring Devices By Optical Means (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
Abstract
The invention discloses a kind of rotor measuring systems of coaxial helicopter, comprising: data collection terminal, data application end, terminal；Data collection terminal includes Distance-sensing unit, Fibre Optical Sensor unit, sensing directional unit, and the data transmission unit is sent to terminal by the way of wired or wireless, by blade tip gap information, blade strain information and azimuth information；Terminal includes computer unit, and the computer unit carries out information exchange for receiving and being further processed blade tip gap information, blade strain information transmitted by data transmission unit and azimuth information, and with helicopter flight control system.The present invention has many advantages, such as that measurement accuracy is high, security performance is high.
Description
Technical field
The present invention relates to rotor field of measuring technique, specifically the rotor measurements of a kind of coaxial helicopter
System.
Background technique
Coaxial helicopter essential characteristic is: two secondary identical rotors are mounted on same root one on the other
It is at regular intervals between two rotors in rotor shaft.The direction of rotation of two secondary rotors is on the contrary, their reaction torque can offset each other.
In this way, just not needing to refill tail-rotor.The directional control of helicopter by upper and lower two rotor always away from differential change complete.
Coaxial helicopter major advantage be it is compact-sized, outer dimension is small.This helicopter is because of No Tail Rotor, institute
Long tail boom is filled also just not reveal, fuselage length can also greatly shorten.There are two secondary rotors to generate lift, every pair rotor
Diameter can also shorten.Airframe components can compactly be arranged in helicopter center of gravity, so flight stability is good, be also convenient for grasping
It is vertical.Compared with single rotor tail-rotor helicopter, driving efficiency obviously increases.Furthermore.Co-axial helicopter aerodynamic force pair
Claim, hovering efficiency is also relatively high.
It, can dynamic measurement rotor intercuspal space in order to improve security performance in coaxial helicopter flight course
And blade aerodynamic load, using current measuring system, generally existing measurement accuracy is low, and the bad defect of measurement effect needs to carry out
It is effective to improve.
Summary of the invention
The purpose of the present invention is to solve the defects that low measurement accuracy in the prior art, measurement effect are poor, mention
It solves the above problems for a kind of rotor measuring system of coaxial helicopter.
To achieve the goals above, technical scheme is as follows: the invention discloses a kind of DCB Specimen close coupled type is straight
The rotor measuring system of the machine of liter, comprising: data collection terminal, data application end, terminal；
The data collection terminal includes Distance-sensing unit, Fibre Optical Sensor unit, sensing directional unit, the distance
Sensing unit for dynamically measure blade tip gap data, the Fibre Optical Sensor unit include at least one fibre strain measuring point and
At least one fiber optic temperature measuring point, for dynamically measuring the strain data of blade, the sensing directional unit is straight for measuring
Rise the azimuth information of machine rotor wing rotation；
The data application end includes data processing unit, data transmission unit, and the data processing unit is used for
Blade tip gap letter is calculated in the output signal for receiving and handling Distance-sensing unit, Fibre Optical Sensor unit, sensing directional unit
Breath, blade strain information and azimuth information are further sent to data transmission unit, and the data transmission unit is using wired
Or wirelessly, blade tip gap information, blade strain information and azimuth information are sent to terminal；
The terminal includes computer unit, and the computer unit is for receiving and being further processed number
According to blade tip gap information, blade strain information transmitted by transmission unit and azimuth information, and and helicopter flight control system
Carry out information exchange.
Preferably, the Distance-sensing unit includes light-beam transmitter and beam receiver, the beam radiation
Device and beam receiver are installed in the following table of at least a piece of transmitting blade of the second main rotor of coaxial helicopter
Face shines towards the upper surface of at least a piece of reflection blade of the first main rotor of coaxial helicopter, beam reception
Device receives the reflected light signal of the reflection blade surface, and data processing unit is emitted by measuring beam and the received time,
The round-trip distance of light beam is calculated, for dynamically measuring the blade tip gap of the transmitting blade and the reflection blade.
Preferably, the Fibre Optical Sensor unit uses fibre optical sensor, the fibre optical sensor is for being mounted on
The of the upper surface of at least a piece of blade of first main rotor of coaxial helicopter or coaxial helicopter
The lower surface of at least a piece of blade of two main rotors, for dynamically measuring the strain of blade.
Preferably, the fibre optical sensor can also be embedded to the first main rotor or the second master of coaxial helicopter
Inside at least a piece of blade of rotor, for dynamically measuring the strain of blade.
Preferably, the sensing directional unit uses aspect sensor, the aspect sensor is mounted on DCB Specimen
On second main rotor of co-axial helicopter, the gyrobearing information between the first main rotor and the second main rotor is measured.
Preferably, passing through cable reality between the data processing unit and the light-beam transmitter and beam receiver
Now power supply and data transmission, the cable can Surface Mount or be embedded to coaxial helicopter the second main rotor.
Preferably, the wired or wireless mode of the data transmission unit include: light or electric slip ring mode, it is wireless
Electric frequency communication mode or optical communication mode.
Preferably, the azimuth information of the sensing directional unit output can be used for triggering the Distance-sensing unit
Carry out blade tip clearance measurement.
The present invention has the advantage that compared with prior art
The invention discloses a kind of rotor measuring system of coaxial helicopter by using Distance-sensing unit,
Fibre Optical Sensor unit, sensing directional unit carry out blade tip gap information, blade strain information and azimuth information acquisition, and are sent to
Data application end carries out data processing and is transmitted to terminal, to realize dynamic measurement coaxial double-rotor helicopter
Then the purpose in blade tip gap and blade aerodynamic load carries out information exchange by computer unit and helicopter flight control system, whole
A measuring system precision greatly improves, and effect is relatively good, and security performance is stronger.
Detailed description of the invention
Fig. 1 is a kind of process flow diagram of the rotor measuring system of coaxial helicopter of the present invention；
Fig. 2 is the main view of coaxial helicopter.
Appended drawing reference are as follows: data collection terminal 1, data application end 2, terminal 3, Distance-sensing unit 11, optical fiber pass
Feel unit 12, sensing directional unit 13, data processing unit 21, data transmission unit 22, computer unit 31, light-beam transmitter
111, beam receiver 112, fibre optical sensor 121, aspect sensor 131.
Specific embodiment
The effect of to make to structure feature of the invention and being reached, has a better understanding and awareness, to preferable
Examples and drawings cooperation detailed description, is described as follows:
As shown in Figure 1, the invention discloses a kind of rotor measuring systems of coaxial helicopter, comprising: data
Collection terminal 1, data application end 2, terminal 3；
The data collection terminal 1 includes Distance-sensing unit 11, Fibre Optical Sensor unit 12, sensing directional unit 13, institute
The Distance-sensing unit 11 stated includes at least one light for dynamically measuring blade tip gap data, the Fibre Optical Sensor unit 12
Fibre strain measuring point and at least one fiber optic temperature measuring point, for dynamically measuring the strain data of blade, the sensing directional list
Member 13 is for measuring the azimuth information of lifting airscrew rotation；
The data application end 2 includes data processing unit 21, data transmission unit 22, the data processing unit
21, for receiving and handling the output signal of Distance-sensing unit 11, Fibre Optical Sensor unit 12, sensing directional unit 13, calculate
To blade tip gap information, blade strain information and azimuth information, it is further sent to data transmission unit 22, the data pass
Defeated unit 22 is sent to calculating by the way of wired or wireless, by blade tip gap information, blade strain information and azimuth information
Machine terminal 3；
The terminal 3 include computer unit 31, the computer unit 31 for receive and it is further
Handle blade tip gap information, blade strain information and azimuth information transmitted by data transmission unit 22, and and helicopter flight
Control system carries out information exchange.
Distance-sensing unit 11 is for dynamically measuring blade tip gap data, and Fibre Optical Sensor unit 12 is for dynamically measuring blade
Strain data, sensing directional unit 13 be used for measure lifting airscrew rotation azimuth information, Distance-sensing unit 11, optical fiber
The blade tip gap information of measurement, blade strain information and azimuth information are sent to number by sensing unit 12, sensing directional unit 13
According to processing unit 21, after processing, blade tip gap information, blade strain information and azimuth information will be calculated, further send
To data transmission unit 22, data transmission unit 22 is by the way of wired or wireless, by blade tip gap information, blade strain letter
Breath and azimuth information are sent to computer unit 31, computer unit 31 receive be further processed after data blade tip gap information,
Blade strain information and azimuth information, and information exchange is carried out with helicopter flight control system, it is measured to realize dynamic
The blade tip gap of coaxial double-rotor helicopter and the purpose of blade aerodynamic load, precision greatly improve, and effect is relatively good, and safety
It can also greatly improve.
Preferably, the Distance-sensing unit 11 includes light-beam transmitter 111 and beam receiver 112, it is described
Beam radiation device 111 and beam receiver 112 are installed at least the one of the second main rotor 16 of coaxial helicopter
Piece emits the lower surface of blade, reflects the upper of blade towards at least a piece of of the second main rotor 15 of coaxial helicopter
Surface light emitting, beam receiver 112 receive the reflected light signal of the reflection blade surface, and data processing unit 21 passes through measurement
Beam emissions and received time calculate the round-trip distance of light beam, for dynamically measuring the transmitting blade and the reflection blade
Blade tip gap.
Preferably, the Fibre Optical Sensor unit 12 uses fibre optical sensor 121, the fibre optical sensor 121 is used
Upper surface or DCB Specimen close coupled type in at least a piece of blade for the second main rotor 15 for being mounted on coaxial helicopter
The lower surface of at least a piece of blade of second main rotor 16 of helicopter, for dynamically measuring the strain of blade.
Preferably, the fibre optical sensor 121 can also be embedded to coaxial helicopter the second main rotor 15 or
Inside at least a piece of blade of second main rotor 16, for dynamically measuring the strain of blade.
Preferably, the sensing directional unit 13 uses aspect sensor 131, the aspect sensor 131 is installed
On the second main rotor 16 of coaxial helicopter, the rotation between the second main rotor 15 and the second main rotor 16 is measured
Azimuth information.
Preferably, leading between the data processing unit 21 and the light-beam transmitter 111 and beam receiver 112
Cross cable realize power supply and data transmission, the cable can Surface Mount or be embedded to coaxial helicopter the second main rotation
The wing.
Preferably, the wired or wireless mode of the data transmission unit 22 includes: light or electric slip ring mode, nothing
Line electric frequency communication mode or optical communication mode.
Preferably, the azimuth information that the sensing directional unit 13 exports can be used for triggering the Distance-sensing list
Member 11 carries out blade tip clearance measurement.
The basic principles, main features and advantages of the present invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and what is described in the above embodiment and the description is only the present invention
Principle, various changes and improvements may be made to the invention without departing from the spirit and scope of the present invention, these variation and
Improvement is both fallen in the range of claimed invention.The present invention claims protection scope by appended claims and its
Equivalent defines.
Claims (8)
1. a kind of rotor measuring system of coaxial helicopter, comprising: data collection terminal (1), data application end (2),
Terminal (3)；
It is characterized by: the data collection terminal (1) includes Distance-sensing unit (11), Fibre Optical Sensor unit (12), orientation
Sensing unit (13), the Distance-sensing unit (11) is for dynamically measuring blade tip gap data, the Fibre Optical Sensor list
First (12) include at least one fibre strain measuring point and at least one fiber optic temperature measuring point, for dynamically measuring the dependent variable of blade
According to the sensing directional unit (13) is used to measure the azimuth information of lifting airscrew rotation；
The data application end (2) includes data processing unit (21), data transmission unit (22), the data processing list
First (21) are used to receive and handle the output of Distance-sensing unit (11), Fibre Optical Sensor unit (12), sensing directional unit (13)
Signal is calculated blade tip gap information, blade strain information and azimuth information, is further sent to data transmission unit
(22), the data transmission unit (22) is by the way of wired or wireless, by blade tip gap information, blade strain information and
Azimuth information is sent to terminal (3)；
The terminal (3) includes computer unit (31), and the computer unit (31) goes forward side by side one for receiving
Blade tip gap information, blade strain information and azimuth information transmitted by step processing data transmission unit (22), and and helicopter
Flight control system carries out information exchange.
2. a kind of rotor measuring system of coaxial helicopter according to claim 1, it is characterised in that: described
Distance-sensing unit (11) include light-beam transmitter (111) and beam receiver (112), the beam radiation device (111)
At least a piece of transmitting blade of the second main rotor (16) of coaxial helicopter is installed in beam receiver (112)
Lower surface, towards coaxial helicopter the second main rotor (15) it is at least a piece of reflection blade upper surface send out
Light, beam receiver (112) receive the reflected light signal of the reflection blade surface, and data processing unit (21) passes through measurement light
Beam transmitting and received time, the round-trip distance of light beam is calculated, for dynamically measuring the transmitting blade and the reflection blade
Blade tip gap.
3. a kind of rotor measuring system of coaxial helicopter according to claim 1, it is characterised in that: described
Fibre Optical Sensor unit (12) use fibre optical sensor (121), the fibre optical sensor (121) is total for being mounted on DCB Specimen
The upper surface of at least a piece of blade of the second main rotor (15) of shaft type helicopter or the second master of coaxial helicopter
The lower surface of at least a piece of blade of rotor (16), for dynamically measuring the strain of blade.
4. a kind of rotor measuring system of coaxial helicopter according to claim 3, it is characterised in that: described
The second main rotor (15) or the second main rotor (16) that fibre optical sensor (121) can also be embedded to coaxial helicopter are extremely
Inside few a piece of blade, for dynamically measuring the strain of blade.
5. a kind of rotor measuring system of coaxial helicopter according to claim 1, it is characterised in that: described
Sensing directional unit (13) uses aspect sensor (131), and it is straight that the aspect sensor (131) is mounted on DCB Specimen close coupled type
On the second main rotor (16) of the machine of liter, the gyrobearing information between the second main rotor 15 and the second main rotor (16) is measured.
6. a kind of rotor measuring system of coaxial helicopter according to claim 1, it is characterised in that: described
Data processing unit (21) and the light-beam transmitter (111) and beam receiver (112) between by cable realize power supply and
Data transmission, the cable can Surface Mount or be embedded to coaxial helicopter the second main rotor.
7. a kind of rotor measuring system of coaxial helicopter according to claim 1, it is characterised in that: described
Data transmission unit (22) wired or wireless mode include: light or electric slip ring mode, radio frequency communication mode or
Optical communication mode.
8. a kind of rotor measuring system of coaxial helicopter according to claim 5, it is characterised in that: described
The azimuth information of sensing directional unit (13) output can be used for triggering the Distance-sensing unit (11) and carry out blade tip gap
Measurement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810546775.7A CN109050968A (en) | 2018-05-31 | 2018-05-31 | A kind of rotor measuring system of coaxial helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810546775.7A CN109050968A (en) | 2018-05-31 | 2018-05-31 | A kind of rotor measuring system of coaxial helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109050968A true CN109050968A (en) | 2018-12-21 |
Family
ID=64819830
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810546775.7A Pending CN109050968A (en) | 2018-05-31 | 2018-05-31 | A kind of rotor measuring system of coaxial helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109050968A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109580057A (en) * | 2019-01-09 | 2019-04-05 | 武汉理工大学 | Lifting airscrew load monitoring system and method based on Built-In Optical-Fiber Sensors Used |
| CN112224446A (en) * | 2020-10-16 | 2021-01-15 | 中国直升机设计研究所 | High-speed coaxial dual-rotor blade tip distance measuring method based on phase distance measuring principle |
| CN113086244A (en) * | 2021-04-20 | 2021-07-09 | 中国直升机设计研究所 | Real-time estimation method for tip spacing of coaxial rotor |
| CN114322867A (en) * | 2021-11-22 | 2022-04-12 | 天津大学 | Coaxial double-rotor-wing tip distance measuring system and method based on ultrasonic measurement |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2415053C1 (en) * | 2009-09-23 | 2011-03-27 | Юрий Александрович Борисов | Method to measure non-in-track condition of helicopter rotor blades and device for its realisation |
| CN206311296U (en) * | 2016-09-30 | 2017-07-07 | 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 wind tunnel test platform transmission mechanism |
| CN207191485U (en) * | 2017-09-13 | 2018-04-06 | 陕西千山航空电子有限责任公司 | A kind of rotor system test equipment |
| CN107933957A (en) * | 2017-12-21 | 2018-04-20 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter blade aerodynamic load flight actual measurement system and its measurement method |
-
2018
- 2018-05-31 CN CN201810546775.7A patent/CN109050968A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2415053C1 (en) * | 2009-09-23 | 2011-03-27 | Юрий Александрович Борисов | Method to measure non-in-track condition of helicopter rotor blades and device for its realisation |
| CN206311296U (en) * | 2016-09-30 | 2017-07-07 | 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 wind tunnel test platform transmission mechanism |
| CN207191485U (en) * | 2017-09-13 | 2018-04-06 | 陕西千山航空电子有限责任公司 | A kind of rotor system test equipment |
| CN107933957A (en) * | 2017-12-21 | 2018-04-20 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter blade aerodynamic load flight actual measurement system and its measurement method |
Non-Patent Citations (2)
| Title |
|---|
| 张勇,宋瑞华,孙江: "直升机桨叶运动参数监测仪设计", 《海军航空工程学院学报》 * |
| 程卫真: "基于光纤光栅的直升机桨叶应变试飞研究", 《应用力学学报》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109580057A (en) * | 2019-01-09 | 2019-04-05 | 武汉理工大学 | Lifting airscrew load monitoring system and method based on Built-In Optical-Fiber Sensors Used |
| CN112224446A (en) * | 2020-10-16 | 2021-01-15 | 中国直升机设计研究所 | High-speed coaxial dual-rotor blade tip distance measuring method based on phase distance measuring principle |
| CN112224446B (en) * | 2020-10-16 | 2022-06-21 | 中国直升机设计研究所 | High-speed coaxial dual-rotor blade tip distance measuring method based on phase distance measuring principle |
| CN113086244A (en) * | 2021-04-20 | 2021-07-09 | 中国直升机设计研究所 | Real-time estimation method for tip spacing of coaxial rotor |
| CN113086244B (en) * | 2021-04-20 | 2022-07-29 | 中国直升机设计研究所 | Real-time estimation method for tip spacing of coaxial rotor |
| CN114322867A (en) * | 2021-11-22 | 2022-04-12 | 天津大学 | Coaxial double-rotor-wing tip distance measuring system and method based on ultrasonic measurement |
| CN114322867B (en) * | 2021-11-22 | 2024-03-22 | 天津大学 | Coaxial double-rotor-wing tip distance measurement system and method based on ultrasonic measurement |
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Application publication date: 20181221 |