CN105070003B - The Transmission system of co-axial helicopter rotor measuring signal - Google Patents
The Transmission system of co-axial helicopter rotor measuring signal Download PDFInfo
- Publication number
- CN105070003B CN105070003B CN201510251615.6A CN201510251615A CN105070003B CN 105070003 B CN105070003 B CN 105070003B CN 201510251615 A CN201510251615 A CN 201510251615A CN 105070003 B CN105070003 B CN 105070003B
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- Prior art keywords
- signal
- outer shaft
- measuring signal
- rotor
- lower rotor
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Abstract
The present invention relates to a kind of Transmission systems of co-axial helicopter rotor measuring signal, to solve the problems, such as fault of construction caused by the wiring of prior art signal transmssion line is complicated, signal transmssion line replacement difficulty is big and notch.The system includes lower rotor measuring signal transmitting device, the lower rotor measuring signal transmitting device includes lower rotor signal transmssion line and reception and the wireless transport module for sending backspin wing measuring signal, which is arranged on the outer wall of the outer shaft between outer shaft top and outer shaft sleeve top.The present invention receives and sends backspin wing measuring signal using wireless transport module, realizes the wireless transmission of lower rotor measuring signal.Therefore it does not need to slot on outer shaft or outer shaft sleeve, avoids fault of construction problem.And wiring is succinct, is conveniently replaceable or adjusts.It is arranged on the outer shaft between outer shaft top and outer shaft sleeve top due to wireless transport module, so not interfering with the relative motion between outer shaft and outer shaft sleeve.
Description
Technical field
The present invention relates to a kind of Transmission systems of co-axial helicopter rotor measuring signal.
Background technique
Compared with single rotor tail-rotor helicopter, co-axial helicopter using two secondary rotors of upper and lower contrarotation come
Rotor torque is balanced, so being not required to tail-rotor.Such structure is with compact-sized, convenient for safeguarding, aerodynamic characteristics are symmetrical, hovering is steady
The qualitative good, advantages such as accident rate is low.Certainly, co-axial helicopter also has its unavoidable disadvantage, more prominent disadvantage be it is upper,
There are aerodynamic interferences between lower rotor, and since the operating mechanism of two secondary rotors concentrates on an axis, lead to that structure is complicated
And it is intensive.Therefore, in co-axial helicopter R&D process a large amount of experimental study be it is essential, the most common mode is
It establishes Test-bed and carries out ground experiment.
When establishing co-axial helicopter Test-bed, the reasonable Arrangement of signal transmssion line is that emphasis is also difficult point.Dan Xuan
The signal transmssion line of wing tail-rotor helicopter Test-bed leads to the bottom end of Test-bed from hollow inner shaft, then passes through
The modes such as collecting ring are acquired the measuring signal transmitted on signal transmssion line.But it due to co-axial helicopter interviews
The internal sleeve for testing the outer shaft connecting on platform with lower rotor is equipped with the inner shaft connecting with upper rotor, and inner shaft therein and outer axle steer are
Opposite, therefore lower rotor can not be by the way of being routed in axis.
It being found by investigation, rotor mostly uses the mode being routed outside axis under existing co-axial helicopter Test-bed,
It needs to slot on outer shaft or outer shaft sleeve in concrete operations, reserves wiring space.But this mode has following lack
It falls into:
(1) signal transmssion line is tediously long, cumbersome,
(2) difficulty according to different experiment increases in demand or replacement signal transmssion line is larger, not very practical；
(3) wiring notch makes Test-bed fault of construction occur, causes stress to be concentrated, is easy to appear fatigue rupture, shadow
The service life of Test-bed is rung, and is possible to jeopardize the safety of experimenter.
Summary of the invention
Complicated, signal transmssion line replacement hardly possible that the technical problem to be solved by the present invention is to the wirings of prior art signal transmssion line
Spend fault of construction problem caused by big and notch.
In order to solve the above technical problems, the invention proposes a kind of transmission systems of co-axial helicopter rotor measuring signal
System.
The Transmission system of co-axial helicopter rotor measuring signal of the present invention, including lower rotor measuring signal transmitting device,
The lower rotor measuring signal transmitting device includes lower rotor signal transmssion line and the reception for carrying lower rotor measuring signal
And send the wireless transport module of the lower rotor measuring signal；Wherein, wireless transport module setting on outer shaft top and
On the outer wall of outer shaft between outer shaft sleeve top.
Further, the Transmission system further includes equal with the lower rotor signal transmssion line, the wireless transport module
The signal picker of circuit connection, to acquire the lower rotor measuring signal on the lower rotor signal transmssion line, and will acquisition
To lower rotor measuring signal be sent to wireless transport module；The signal picker is arranged on outer shaft top and outer shaft sleeve top
On the outer wall of outer shaft between end.
Further, the signal picker, which is built-in with, converts digital signal for collected lower rotor measuring signal
Analog-to-digital conversion module.
Still further, the wireless transport module is built-in with the memory module for storing the digital signal.
Further, the Transmission system further includes upper rotor measuring signal transmitting device, the upper rotor measuring signal
Transmitting device includes the upper rotor signal transmssion line being threaded through inside inner shaft, and the upper rotor signal transmssion line carries rotor
Measuring signal.
Further, the inner shaft is internally provided at least one tee connector.
Further, the upper rotor signal transmssion line classification outside the inner shaft is fixed on propeller hub.
Preferably, the lower rotor signal transmssion line classification is fixed on lower propeller hub.
Preferably, the signal picker is cyclic structure, is disposed around on outer shaft.
Preferably, the wireless transport module is cyclic structure, is disposed around on outer shaft.
The Transmission system of co-axial helicopter rotor measuring signal of the present invention has the advantages that
Firstly, the present invention receives and send backspin wing measuring signal using wireless transport module, lower rotor measurement is realized
The wireless transmission of signal.Since this mode does not need to slot under outer shaft or outer shaft sleeve, avoid due to wiring groove
Fault of construction problem caused by mouthful also improves security performance while extending the service life of Test-bed.
Secondly as wiring is succinct, is conveniently replaceable or adjusts, real by the way of being wirelessly transferred lower rotor measuring signal
It is higher with property.
Finally, due to wireless transport module is arranged on the outer shaft between outer shaft top and outer shaft sleeve top, so
The relative motion between outer shaft and outer shaft sleeve is not interfered with.
Detailed description of the invention
The features and advantages of the present invention will be more clearly understood by referring to the accompanying drawings, and attached drawing is schematically without that should manage
Solution is carries out any restrictions to the present invention, in the accompanying drawings:
Fig. 1 shows the scheme of installation of the Transmission system of co-axial helicopter rotor measuring signal of the present invention；
Fig. 2 shows the enlarged views of A in Fig. 1；
Fig. 3 shows the enlarged view of B in Fig. 1.
Specific embodiment
Below in conjunction with attached drawing, embodiments of the present invention is described in detail.
Embodiment 1
As shown in Figure 1,3, the present embodiment provides a kind of Transmission system of co-axial helicopter rotor measuring signal, the transmission
System includes lower rotor measuring signal transmitting device, which includes carrying lower rotor measuring signal
Lower rotor signal transmssion line 8 and receive and send the wireless transport module 10 of backspin wing measuring signal；
Wherein, the outer of the outer shaft 6 between the top of outer shaft 6 and the top of outer shaft sleeve 5 is arranged in wireless transport module 10
On wall.
In order to understand the above-mentioned technical proposal of the present embodiment, below to the correlation zero on co-axial helicopter Test-bed
Part and its connection relationship do simple introduction, but are not intended as the restriction to above-mentioned technical proposal.
The upper and lower rotor contrarotation of co-axial helicopter, upper rotor are connect with inner shaft 1, and lower rotor is connect with outer shaft 6,
Inner shaft 1 is set in outer shaft 6, and outer shaft 6 is set in outer shaft sleeve 5, and the steering of inner shaft 1 and outer shaft 6 is on the contrary, and outer shaft 6 and outer
Also relative motion between shaft sleeve 5.It is provided with lower propeller hub 7 on outer shaft 6, is provided with propeller hub 2 in inner shaft 1.Lower rotor, outer shaft 6
And lower propeller hub 7 rotates synchronously, upper rotor, inner shaft 1 and upper propeller hub 2 rotate synchronously.
Transmission system provided in this embodiment has the advantage that
Firstly, the present invention is received using wireless transport module 10 and sends backspin wing measuring signal, realizes lower rotor and survey
Measure the wireless transmission of signal.Extraneous radio receiver receives the lower rotor measuring signal of the sending of wireless transport module 10,
Computer is imported again to be handled, and ground experiment can be analyzed.Since this mode is not needed in outer shaft 6 or outer shaft
The lower fluting of cylinder 5, therefore the fault of construction problem as caused by wiring notch is avoided, extend the service life of Test-bed
While, also improve security performance.
Secondly as wiring is succinct, is conveniently replaceable or adjusts, real by the way of being wirelessly transferred lower rotor measuring signal
It is higher with property.
Finally, due to which wireless transport module 10 is arranged on the outer wall of outer shaft 6, therefore wireless transport module 10 and outer shaft 6
It rotates synchronously, and because outer shaft 6 and lower rotor rotate synchronously, wireless transport module 10, outer shaft 6 and lower rotor are relatively quiet
Only.Because wireless transport module 10 is arranged on the outer shaft 6 between the top of outer shaft 6 and the top of outer shaft sleeve 5, i.e., without
Line transmission module 10 is arranged in outer shaft 6 and does not enter into the part of outer shaft sleeve 5, so not interfering with outer shaft 6 and outer shaft sleeve 5
Between relative motion.
Lower rotor signal transmssion line 8 is drawn from lower rotor, and lower rotor measurement letter is carried on lower rotor signal transmssion line 8
Number, which is to acquire the measuring signal of the lower dynamic components such as rotor blade and/or lower pitch-change-link, therefore basis
The difference of acquisition component, lower rotor measuring signal are at least a kind of.Meanwhile the present invention is not to the number of wireless transport module 10
It limits, can be one, send all lower rotor measuring signals for receiving；Or it is multiple, each receives hair
Send a kind of lower rotor measuring signal.
How lower rotor measuring signal is acquired without limitation to wireless transport module 10 in the present embodiment, can wirelessly passed
An acquisition unit built in defeated module 10 can also carry out the acquisition work of lower rotor measuring signal using external acquisition module
Make.
Further, when rotated due to outer shaft 6, the wireless transport module 10 being connect with outer shaft 6 will receive it is certain from
Mental and physical efforts, it is possible to wireless transport module 10 can be damaged or to install wireless transport module 10 unstable.So can be by nothing
Line transmission module 10 is set as cyclic structure, is disposed around on outer shaft 6, so that the radial dimension of wireless transport module 10 compared with
It is small, guarantee the stabilization of its working performance as far as possible.
Embodiment 2
As shown in Figure 1,3, the present embodiment further defines that on the basis of above-described embodiment 1
Transmission system provided in this embodiment further includes and lower rotor signal transmssion line 8, the equal circuit of wireless transport module 10
The signal picker 9 of connection, to acquire the lower rotor measuring signal on lower rotor signal transmssion line 8, and will be collected under
Rotor measuring signal is sent to wireless transport module 10；
The outer of the outer shaft 6 between the top of outer shaft 6 and the top of outer shaft sleeve outer shaft cylinder 5 is arranged in signal picker 9
On wall.
The present embodiment measures letter using a kind of external signal picker 9, to the lower rotor on lower rotor signal transmssion line 8
It number is acquired, and collected lower rotor measuring signal is sent to wireless transport module 10.The signal acquisition of this mode
Device 9 has the advantages that flexible, adjustable relative to built-in acquisition unit.
Signal picker 9 is arranged on the outer wall of outer shaft 6, therefore signal picker 9 and outer shaft 6 rotate synchronously, and because
Outer shaft 6 and lower rotor rotate synchronously, so signal picker 9, outer shaft 6 and lower rotor are relatively stationary, coiling will not occur
The problem of.Again because signal picker 9 is arranged on the outer shaft 6 between the top of outer shaft 6 and the top of outer shaft sleeve 5, i.e.,
Signal picker 9 is arranged in outer shaft 6 and does not enter into the part of outer shaft sleeve 5, so not interfering with outer shaft 6 and outer shaft sleeve 5
Between relative motion.Without limitation to the specific location of signal picker 9, for example, can below lower propeller hub 7 40mm it is outer
On 6 outer wall of axis.
The present embodiment is not defined the number of signal picker 9, can be one, for acquiring all backspins
Wing measuring signal；Or it is multiple, each reception sends a kind of lower rotor measuring signal.
Further, the transmission due to the transmission of digital signal relative to analog signal has better anti-interference ability, institute
With analog-to-digital conversion module settable in signal picker 9, for converting digital signal for collected lower rotor measuring signal,
Then digital signal is sent to wireless transport module 10, sends to digital signal.
Further, in order to avoid extraneous radio receiver failure or wireless signal be bad etc., reasons cause transmission to believe
Number loss, memory module can be set in wireless transport module 10, for storing digital signal, avoid losing.
Further, when rotated due to outer shaft 6, the signal picker 9 connecting with outer shaft 6 will receive certain centrifugation
Power, it is possible to signal picker 9 can be damaged or to install signal picker 9 unstable.So can be by signal picker 9
It is set as cyclic structure, is disposed around on outer shaft 6, so that the radial dimension of signal picker 9 is smaller, guarantees its work as far as possible
The stabilization of performance.
Further, according to the difference of acquisition component, lower rotor measuring signal more than one, lower rotor signal transmssion line 8
Also with regard to more than one.In test, rotor signal transmssion line 8 is mixed and disorderly at present or is hard to tell in order to prevent, by lower rotor signal transmssion line
8 taxonomic revisions, and after being fixed on lower propeller hub 7, then import signal picker 9.Specific mode classification can be classified or be adopted with tee connector
With the transmission line of different colours.
Embodiment 3
As shown in Figure 1, 2, the present embodiment further defines that on the basis of above-described embodiment 1
Transmission system provided in this embodiment further includes upper rotor measuring signal transmitting device, upper rotor measuring signal transmission
Device includes the upper rotor signal transmssion line 4 being threaded through inside inner shaft 1, and upper rotor signal transmssion line 4 carries rotor measurement
Signal.
The upper end of inner shaft 1 is arranged in upper propeller hub 2, and upper rotor, upper propeller hub 2 and inner shaft 1 are opposing stationary, draws from upper rotor
Upper rotor signal transmssion line 4 imports inside inner shaft 1 from the top of inner shaft 1, then connect with the collecting ring of 1 bottom end of inner shaft, will be upper
Upper rotor measuring signal on rotor signal transmssion line 4 is exported by collecting ring to external cable reception device, cable network reception
Upper rotor measuring signal is imported computer disposal by equipment, and can be analyzed ground experiment.Rotor measuring signal is on this
The measuring signal of the dynamic components such as rotor blade and/or upper pitch-change-link in acquisition.
Upper rotor measuring signal is transmitted by the way of wire transmission in the present embodiment, using the side of wireless transmission
Formula transmits lower rotor measuring signal, due to wire transmission mode high reliablity, at low cost, wireless transmission method wiring letter
It is clean, avoid fault of construction and be conveniently replaceable, according to the own characteristic of co-axial helicopter, guaranteeing to reduce the same of cost as far as possible
When, improve the overall performance of co-axial helicopter ground experiment platform.
Further, for the ease of arranging, classifying to upper rotor signal transmssion line 4, in being internally provided at least for inner shaft 1
One tee connector 3.There are multiple branch holes on tee connector 3, can play to the classification of upper rotor signal transmssion line 4, fixed effect.
The number of tee connector 3 is set according to the length of inner shaft 1, such as a separated time is respectively set on the top, bottom end and middle part of inner shaft 1
Folder 3.
Further, according to the difference of acquisition component, upper rotor measuring signal more than one, upper rotor signal transmssion line 4
Also just not only one.In order to prevent in test on rotor signal transmssion line 4 it is mixed and disorderly or be hard to tell, by upper rotor signal transmssion line
4 taxonomic revisions, and after being fixed on propeller hub 2, then import the inside of inner shaft 1.Specific mode classification can be classified or be adopted with tee connector 3
With the transmission line of different colours.
In conclusion the invention has the following advantages that
(1) the invention avoids fault of construction problems caused by wiring notch；
(2) wiring is succinct, is conveniently replaceable or adjusts；
(3) centrifugal force that signal picker of the invention, wireless transport module are subject to is small, stable working performance；
(4) digital signal first is converted by lower rotor measuring signal to retransmit, improve the anti-interference ability of signal；
(5) memory module stores digital signal, avoids the loss of signal；
(6) transmission line is combed using tee connector, avoids the mixed and disorderly of transmission line；
(7) corresponding transmission line is classified and is fixed respectively at upper propeller hub or lower propeller hub, further avoid transmission
Line it is mixed and disorderly.
It should be noted that the present invention is applicable not only to the ground experiment of co-axial helicopter, it can also be straight in close coupled type
During the taking a flight test, overhaul or repair etc. of the machine of liter.
It should be appreciated that the technical characteristic in the above various embodiments and embodiment can appoint in the absence of conflict
Meaning combination, the technical solution after combination are still fallen within the protection scope of the present invention.
Although the embodiments of the invention are described in conjunction with the attached drawings, but those skilled in the art can not depart from this hair
Various modifications and variations are made in the case where bright spirit and scope, such modifications and variations are each fallen within by appended claims
Within limited range.
Claims (8)
1. a kind of Transmission system of co-axial helicopter rotor measuring signal, it is characterised in that: passed including lower rotor measuring signal
Defeated device, the lower rotor measuring signal transmitting device include carry the lower rotor signal transmssion line of lower rotor measuring signal with
And receive and send the wireless transport module of the lower rotor measuring signal；
Wherein, the wireless transport module is arranged on the outer wall of the outer shaft between outer shaft top and outer shaft sleeve top；
It further include upper rotor measuring signal transmitting device, the upper rotor measuring signal transmitting device includes being threaded through inside inner shaft
Upper rotor signal transmssion line, the upper rotor signal transmssion line carries rotor measuring signal；Upper propeller hub is set to inner shaft
Upper end, from upper rotor draw upper rotor signal transmssion line from the top of inner shaft import inner shaft inside, then with inner shaft bottom end
Collecting ring connection, the upper rotor measuring signal on upper rotor signal transmssion line is exported into wired connecing to outside by collecting ring
Receiving unit；
Wherein: it further include the signal picker with the lower rotor signal transmssion line, the equal circuit connection of the wireless transport module,
It is sent to acquire the lower rotor measuring signal on the lower rotor signal transmssion line, and by collected lower rotor measuring signal
To wireless transport module；
The signal picker is arranged on the outer wall of the outer shaft between outer shaft top and outer shaft sleeve top.
2. Transmission system according to claim 1, it is characterised in that: the signal picker be built-in with will be collected under
Rotor measuring signal is converted into the analog-to-digital conversion module of digital signal.
3. Transmission system according to claim 2, it is characterised in that: the wireless transport module is built-in with the storage number
The memory module of word signal.
4. Transmission system according to claim 1 to 3, it is characterised in that: the inner shaft is internally provided at least one
A tee connector.
5. Transmission system according to claim 1 to 3, it is characterised in that: the upper rotor signal outside the inner shaft passes
Defeated line classification is fixed on propeller hub.
6. Transmission system according to claim 1 to 3, it is characterised in that: the lower rotor signal transmssion line classification is solid
It is scheduled on lower propeller hub.
7. Transmission system according to claim 1 to 3, it is characterised in that: the signal picker is cyclic structure,
It is disposed around on outer shaft.
8. Transmission system according to claim 1 to 3, it is characterised in that: the wireless transport module is cyclic annular knot
Structure is disposed around on outer shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510251615.6A CN105070003B (en) | 2015-05-18 | 2015-05-18 | The Transmission system of co-axial helicopter rotor measuring signal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510251615.6A CN105070003B (en) | 2015-05-18 | 2015-05-18 | The Transmission system of co-axial helicopter rotor measuring signal |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105070003A CN105070003A (en) | 2015-11-18 |
| CN105070003B true CN105070003B (en) | 2019-05-17 |
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ID=54499357
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510251615.6A Expired - Fee Related CN105070003B (en) | 2015-05-18 | 2015-05-18 | The Transmission system of co-axial helicopter rotor measuring signal |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105070003B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112419832A (en) * | 2020-11-20 | 2021-02-26 | 中国直升机设计研究所 | Upper rotor control mechanism for coaxial helicopter model rotor test |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2589335Y (en) * | 2002-09-13 | 2003-12-03 | 李晓阳 | Electromagnetic heading control device for coaxial double-rotor helicopter |
| CN1645284A (en) * | 2004-12-17 | 2005-07-27 | 华北电力大学（北京） | Power circuit scanning test robot airplane and controlling system |
| CN101421157A (en) * | 2004-04-14 | 2009-04-29 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| CN104481894A (en) * | 2014-11-28 | 2015-04-01 | 东营广兴石油装备有限公司 | Centrifugal electric submersible pump downhole torque testing system |
-
2015
- 2015-05-18 CN CN201510251615.6A patent/CN105070003B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2589335Y (en) * | 2002-09-13 | 2003-12-03 | 李晓阳 | Electromagnetic heading control device for coaxial double-rotor helicopter |
| CN101421157A (en) * | 2004-04-14 | 2009-04-29 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| CN1645284A (en) * | 2004-12-17 | 2005-07-27 | 华北电力大学（北京） | Power circuit scanning test robot airplane and controlling system |
| CN104481894A (en) * | 2014-11-28 | 2015-04-01 | 东营广兴石油装备有限公司 | Centrifugal electric submersible pump downhole torque testing system |
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| CN105070003A (en) | 2015-11-18 |
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Granted publication date: 20190517 Termination date: 20200518 |