CN105070003A - Coaxial helicopter rotor measurement signal transmission system - Google Patents
Coaxial helicopter rotor measurement signal transmission system Download PDFInfo
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- CN105070003A CN105070003A CN201510251615.6A CN201510251615A CN105070003A CN 105070003 A CN105070003 A CN 105070003A CN 201510251615 A CN201510251615 A CN 201510251615A CN 105070003 A CN105070003 A CN 105070003A
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Abstract
The present invention relates to a coaxial helicopter rotor measurement signal transmission system so as to solve the problems of complex signal transmission wiring, high signal transmission wire replacement difficulty and structure defect caused by notch in the prior art. The system comprises a lower rotor measurement signal transmission device, wherein the lower rotor measurement signal transmission device comprises a lower rotor signal transmission line and a wireless transmission module for receiving and transmitting a lower rotor measurement signal, and the wireless transmission module is arranged on the outer wall of the outer shaft between the top end of the outer shaft and the top end of the outer shaft bush. According to the present invention, the wireless transmission module is used to receive and transmit the lower rotor measurement signal so as to achieve the wireless transmission of the lower rotor measurement signal, such that the groove arrangement on the outer shaft or the outer shaft bush is not required, and the structure defect problem is avoided; the wiring is simple so as to easily replace or adjust; and the wireless transmission module is arranged on the outer shaft between the top end of the outer shaft and the top end of the outer shaft bush, such that the relative movement between the outer shaft and the outer shaft bush can not be affected.
Description
Technical field
The present invention relates to a kind of transmission system of co-axial helicopter rotor measuring-signal.
Background technology
Compared with single rotor tail-rotor helicopter, co-axial helicopter adopts two of upper and lower contrarotation secondary rotors to balance rotor torque, so do not need tail-rotor.Such structure has compact conformation, is convenient to advantages such as safeguarding, aerodynamic characteristics is symmetrical, hoverning stability is good, accident rate is low.Certainly, co-axial helicopter also has its unavoidable shortcoming, and comparatively outstanding shortcoming there is aerodynamic interference between upper and lower rotor, and concentrates on an axis due to the catanator of two secondary rotors, causes complex structure and intensive.Therefore, experimental studies a large amount of in co-axial helicopter R&D process is absolutely necessary, and modal mode sets up Test-bed to carry out ground experiment.
When setting up co-axial helicopter Test-bed, the reasonable Arrangement of signal transmssion line is emphasis is also difficult point.The signal transmssion line of single rotor tail-rotor helicopter Test-bed leads to the bottom of Test-bed from axle in hollow, then gathered the measuring-signal that signal transmssion line transmits by modes such as collector ring.But axle in the internal sleeve of outer shaft connected due to co-axial helicopter Test-bed up and down rotor is equipped with and is connected with upper rotor, interior axle wherein and outer axle steer are contrary, therefore descend rotor cannot adopt the mode connected up in axle.
Find through investigation, the mode that under existing co-axial helicopter Test-bed, rotor many employings axle connects up outward, needs to slot on outer shaft or outer shaft sleeve, reserves wiring space in concrete operations.But this mode has following defect:
(1) signal transmssion line is tediously long, loaded down with trivial details,
(2) comparatively large according to the difficulty of different experiment increases in demand or replacing signal transmssion line, practicality is not strong;
(3) notch that connects up makes Test-bed occur fault of construction, causes stress to be concentrated, easily occurs fatigure failure, affect the serviceable life of Test-bed, and likely jeopardize the safety of experimenter.
Summary of the invention
Technical matters to be solved by this invention is the fault of construction problem that the wiring of prior art signal transmssion line is complicated, signal transmssion line replacing difficulty is large and notch causes.
For solving above-mentioned technical matters, the present invention proposes a kind of transmission system of co-axial helicopter rotor measuring-signal.
The transmission system of co-axial helicopter rotor measuring-signal of the present invention, comprise lower rotor measuring-signal transmitting device, described lower rotor measuring-signal transmitting device comprises the lower rotor signal transmssion line and reception that carry lower rotor measuring-signal and sends the wireless transport module of described lower rotor measuring-signal; Wherein, described wireless transport module is arranged on the outer wall of the outer shaft between outer shaft top and outer shaft sleeve top.
Further, described transmission system also comprises the signal picker be connected with described lower rotor signal transmssion line, the equal circuit of described wireless transport module, in order to gather the lower rotor measuring-signal on described lower rotor signal transmssion line, and the lower rotor measuring-signal collected is sent to wireless transport module; Described signal picker is arranged on the outer wall of the outer shaft between outer shaft top and outer shaft sleeve top.
Further, described signal picker is built-in with the analog-to-digital conversion module lower rotor measuring-signal collected being converted into digital signal.
Again further, described wireless transport module is built-in with the memory module storing described digital signal.
Further, described transmission system also comprises rotor measuring-signal transmitting device, and described upper rotor measuring-signal transmitting device comprises the upper rotor signal transmssion line being located in interior axle inside, and described upper rotor signal transmssion line carries rotor measuring-signal.
Further, the inside of described interior axle is provided with at least one tee connector.
Further, the upper rotor signal transmssion line classification of described interior axle outside is fixed on propeller hub.
Preferably, described lower rotor signal transmssion line classification is fixed on lower propeller hub.
Preferably, described signal picker is ring texture, is around on outer shaft.
Preferably, described wireless transport module is ring texture, is around on outer shaft.
The transmission system of co-axial helicopter rotor measuring-signal of the present invention has following beneficial effect:
First, the present invention utilizes wireless transport module to receive and sends backspin wing measuring-signal, achieves the wireless transmission of lower rotor measuring-signal.Because this mode does not need to slot under outer shaft or outer shaft sleeve, therefore avoid the fault of construction problem because wiring notch causes, while the serviceable life extending Test-bed, also improve security performance.
Secondly, due to the mode of rotor measuring-signal under employing wireless transmission, wiring is succinct, and be convenient to change or adjustment, practicality is higher.
Finally, because 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 can not be had influence on.
Accompanying drawing explanation
Can understanding the features and advantages of the present invention clearly by reference to accompanying drawing, accompanying drawing is schematic and should not be construed as and carry out any restriction 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 zoomed-in view of A in Fig. 1;
Fig. 3 shows the zoomed-in view of B in Fig. 1.
Embodiment
Below in conjunction with accompanying 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, this transmission system comprises lower rotor measuring-signal transmitting device, and this rotor measuring-signal transmitting device comprises the lower rotor signal transmssion line 8 that carries lower rotor measuring-signal and receives and send the wireless transport module 10 of backspin wing measuring-signal;
Wherein, wireless transport module 10 is arranged on the outer wall of the outer shaft 6 between the top of outer shaft 6 and the top of outer shaft sleeve 5.
In order to understand the technique scheme of the present embodiment, simple introduction is done to the correlated parts on co-axial helicopter Test-bed and annexation thereof below, but not as the restriction to technique scheme.
The upper and lower rotor contrarotation of co-axial helicopter, upper rotor is connected with interior axle 1, and lower rotor is connected with outer shaft 6, interior axle 1 is set in outer shaft 6, outer shaft 6 is set in outer shaft sleeve 5, and turning to of interior axle 1 and outer shaft 6 is contrary, and also relative motion between outer shaft 6 and outer shaft sleeve 5.Outer shaft 6 is provided with lower propeller hub 7, interior axle 1 is provided with propeller hub 2.Lower rotor, outer shaft 6 and lower propeller hub 7 synchronous axial system, upper rotor, interior axle 1 and upper propeller hub 2 synchronous axial system.
The transmission system that the present embodiment provides has the following advantages:
First, the present invention utilizes wireless transport module 10 to receive and sends backspin wing measuring-signal, achieves the wireless transmission of lower rotor measuring-signal.Extraneous radio receiver receives the lower rotor measuring-signal that wireless transport module 10 sends, then imports computing machine and process, and just can analyze ground experiment.Because this mode does not need, at outer shaft 6 or outer shaft sleeve 5 times flutings, therefore to avoid the fault of construction problem because wiring notch causes, while the serviceable life extending Test-bed, also improve security performance.
Secondly, due to the mode of rotor measuring-signal under employing wireless transmission, wiring is succinct, and be convenient to change or adjustment, practicality is higher.
Finally, because wireless transport module 10 is arranged on the outer wall of outer shaft 6, therefore wireless transport module 10 and outer shaft 6 synchronous axial system, again because outer shaft 6 and lower rotor synchronous axial system, so wireless transport module 10, outer shaft 6 and lower rotor are geo-stationary.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, namely wireless transport module 10 is arranged on the part that outer shaft 6 does not enter outer shaft sleeve 5, so can not have influence on the relative motion between outer shaft 6 and outer shaft sleeve 5.
Lower rotor signal transmssion line 8 is drawn from lower rotor, lower rotor signal transmssion line 8 carries lower rotor measuring-signal, this lower rotor measuring-signal is the measuring-signal gathering the lower dynamic component such as rotor blade and/or lower pitch-change-link, therefore according to the difference of acquisition component, lower rotor measuring-signal has one at least.Meanwhile, the present invention does not limit the number of wireless transport module 10, can be one, sends all lower rotor measuring-signals for receiving; Also can be multiple, each receives and sends a kind of lower rotor measuring-signal.
How to gather lower rotor measuring-signal to wireless transport module 10 in the present embodiment not limit, can, at the built-in collecting unit of wireless transport module 10, external acquisition module also can be adopted to carry out the collecting work of lower rotor measuring-signal.
Further, due to outer shaft 6 when rotated, the wireless transport module 10 be connected with outer shaft 6 can be subject to certain centrifugal force, likely can damage or make wireless transport module 10 to install instability to wireless transport module 10.So wireless transport module 10 can be set to ring texture, be around on outer shaft 6, make the radial dimension of wireless transport module 10 less like this, ensure the stable of its serviceability as far as possible.
Embodiment 2
As shown in Figure 1,3, the present embodiment, on the basis of above-described embodiment 1, limits further:
The transmission system that the present embodiment provides also comprises the signal picker 9 be connected with lower rotor signal transmssion line 8, the equal circuit of wireless transport module 10, in order to gather the lower rotor measuring-signal on lower rotor signal transmssion line 8, and the lower rotor measuring-signal collected is sent to wireless transport module 10;
Signal picker 9 is arranged on the outer wall of the outer shaft 6 between the top of outer shaft 6 and the top of outer shaft sleeve outer shaft cylinder 5.
The present embodiment adopts a kind of external signal picker 9, gathers, and the lower rotor measuring-signal collected is sent to wireless transport module 10 to the lower rotor measuring-signal on lower rotor signal transmssion line 8.The signal picker 9 of this mode, relative to built-in collecting unit, has flexible, adjustable advantage.
Signal picker 9 is arranged on the outer wall of outer shaft 6, and therefore signal picker 9 and outer shaft 6 synchronous axial system, again because outer shaft 6 and lower rotor synchronous axial system, so signal picker 9, outer shaft 6 and lower rotor are geo-stationary, the problem of coiling can not occur.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, namely signal picker 9 is arranged on the part that outer shaft 6 does not enter outer shaft sleeve 5, so can not have influence on the relative motion between outer shaft 6 and outer shaft sleeve 5.The particular location of signal picker 9 is not limited, such as can below lower propeller hub 7 40mm outer shaft 6 outer wall on.
The present embodiment does not limit the number of signal picker 9, can be one, for gathering all lower rotor measuring-signals; Also can be multiple, each receives and sends a kind of lower rotor measuring-signal.
Further, because the transmission of digital signal is relative to the transmission of simulating signal, there is better antijamming capability, so analog-to-digital conversion module can be arranged in signal picker 9, for the lower rotor measuring-signal collected is converted into digital signal, then digital signal sends to wireless transport module 10, sends digital signal.
Further, in order to avoid the loss of the radio receiver fault in the external world or reason the causes signal transmission such as wireless signal is not good, memory module can being set in wireless transport module 10, for storing digital signal, avoiding losing.
Further, due to outer shaft 6 when rotated, the signal picker 9 be connected with outer shaft 6 can be subject to certain centrifugal force, likely can damage or make signal picker 9 to install instability to signal picker 9.So signal picker 9 can be set to ring texture, be around on outer shaft 6, make the radial dimension of signal picker 9 less like this, ensure the stable of its serviceability as far as possible.
Further, according to the difference of acquisition component, lower rotor measuring-signal is incessantly a kind of, and lower rotor signal transmssion line 8 is also with regard to more than one.In order to prevent from descending at the trial rotor signal transmssion line 8 mixed and disorderly or be hard to tell, by lower rotor signal transmssion line 8 taxonomic revision, and after being fixed on lower propeller hub 7, then lead-in signal collector 9.Concrete mode classification can be classified or adopt the transmission line of different colours by tee connector.
Embodiment 3
As shown in Figure 1, 2, the present embodiment, on the basis of above-described embodiment 1, limits further:
The transmission system that the present embodiment provides also comprises rotor measuring-signal transmitting device, and upper rotor measuring-signal transmitting device comprises the upper rotor signal transmssion line 4 being located in interior axle 1 inside, and upper rotor signal transmssion line 4 carries rotor measuring-signal.
Upper propeller hub 2 is arranged on the upper end of interior axle 1, upper rotor, upper propeller hub 2 and interior axle 1 geo-stationary, the upper rotor signal transmssion line 4 of drawing from upper rotor imports interior axle 1 inside from the top of interior axle 1, then be connected with the collector ring of interior axle 1 bottom, upper rotor measuring-signal on upper rotor signal transmssion line 4 is exported to outside cable reception device by collector ring, upper rotor measuring-signal is imported computer disposal by cable reception device, and can analyze ground experiment.On this, rotor measuring-signal is the measuring-signal gathering the upper dynamic component such as rotor blade and/or upper pitch-change-link.
The mode of wire transmission is adopted to transmit upper rotor measuring-signal in the present embodiment, the mode of wireless transmission is adopted to transmit lower rotor measuring-signal, because wire transmission mode reliability is high, cost is low, wireless transmission method connects up succinctly, avoids fault of construction and is convenient to change, according to the own characteristic of co-axial helicopter, while ensureing to reduce costs, improve the overall performance of co-axial helicopter ground experiment platform as far as possible.
Further, for the ease of arranging upper rotor signal transmssion line 4, classify, the inside of interior axle 1 is provided with at least one tee connector 3.Tee connector 3 there are multiple points of string holes, the effect of upper rotor signal transmssion line 4 being classified, fixing can be played.The number of tee connector 3 is set according to the length of interior axle 1, such as, a tee connector 3 is set respectively at the top of interior axle 1, bottom and middle part.
Further, according to the difference of acquisition component, upper rotor measuring-signal is not only a kind of, and upper rotor signal transmssion line 4 is also with regard to not only one.Mixed and disorderly or be hard to tell in order to prevent from going up at the trial rotor signal transmssion line 4, by upper rotor signal transmssion line 4 taxonomic revision, and after being fixed on propeller hub 2, then the inside of axle 1 in importing.Concrete mode classification can be classified or adopt the transmission line of different colours by tee connector 3.
In sum, the present invention has the following advantages:
(1) present invention, avoiding the fault of construction problem that wiring notch causes;
(2) wiring succinct, be convenient to change or adjustment;
(3) centrifugal force that is subject to of signal picker of the present invention, wireless transport module is little, stable work in work;
(4) first lower rotor measuring-signal is converted into digital signal to send again, improves the antijamming capability of signal;
(5) memory module is to digital signal storage, avoids the loss of signal;
(6) utilize tee connector combing transmission line, avoid the mixed and disorderly of transmission line;
(7) respectively respective transmissions line classified at upper propeller hub or lower propeller hub place and fix, further avoid the mixed and disorderly of transmission line.
It should be noted that the present invention is not only applicable to the ground experiment of co-axial helicopter, also can the taking a flight test of co-axial helicopter, to overhaul or in the process such as maintenance.
Should be appreciated that technical characteristic in above each embodiment and embodiment can combination in any when not conflicting, the technical scheme after combination is still within protection scope of the present invention.
Although describe embodiments of the present invention by reference to the accompanying drawings, but those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, such amendment and modification all fall into by within claims limited range.
Claims (10)
1. the transmission system of a co-axial helicopter rotor measuring-signal, it is characterized in that: comprise lower rotor measuring-signal transmitting device, described lower rotor measuring-signal transmitting device comprises the lower rotor signal transmssion line and reception that carry lower rotor measuring-signal and sends the wireless transport module of described lower rotor measuring-signal;
Wherein, described wireless transport module 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 characterized in that: also comprise the signal picker be connected with described lower rotor signal transmssion line, the equal circuit of described wireless transport module, in order to gather the lower rotor measuring-signal on described lower rotor signal transmssion line, and the lower rotor measuring-signal collected is sent to wireless transport module;
Described signal picker is arranged on the outer wall of the outer shaft between outer shaft top and outer shaft sleeve top.
3. transmission system according to claim 2, is characterized in that: described signal picker is built-in with the analog-to-digital conversion module lower rotor measuring-signal collected being converted into digital signal.
4. transmission system according to claim 3, is characterized in that: described wireless transport module is built-in with the memory module storing described digital signal.
5. according to the arbitrary described transmission system of claim 1-4, it is characterized in that: also comprise rotor measuring-signal transmitting device, described upper rotor measuring-signal transmitting device comprises the upper rotor signal transmssion line being located in interior axle inside, and described upper rotor signal transmssion line carries rotor measuring-signal.
6. transmission system according to claim 5, is characterized in that: the inside of described interior axle is provided with at least one tee connector.
7. transmission system according to claim 5, is characterized in that: the upper rotor signal transmssion line classification of described interior axle outside is fixed on propeller hub.
8. according to the arbitrary described transmission system of claim 1-4, it is characterized in that: described lower rotor signal transmssion line classification is fixed on lower propeller hub.
9., according to the arbitrary described transmission system of claim 2-4, it is characterized in that: described signal picker is ring texture, is around on outer shaft.
10., according to the arbitrary described transmission system of claim 1-4, it is characterized in that: described wireless transport module is ring texture, is 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 |
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| Publication Number | Publication Date |
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| CN105070003A true CN105070003A (en) | 2015-11-18 |
| CN105070003B CN105070003B (en) | 2019-05-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510251615.6A Expired - Fee Related CN105070003B (en) | 2015-05-18 | 2015-05-18 | The Transmission system of co-axial helicopter rotor measuring signal |
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Cited By (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 | Rotor craft |
| 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 | Rotor craft |
| 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 |
Cited By (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 |
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Granted publication date: 20190517 Termination date: 20200518 |