CN205228398U - Centrum survey control box - Google Patents
Centrum survey control box Download PDFInfo
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- CN205228398U CN205228398U CN201520965922.6U CN201520965922U CN205228398U CN 205228398 U CN205228398 U CN 205228398U CN 201520965922 U CN201520965922 U CN 201520965922U CN 205228398 U CN205228398 U CN 205228398U
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- blade
- centrum
- front shroud
- control box
- rotor
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Abstract
The utility model provides a centrum survey control box which includes: front shroud, back casing the front end of front shroud is provided with LED pilot lamp and charactron, back casing with be provided with the 2nd power module, microprocessor, control button between the front shroud, the 2nd power module is used for for the electronic parts in the centrum survey control box supplies power, microprocessor with control button and outside rotor centrum monitoring devices electricity are connected.
Description
Technical field
The utility model relates to rotor monitoring field, particularly a kind of centrum Survey control box of aircraft.
Background technology
Cone monitoring equipment is the cone monitoring of the rotor realizing helicopter and the visual plant safeguarded, the centrum degree of the degree of stability of helicopter flight and its rotor is closely related, only has the consistance of the centrum degree of each blade in predetermined scope, the flight of helicopter just has good stability, the consistance of the centrum degree of each blade of rotor is higher, namely the same tapering of rotor is higher, and the flight of helicopter is more stable.
Existing cone monitoring technology concrete condition is as follows:
A) ground maintenance personnel stick target on the every a slice blade of helicopter;
B) helicopter must be driven on ground, and blade is rotated;
C) ground maintenance personnel are glimmered by the target utilizing stroboscope and face toward on blade;
D) when stroboscope glimmers to target, maintainer can find out the height of target by eyes, thus locates that sheet blade relative datum blade and have larger deviation.
The utility model people is carrying out finding in research process of the present utility model, and prior art exists following technological deficiency:
A) each cone monitoring all needs too many manual operation;
B) be only applicable to helicopter drive on ground, blade is rotated, thus carry out cone survey, cannot monitor aloft helicopter;
C) the same taper value of eye recognition blade: ground maintenance personnel are glimmered by the target utilizing stroboscope and face toward on blade, when stroboscope glimmers to target, maintainer can find out the height of target by eyes, thus locates that sheet blade relative datum blade and have larger deviation.
Utility model content
One of the utility model embodiment object is to provide a kind of centrum Survey control box, its Structural Integrity frame, easy to assembly, and application simple installation, easy to operate, can be concise and to the point show the centrum measurement result of current rotor for crew, and facilitate crew to operate the work of the centrum measurement component controlled on aircraft rotary wing.
A kind of centrum Survey control box that the utility model embodiment provides, comprising:
Front shroud, back casing, the front end of described front shroud is provided with LED light and charactron, second source module, microprocessor, control button is provided with between described back casing and described front shroud, described second source module is used for for the electronic unit in centrum Survey control box is powered, and described microprocessor is electrically connected with the rotor centrum monitoring device of described control button and outside.
Alternatively, the surrounding of described front shroud is all wider than the front end surrounding of back casing.
Alternatively, four summit places of described front shroud are provided with screw hole, when mounted, to be installed on the operational platform described front shroud and equal with platform by screw, described back casing is embedded in operating platform.
Alternatively, described front shroud, back casing all adopt metal material to make.
Alternatively, between described front shroud, back casing all between be separated with flexible heat outlet washer.
Therefore, adopt the centrum Survey control box of the present embodiment, its Structural Integrity frame, easy to assembly, and application simple installation, easy to operate, can be concise and to the point show the centrum measurement result of current rotor for crew, and facilitate crew to operate the work of the centrum measurement component 200 controlled on aircraft rotary wing.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, forms a application's part, does not form improper restriction of the present utility model, in the accompanying drawings:
Fig. 1 is the utility model embodiment 1 rotor centrum monitoring method schematic flow sheet;
The electrical block diagram of rotor centrum monitoring device of Fig. 2 for providing in the utility model embodiment 1,2;
The physical construction schematic diagram of rotor centrum monitoring device of Fig. 3 for providing in the utility model embodiment 1,2;
The electrical block diagram of centrum Survey control box of Fig. 4 for providing in the utility model embodiment 1,2;
The physical construction schematic diagram of centrum Survey control box of Fig. 5 for providing in the utility model embodiment 1,2;
The electrical block diagram of rotor centrum monitoring device of Fig. 6 for providing in the utility model embodiment 1,2.
Embodiment
Describe connection accompanying drawing and specific embodiment in detail the utility model below, be used for explaining the utility model in this illustrative examples of the present utility model and explanation, but not as to restriction of the present utility model.
Embodiment 1:
Shown in Fig. 1-6, present embodiments provide a kind of method for the monitoring of aircraft rotary wing centrum, when carrying out the monitoring of aircraft rotary wing centrum, the rotor of aircraft is at the uniform velocity rotation status all the time, when monitoring, tested aircraft can be in any state of flight, also can be in ground driving state.
This monitoring method mainly comprises the following steps:
Step 101: position angle speed probe 201 receives the reflected light of baseline blade reflection, exports rotor azimuth signal to frequency multiplier circuit 202.
The reflected light of the present embodiment preferably but be not limited to infrared light.
The rotational speed of rotor monitored by position angle speed probe 201, swing circle according to rotor generates rotor azimuth signal, the cycle of this rotor azimuth signal is identical with the swing circle of rotor, and position angle speed probe 201 exports this rotor azimuth signal to frequency multiplier circuit 202.
As the signal of the present embodiment, can be selected one of them as baseline blade in multiple blades of rotor, a reflecting piece is sticked in the blade root portion of baseline blade, position angle speed probe 201 reflexes to the reflected light of this azimuth sensor by this reflecting piece of monitoring, and determine the swing circle of rotor, namely the reflected light that position angle speed probe 201 often receives reflecting piece reflection sends a rotor azimuth signal to frequency multiplier circuit 202.
Step 102: frequency multiplier circuit 202 for Clock Multiplier Factor, carries out process of frequency multiplication to rotor azimuth signal with the paddle blade number of current tested aircraft, generates sync pulse jamming signal, exports this sync pulse jamming signal to camera 204 driving circuit 203.
If the paddle blade number N on the rotor of current tested aircraft is 10, a frequency-doubled signal is obtained after then the rotor azimuth signal of frequency multiplier circuit 202 to input carries out 10 times of frequencys multiplication, sync pulse jamming signal using this frequency-doubled signal as the present embodiment, exports this sync pulse jamming signal to camera 204.
Within arbitrary rotor azimuth signal cycle, namely each sync pulse jamming signal is corresponding with each blade respectively.Namely within arbitrary rotor azimuth signal cycle, frequency multiplier circuit 202 exports 10 sync pulse jamming signals backward, each sync pulse jamming signal is sequentially corresponding with every sheet blade respectively, so that camera 204 is taken pictures to a blade respectively confiscating a sync pulse jamming signal, in a swing circle, camera 204 sequentially completes the shooting to 10 blades.
Step 103: control camera 204 according to the sync pulse jamming signal received, shooting obtains the image of each blade.
When taking, rotor according to predetermined speed, at the uniform velocity rotates all the time.
The camera 204 of the present embodiment is fixedly mounted on tested aircraft, preferably but be not limited to be fixedly mounted on the mast footpath of aircraft.
Ideally, camera 204 often receives a sync pulse jamming signal, then take the image of blade first, and within a rotor azimuth signal cycle, (namely in the rotor wing rotation duration of a week) camera 204 order takes the image of each blade of rotor.
Step 104: according to the image of each blade, determines the height of each blade, according to the height of each blade and the height of baseline blade, determines the common tapering of each blade of rotor.
After the image obtaining each blade, the image of blade is calculated to the height (coordinate according to the pixel of the blade on image can calculate its position) of each blade, the position height of each blade is deducted the position height of baseline blade, namely the relative height of each blade relative to baseline blade is obtained, can determine the same tapering of current rotor according to the relative height of each blade, the calculating of concrete same tapering can be, but not limited to conventionally carry out.
Therefore, application the present embodiment technical scheme, can by the mode of automatic test, in each swing circle, sequentially take the image of each blade, by the image to each blade and determine the relative height of each blade relative to baseline blade of aircraft, and finally determine the same tapering of the blade on rotor.Relative to prior art, the present embodiment technical scheme in measuring process without the need to manual operation, without the need to reequiping aircraft, also without the need to limiting the flight data dispose of tested aircraft, no matter at aircraft for any state of flight or for bottom surface state, application the present embodiment technical scheme can be tested the same tapering of the rotor of aircraft, is conducive to the degree of accuracy improving monitoring, improves the security of aircraft flight.
As the signal of the present embodiment, the present embodiment can in multiple swing circle, to the shooting that each blade carries out repeatedly, the image of every blade is made to be respectively multiframe, to superpose the multiple image of each blade, then image procossing is carried out to the image after superposition, thus the image that position that is more clear, blade, the border obtaining this blade is more accurate.
As the signal of the present embodiment, the camera lens of the camera 204 of the present embodiment preferably but be not limited to the blade tip position aiming at blade, specifically take the image of the blade tip of each blade, using the position of the blade tip of blade as the height and position on the border of this blade tip, the utility model is carrying out finding in the utility model research, the image of the blade tip of blade and the aberration of background better, it has preferably border property, selects blade tip to be more conducive to as the position height of blade improving the degree of accuracy measured.
As the signal of the present embodiment, the present embodiment is when carrying out the image taking of blade, for controlling the CPU control module 205 of camera 204 also according to the cycle of sync pulse jamming signal, and the cycle of rotor azimuth signal, and determine the serial number information of the current blade that should take, if the image of the current actual blade to these needs of failing to take, namely the leakage that there is blade image is clapped, then CPU control module 205 controls the shooting of camera 204 time-out, until the end cycle of this rotor azimuth signal, and this leakage clap the sync pulse jamming signal corresponding to blade arrive time, CPU control module 205 controls the sync pulse jamming signal continuation shooting that camera 204 is subject to according to this its, the blade that this leakage is clapped is taken pictures, and continue sequentially to take other blades according to normal flow, and upper once occur certain blade leak clap time, according to above-mentioned treatment scheme process, until the amount of images of each blade of shooting reaches predetermined quantity.
For example: within a rotor azimuth signal cycle, the image of the i-th blade leaks to be clapped, then CPU control module 205 controls the shooting of described camera 204 time-out, until next rotor azimuth signal arrives, described camera 204 starts one by one to follow-up each described blade shooting from the i-th blade, until wherein i is greater than the natural number that 1 is less than N, N is the total tablet number of blade.
In detail, reflecting piece is to position angle speed probe 201 reflective light (preferred infrared light), and the rotor position angle speed probe 201 that often turns around receives a heliogram, and position angle speed probe 201 produces a rotor azimuth signal.Frequency multiplier circuit 202 often receives a rotor azimuth signal, carries out frequency multiplication according to rotor azimuth signal, generates a sync pulse jamming signal.If when the paddle blade number of current rotor is 10, then frequency multiplier circuit 202 generates 10 pulses (i.e. sync pulse jamming signal) according to rotor azimuth signal, control camera 204 sequentially to go to clap this 10 blades, get the image of each blade of needs after having clapped, each blade all has multiple images.
Within first rotor azimuth signal cycle, take the image of ten blades, the sequence number of the image of each blade is respectively 1-10, in next rotor azimuth signal cycle the blade of shooting image be exactly 11-20, by that analogy, suppose that camera 204 leaks the 3rd blade to clap, then within this cycle, suspend shooting, until next rotor azimuth signal arrives, and during the 3rd pulse arrival of sync pulse jamming signal, again take, take the image of the 3rd blade, thus guarantee that the sequence number of the sequence number of image and the blade taken is completely the same, guarantee the order of the image of each blade, and be not easy to confusion.When supposing that the predetermined picture number needing to take each blade is 3, then until when the number of image frames of shooting reaches 30, stop shooting.
As the signal of the present embodiment, after camera 204 obtains the image of every blade according to the shooting of sync pulse jamming signal, the image buffer storage of this blade current shooting obtained is in the memory queue of CPU control module 205, temporarily do not process, to control the workload of cpu controller now, guarantee the accuracy of the control of cpu controller azimuthal speed probe 201, camera 204, avoid Lou clapping leaking image.
As the signal of the present embodiment, be temporarily stored at the image of whole blade after in the memory queue of CPU module, CPU control module 205 starts another thread, CPU control module 205 sequentially reads the image of memory queue, sequentially image procossing is carried out, to determine the height of each blade according to the image of each blade to the described image read by the image processing module in CPU control module 205.
As the signal of the present embodiment, after obtaining image, CPU control module 205 carries out the process of binaryzation black and white according to the algorithm of threshold value to figure, then expansion algorithm is adopted to make the border of image more obvious, then ask largest connected territory remove external infections (such as, suppose that blade drops on image, image there is a shadow, so may there is the image of bird, remove outside interference, block), this part black region of blade, the minimum point of the minimum physical location of pixel is looked for again in black region, point is positioned at the pixel coordinate position of image, according to the mapping relations of the pixel coordinate preset and actual physical location, determine the position height of this blade, thus carry out difference algorithm with the position height of baseline blade, obtain the same tapering of a slurries.
As the signal of the present embodiment, the CPU control module 205 of the present embodiment also preferably but be not limited by LAN (Local Area Network) or communication interface is connected with the data management computer on aircraft, so that data and image are sent to data management computer by CPU control module 205.
As the signal of the present embodiment, data management computer is provided with data management computer communication function module, this module mainly completes and communicates with data management computer, by sending task start instruction to data management computer, recognition function opened by notification data supervisory computer, after data management computer opens recognition function, reverting starting acquisition instructions is to CPU control module 205, Information Monitoring is sent to data management computer by CPU control module 205 again, completes acquisition function.
As the signal of the present embodiment, the CPU control module 205 of track-height measuring system is also by local area wireless network and Ground Processing System wireless connections, so that the common tapering information of each described blade and view data etc. are sent to Ground Processing System by CPU control module 205.Track-height measuring system is connected by the supporting support equipment in Ethernet and ground, carries out maintenance work to track-height measurement mechanism.Track-height measurement mechanism, real-time Transmission shooting image, real time processed images calculate same tapering that same tapering, in real time display cone measurement mechanism device calculate, the image reproducing that participates in measuring, adjustment camera 204 coefficient, to send instruction to slave computer, gather paddle blade number etc. is connected to as long-range.
As the signal of the present embodiment, the CPU control module 205 of the present embodiment is after the same tapering of rotor is determined in calculating, same tapering information is sent to the centrum Survey control box 300 in aircraft, charactron 305 driving circuit 304 and charactron 305 can also be set on centrum Survey control box 300, the current most Datong District tapering recorded is shown by charactron 305, and the blade of this most Datong District tapering, can also but be not limited to show other information, so that crew carries out Real-Time Monitoring to current rotor with tapering.
For example, arrange " measurement mechanism " LED 306 to indicate the duty of the track-height measurement mechanism on aircraft rotary wing, green expression is normal, and redness represents fault;
Arrange " control enclosure " LED 306 to indicate the duty of the cone Survey control box in aircraft, green expression is normal, and redness represents fault;
Arrange " being ready to " LED 306 and whether normally to indicate the work of cone measurement mechanism and cone Survey control box, and whether rotating speed reaches requirement, green expression is normal, red expression fault;
" blade " charactron 305 is set to show the blade number of most Datong District cone value;
The charactron 305 groups of " cone measured value " is set to show the maximum same tapering of blade.
Embodiment 2:
Shown in Fig. 1-6, present embodiments provide a kind of rotor centrum monitoring system, it mainly comprises: centrum measurement mechanism 200 and centrum Survey control box 300, wherein centrum measurement mechanism 200 is arranged on the rotor footpath of aircraft, monitor with the same tapering of the rotor to aircraft, centrum Survey control box 300 is arranged in aircraft, so that the work of crew to centrum Survey control box 300 controls, and checks the same tapering monitoring result of rotor.
Centrum measurement mechanism 200 comprises: the first power module 206, position angle speed probe 201, frequency multiplier circuit 202, camera 204, CPU control module 205, first power module 206 is for providing power supply for each electronic unit in centrum measurement mechanism 200, position angle speed probe 201 is electrically connected with described frequency multiplier circuit 202, and driving circuit, the CPU control module 205 of frequency multiplier circuit 202 and camera 204 are electrically connected respectively.
Position angle speed probe 201 receives the reflected light of baseline blade reflection, rotor azimuth signal is exported to frequency multiplier circuit 202, frequency multiplier circuit 202 for the paddle blade number of current tested aircraft for Clock Multiplier Factor, process of frequency multiplication is carried out to rotor azimuth signal, using the frequency-doubled signal of generation as sync pulse jamming signal, and export sync pulse jamming signal to camera 204; CPU control module 205 is for controlling the image of camera 204 according to each blade of sync pulse jamming signal shooting acquisition, the height of each blade is determined according to the image of each blade, with according to the height of each blade and the height of baseline blade, determine the relative height of each blade relative to baseline blade, thus determine the common tapering of each blade of rotor.Wherein, when taking, each blade, according to predetermined speed, at the uniform velocity rotates;
Centrum Survey control box 300 comprises: second source module 301, microprocessor 302, control button 303, second source module 301 is for powering for the electronic unit in centrum Survey control box 300, microprocessor 302 is electrically connected with control button 303, also be electrically connected with the CPU control module 205 of centrum measurement mechanism 200, for controlling the work of the CPU control module 205 of centrum measurement mechanism 200 to the operation controlling button 303 according to user.
The principle of work of detailed rotor centrum monitoring system is in detail see the description of embodiment 1.
The centrum Survey control box 300 of the present embodiment comprises: front shroud 501 and back casing 502, wherein LED and charactron 305 are arranged on front shroud 501 front end, back casing 502 is fixed on front shroud 501 rear end, a cavity is provided with in back casing 502, when front shroud 501 is connected with back shroud, a seal chamber is formed between them, in this cavity, electronic circuit board is set, include but not limited to second source module 301, microprocessor 302, control button 303, electronic unit such as second source module 301 grade.
As the signal of the present embodiment, the front shroud 501 of the present embodiment all protrudes relative to the width of the surrounding of back casing 502, four summit places of front shroud 501 are provided with screw hole, when mounted, by screw 503 front shroud 501 can be arranged on the operating platform in aircraft and basic equal with platform, and back casing 502 is embedded in operating platform, be conducive to the convenience improving convenience and the application operating installed.
As the signal of the present embodiment, the centrum measurement mechanism 200 of the present embodiment comprises a housing body 401, the rear ends of this housing body 401 is respectively empty, when mounted, camera 204 is made to load in housing body 401 from the rear end of housing body 401, camera lens is towards front end, treat camera 204 and other electronic circuits (the first power module 206, frequency multiplier circuit 202 and CPU control module 205 etc.) all install fix after in housing master, adopt back shroud 402 sealing blocking in housing body 401 rear end, adopt the front end of front shroud 403 shutoff housing body 401, and the front end of front shroud 403 is provided with an opening 404 matched with camera lens, so that blade taken by camera 204, top blind flange 408 sealing is arranged on the top of housing body 401, stretch out at the top of top blind flange 408 and be provided with position angle speed probe 201, the reflected light reflected back with the reflecting piece of monitoring on the blade of rotor and generate rotor azimuth signal.
Shown in figure, the left and right side of housing body 401 is respectively arranged with confronting grooves 405, top blind flange 408 arranges fin 406, housing body 401, front shroud 403, back shroud 402 and top blind flange 408 adopt metal material to make respectively, adopt this to be designed with and be beneficial to the heat dispersion improving this centrum measurement mechanism 200, guarantee the normal work of internal electrical components.
As the signal of the present embodiment, between housing body 401, flexible heat outlet washer 407 is lined with respectively in front shroud 403, back shroud 402 and top blind flange 408, to improve the tightness connected and the problem avoided rigid contact surfaces directly to contact and cause easily being shaken and cause connection easily loosening, and guarantee that thermal conductivity improves heat dispersion.
Above-described embodiment, does not form the restriction to this technical scheme protection domain.The amendment done within any spirit at above-mentioned embodiment and principle, equivalently to replace and improvement etc., within the protection domain that all should be included in this technical scheme.
Claims (5)
1. a centrum Survey control box, is characterized in that, comprising:
Front shroud, back casing, the front end of described front shroud is provided with LED light and charactron, second source module, microprocessor, control button is provided with between described back casing and described front shroud, described second source module is used for for the electronic unit in centrum Survey control box is powered, and described microprocessor is electrically connected with the rotor centrum monitoring device of described control button and outside.
2. centrum Survey control box according to claim 1, is characterized in that,
The surrounding of described front shroud is all wider than the front end surrounding of back casing.
3. centrum Survey control box according to claim 1, is characterized in that,
Four summit places of described front shroud are provided with screw hole, and when mounted, to be installed on the operational platform described front shroud and equal with platform by screw, described back casing is embedded in operating platform.
4. centrum Survey control box according to claim 1, is characterized in that,
Described front shroud, back casing all adopt metal material to make.
5. centrum Survey control box according to claim 4, is characterized in that,
Flexible heat outlet washer is separated with between equal between described front shroud, back casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520965922.6U CN205228398U (en) | 2015-11-26 | 2015-11-26 | Centrum survey control box |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520965922.6U CN205228398U (en) | 2015-11-26 | 2015-11-26 | Centrum survey control box |
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| CN205228398U true CN205228398U (en) | 2016-05-11 |
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| CN201520965922.6U Active CN205228398U (en) | 2015-11-26 | 2015-11-26 | Centrum survey control box |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105258672A (en) * | 2015-11-26 | 2016-01-20 | 广州航新航空科技股份有限公司 | Monitoring method for cone of rotor wing and device and system for measuring cone |
| CN106091112A (en) * | 2016-06-17 | 2016-11-09 | 珠海格力电器股份有限公司 | Indoor apparatus of air conditioner and there is its air-conditioner |
-
2015
- 2015-11-26 CN CN201520965922.6U patent/CN205228398U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105258672A (en) * | 2015-11-26 | 2016-01-20 | 广州航新航空科技股份有限公司 | Monitoring method for cone of rotor wing and device and system for measuring cone |
| CN105258672B (en) * | 2015-11-26 | 2017-11-14 | 广州航新航空科技股份有限公司 | Rotor centrum monitoring method and centrum measurement apparatus and system |
| CN106091112A (en) * | 2016-06-17 | 2016-11-09 | 珠海格力电器股份有限公司 | Indoor apparatus of air conditioner and there is its air-conditioner |
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